RU2188960C1 - Method of energy conversion in power plant (versions), jet-adaptive engine and gas generator - Google Patents

Abstract

FIELD: self-contained drive for high power mobile electric generators, propulsion units of vehicles and other devices and mechanisms. SUBSTANCE: according to proposed method, torque on power plant rotor shaft is obtained owing to reactive thrust created by reactive mass of combustion products produces in periodical combustion chamber and transformed into pulses of supersonic reactive jet getting out of jet device into additional masses connecting device where vacuum is built by reactive jet and supersonic jet of combustion products in this device and additional gas masses are delivered into device, then additional gas masses are accelerated by transmitting to them part of energy of combustion products reactive jet pulses and combined reactive mass is formed to create reactive thrust. According to other version, part of available kinetic energy left after creating a torque is utilized by means of blade turbine which is not kinematically coupled with power shaft. Reactive mass jet flow is converted into kinetic energy of rotation of devices kinematically coupled with this turbine and having inertia mass by means of which it is accumulated and, if necessary, converted into electric energy and potential energy of compressed gas. To convert energy in jet-adaptive engine reactive mass is obtained using several working media of different thermodynamic characteristics. Reactive jet is formed in jet device by means of main working medium featuring high potential energy, this jet is directed into additional masses connecting device and is used as active jet in process of connection. Other working medium of potential energy smaller than that of main working medium is directed to inlet of same connecting device. According to proposed method of energy conversion in gas generator, at partial expansion of combustion products in closed volume of periodical combustion chamber, spool valve is shifted from initial position, in which spring is released and exhaust channel is closed, through certain distance. In process of covering the distance, spring is compressed for accumulating energy provided its return into initial position, and passages for discharge of combustion products are opened. Under action of compressed spring, valve is stopped and return travel is started during which fuel is injected under pressure and compressed air is fed to form fuel-air mixture for following thermodynamic cycle. EFFECT: increased efficiency. 68 cl, 32 dwg

Description

 The group of inventions relates to heat engines, and in particular to a method for converting energy in power plants and engines to generate power on a power shaft. The claimed inventions can be used together or separately for a standalone drive, for example, high-power mobile power generators, propulsion vehicles and other devices and mechanisms, including those working under water or in an aggressive environment with a pressure exceeding atmospheric, as well as to obtain power on the power shaft with the simultaneous production of compressed air, low temperature air, electricity to provide external consumers without connecting additional devices, as in left stationary conditions, and on board a moving vehicle.

 The prior art in this field is characterized by various directions for improving the processes of converting thermal energy from fuel combustion into mechanical energy of rotation of the power shaft of internal combustion engines to transmit power to the consumer. When improving piston and gas turbine engines, the use of methods such as turbocharging, electronic ignition system, increasing the degree of compression, increasing the flow area of valves, etc. improves individual parameters, not excluding fundamental disadvantages, namely that most of the energy in the thermodynamic cycle remains unused, since the high-temperature working fluid is ejected from the piston device until it expands completely, which, along with direct energy losses, requires the use of silencing systems, increasing engine mass and reducing its efficiency, operation modes are controlled by adjusting the amount of fuel, changing the optimal ratio of components to fuels air mixture that impair its completeness of combustion, increasing energy losses and toxicity of emissions; a significant part of the energy is lost during the forced cooling of heat-stressed units with the subsequent removal of heat into the environment; after the vehicle reaches a predetermined speed, it is impossible to reduce the energy consumption to the necessary level sufficient to overcome the dissipative forces of resistance to movement without disconnecting part of the cylinders, or changing their volume, or using multi-stage transmissions; a “idle” mode is required, in which at zero efficiency the engine consumes fuel and pollutes the environment; many auxiliary systems, such as lubrication, clutch, starting, regulation of fuel supply, ignition synchronization, which require energy to drive them, increase the mass of the engine, the complexity of production, maintenance and reduce its reliability.

 The nature of energy conversion in turboshaft gas turbine engines (GTE) gives them certain advantages compared to piston ones: lower specific gravity per unit of power and overall dimensions, easy start-up in the cold season, increased power during engine operation in low-temperature conditions, work on various types and grades of fuel and reduction of toxicity of emissions, significantly fewer engine parts. The value of the efficiency of a gas turbine engine depends on their purpose, design schemes, and parameters of the thermodynamic cycle being implemented. Typical for the implementation of the traditionally used Brighton thermodynamic cycle (with adiabatic compression and expansion, and heat supply to the working fluid at constant pressure) traditionally used in the majority of gas turbine engines, the cost of mechanical work is to compress the air (from 25 to 75%, depending on the degree of heat supply and pressure increase in cycle), even with a large value of thermal efficiency, it is not possible to provide a large value of effective efficiency. Moreover, the possibilities of improving the gas turbine engine working on this cycle by increasing the parameters of the working process (cycle temperature, the degree of pressure increase in it), as well as increasing the efficiency of the elements that carry out the processes of compression, combustion and expansion, are practically exhausted. Increasing the parameters to achieve acceptable thermal efficiency forces the use of heat-resistant materials and the use of active cooling methods for blade turbines, which increases the already large mass due to the principle of their design. In this regard, the one-two-stage rotors of blade turbines used in the gas turbine engine of vehicles have increased inertia, worsening the dynamics of the engine, and the use of multi-stage rotors that provide more complete use of the reactive mass energy, all the more increases the mass and inertia, and therefore it is not practical. As a result, the thermal and kinetic energy of the reactive jet of the working fluid remaining after the vehicles in the blades of the compressor and then the turbine engine turbine is no longer used for useful work and, in the best case, is dissipated in the atmosphere if it does not require the use of jamming systems, further increasing mass and reducing the useful work of expanding the cycle.

 The situation is somewhat better with the use of the energy of the working fluid remaining after creating the moment on the shaft in turbojet engines (turbojet engines) used as jet propulsors of vehicles. Their effective efficiency is increased by using the energy of the working fluid remaining after the turbocharger drive to create reactive thrust. In this case, jet thrust is increased due to a more complete use of the available energy of the jet stream of the thermodynamic circuit to increase the reactive mass while reducing its flow rate and reducing the rate of loss of jet exhaust. For example, due to the ejection of external masses of atmospheric air by a jet stream when installing an ejector nozzle on a turbojet engine. However, the efficiency of this process - the parallel addition of additional masses, in which the stationary jet expiring is the active jet, is low because the coefficient of coupling m (the ratio of the attached mass of air to the reactive mass of the thermodynamic circuit) at initial speeds, when the effect of increased thrust is possible in this process due to atmospheric air ejection, it is insignificant, and after acceleration with an increase in the speed of the incoming air flow, the thrust growth decreases to zero and even decreases t initial thrust of the jet propulsion. In turbojet dual-circuit engines (turbojet engines), due to the transfer of part of the energy of the internal thermodynamic circuit to the fan, which compresses the atmospheric air in the external circuit to form additional reactive mass, the amount of connected air and the relative flow rate of the increased reactive mass are increased in comparison with the process of connection in the ejector. Moreover, these engines can be adapted to flight conditions by changing the bypass ratio m (the ratio of the mass of air connected through the external circuit to the reactive mass of the internal thermodynamic circuit) to increase efficiency. However, due to the large magnitude of the mechanical work of compression of the Brighton cycle, the turbojet engines, like turbojet engines, have a low efficiency of the thermodynamic circuit with a large mass of the turbocompressor of the gas generator, and the coefficient m and the efficiency of their jet propulsion is less than that of a screw or fan propulsion, with a slight difference cruising flight speeds, moreover, an increase in their double-circuit speed (at the maximum speed limits of the jet stream of the thermodynamic circuit that are economically feasible in this cycle), increasing traction will further reduce the speed of the reactive mass and reduce cruising speed, narrowing the scope of their application.

 The closest set of essential features to the method of converting energy in a power plant is the method using a radial centrifugal turbine - a jet engine, described in the article "Combined power unit + flywheel". Automotive industry, 1996 , 11, p. 11,12 and continuation-1997., 1, p. 17., Author Nekrasov V.G. The torque on the power shaft of the rotor of the jet engine is obtained due to jet propulsion created by the reactive mass of combustion products flowing out of the jet device, and to obtain the reactive mass, they spend energy to compress atmospheric air in the compressor and heat it in the combustion chamber. However, as with the use of Brighton's tempera-dynamic cycle in other gas turbine engines, the efficiency of the power unit in this method cannot be high.

 As a prototype of another variant of the method of energy conversion in a power plant, the method described in the article "AGTD. Structural schemes" is used. Automotive industry, 1996, 6, p. 16-21, author Nekrasov V.G. In the schemes under consideration, part of the available energy of the reactive mass remaining after creating the moment on the power shaft is disposed of using a heat exchanger or gas turbine with a super flywheel. The use of a heat exchanger increases mass, and a super-flywheel requires a complex magnetic rotor suspension or a complex bearing lubrication system.

 The closest analogue of the proposed method for converting energy in an adaptive jet engine is described in Russian patent 2093715 from 10.20.1997. , authors Kondrashov B.M., Sayapin V.V. The jet engine is a radial centrifugal turbine with 100% reactivity, creating a moment on the shaft due to the reactive mass flowing out of the inkjet devices. The main advantage of a jet engine when creating power, compared with traditionally used blade turbines, is many times less inertia of the rotor, which makes it possible to obtain a more dynamic system when using it. However, due to speed losses, which constitute a significant part of the available energy of the jet exhaust of its inkjet devices, which use narrowing nozzles or Laval nozzles, the jet engine has a low efficiency. In addition, the use of these nozzles causes energy losses associated with the over-expansion or under-expansion of the working fluid when the pressure changes before their critical section, which further reduces the efficiency and limits its scope.

 In the following presentation, by an adaptive jet engine we mean an engine in which, in order to achieve optimal efficiency when creating power in multi-mode applications, the magnitude and thermodynamic characteristics of the reactive mass are controlled by changing the number and parameters of the jet devices involved in its creation and changing parameters of the process of joining additional masses.

 The proposed method of energy conversion uses a thermodynamic cycle with heat supply at a constant volume, which allows to obtain a higher efficiency and specific power of a gas turbine engine. This cycle is implemented in gas generators based on periodic combustion chambers. The closest analogue of the method of energy conversion in a gas generator is considered in the work "Optimization of phase distribution in gas turbine engine of periodic combustion". Izv. Universities. Engineering. 1993 10-12. Page 44-48. During combustion in a closed volume of the periodic combustion chambers, in each thermodynamic cycle the pressure rises and the available work of expanding the combustion products increases. Known schemes for organizing the combustion process in these chambers are quite complex due to the need to coordinate the duration of the processes of filling, combustion and expansion of gas with phase distribution, i.e. with the moments of opening and closing the valves to ensure optimal efficiency of the gas generator in various modes, and in addition, they do not provide the specified amplitude and duration of the pulses of the working fluid when changing the frequency of thermodynamic cycles.

 The technical task of this group of inventions is the creation of effective energy conversion methods that provide high efficiency when creating power at various operating modes, expanding the functional purpose and interaction of the main elements involved in the thermodynamic cycle of a gas turbine engine, in order to increase specific power and environmental friendliness while simultaneously performing a power plant, engine and gas generator of additional functions that expand the scope of their application.

 The technical result that provides a solution to the problem in part of one version of the method of converting energy in a power plant is to: increase the power on the power shaft by organizing the process of sequential connection of additional masses while reducing energy costs for compression and heating of atmospheric air, as well as reducing losses on the efficiency of devices carrying out these processes, losses of kinetic energy of jet exhaust and losses of heat dissipated with exhaust gases in at Mosfere; optimization of energy costs in various operating modes by changing the number and parameters of devices to create a combined reactive mass, thrust and torque on the shaft with a simultaneous additional reduction in speed and heat losses of jet exhaust in a specific mode; optimizing energy costs and maintaining environmental friendliness in transient modes of operation during power control by changing the frequency of combustion without changing the amount of fuel in the thermodynamic cycle and while increasing efficiency in a steady state; reducing energy loss by reducing Coriolis forces; reducing inertial mass and reducing the necessary heat resistance of turbine blades by lowering the temperature of the combined reactive mass; increasing the power of the power plant while overcoming peak loads due to the possibility of using additional autonomous energy sources; utilization and additional use of kinetic energy of the combined reactive mass remaining after creating the moment on the power shaft to perform useful work; using part of the potential energy of the combustion products obtained by burning fuel in a closed volume to compress air; simplifying and improving the reliability of the power plant by compressing the air in the jet compressor; improving the use of thermal energy from fuel combustion by heating pre-compressed atmospheric air during the cooling of the flow path with the subsequent performance of useful work during expansion; preventing the dissipation of thermal energy from fuel combustion through heat-conducting structural elements to the external environment by heating the working fluid of the second thermodynamic circuit through the heat-conducting walls of the main thermodynamic circuit; simplifying and improving the reliability of the power plant by reducing the speed difference between the inner and outer rings of the bearings of the power shaft, increasing their life and performance without the use of forced lubrication systems; improving the efficiency and specific power of the power plant, as well as obtaining additional advantages when it is designed to drive various types of vehicles using a biotic turbine with differential transmission to use the kinetic energy of the jet of a rotating nozzle, which remains after creating a moment on the power shaft of the jet adaptive engine ; reducing the air mass necessary to create a reactive mass due to the formation of a closed thermodynamic circuit and the use of exhaust gases as an additional mass to be connected; improving the quality of exhaust gas neutralization by increasing the contact time with the exhaust gas catalyst and using not rare earth and noble metals as catalysts in the neutralization process, but widespread inexpensive materials; reducing the noise effect during exhaust emissions to regulatory requirements without the use of additional external silencing systems.

 The invention in part of one variant of the method of energy conversion in a power plant is as follows. A method of converting energy in a power plant, in which the torque on the power shaft of the rotor of the jet engine is obtained due to jet propulsion generated by the reactive mass of combustion products flowing out of at least one jet device, and energy is used to compress atmospheric air to produce the reactive mass the compressor and its heating in the combustion chamber, and by increasing the temperature during the combustion process in a closed volume of the periodic combustion chamber in each thermodynamic cycle in several times, compared with the potential energy of the air-fuel mixture, increase the potential energy of the combustion products, which are then sent to the jet devices of a rotating nozzle apparatus of an ejector type located at least at one level on the outer part of the impeller of at least one rotor stage of the jet adaptive engine power plant, for converting the received potential energy into the kinetic energy of the pulse of a supersonic jet jet flowing out of the jet mouth properties in the device for joining the additional masses of this nozzle apparatus and creating, in each thermodynamic cycle, following the gas mass of the combustion products moving in this device at supersonic speed, the vacuum that is used to supply additional gas masses to the same device and carry out the process of sequentially connecting them to gaps between pulses, in which these additional masses are accelerated by transferring to them part of the energy of the pulses of the jet of combustion products and uchayut combined reactive mass, which creates the torque reaction arm and torque on the shaft, wherein the proportional increase in pressure in the combustion process and the amount of addition of extra weight factor m is reduced by the air compression energy costs in the compressor and heating it in the combustion chamber.

In special cases, the implementation of the method
To obtain the necessary moment on the rotor shaft of the jet-adaptive engine, the jet thrust force is controlled by changing the number and parameters of inkjet devices with connection devices, by connecting through separate channels to each device or groups of devices corresponding in their parameters to a given operating mode, periodic cameras combustion and sources of additional masses to change the magnitude and speed of the combined reactive mass.

 To obtain the required moment on the rotor shaft of the jet-adaptive engine, the reactive thrust force is controlled by changing the frequency of thermodynamic cycles in the periodic combustion chambers and, accordingly, the mass and thermodynamic characteristics of the combustion products supplied per unit time, the parameters of the coupling processes and the coupling coefficients of the additional masses m involved in the process of creating a combined reactive mass of devices to change the magnitude and speed of the combined reactive mass. Moreover, during the combustion process, the amount of fuel in the composition of the air-fuel mixture does not change, but in the steady state, the air compression ratio is increased, depleting the air-fuel mixture.

 The moment on the rotor shaft of the jet adaptive engine is obtained due to the expiration of the combined reactive mass from the rotating nozzle apparatus of at least one rotor stage and the simultaneous action of the combined reactive mass from the stationary nozzle apparatus on the blades of at least one blade stage of the same rotor.

 Simultaneously with the combined reactive mass obtained in the process of sequential addition of additional masses, to create a moment on the power shaft of the jet-adaptive engine, one also uses a reactive mass obtained in another way, for example, during stationary expiration of a working fluid from jet nozzles or obtained in the process of parallel addition of additional masses due to their ejection by a stationary flowing jet.

 The air is compressed in the compressor of the dynamic principle of operation due to the part of the available kinetic energy of the combined reactive mass remaining after creating a moment on the shaft of the jet adaptive engine. This energy is utilized by directing the jet to act on the blades of at least one turbine, the rotor of which is kinematically not connected to the power shaft and, converting into kinetic energy of its rotation, provide a compressor drive.

 The air is compressed in a volumetric principle compressor due to part of the increase in potential energy of the combustion products obtained in the process of fuel combustion in a closed volume of the periodic combustion chamber. Due to the partial expansion of the combustion products within the volume of the combustion chamber, its slide valve is moved and, acting on the compressor piston, compresses the spring, as well as the air in the volume in front of the piston, and creates a vacuum in the volume behind the moving piston for atmospheric air. At the end of this piston stroke, combustion products are discharged from the combustion chamber, and compressed air is released from the compressor to expand them in jet devices, then the spool valve and compressor piston are returned to their original position due to the energy accumulated by the spring. During the return stroke, the incoming air is compressed, which is used to form the air-fuel mixture of the next thermodynamic cycle.

 The air is compressed in a jet compressor, forming a mixture of additional air masses with combustion products from the combustion chamber, due to the kinetic energy of which these additional masses accelerate and combine in one stream. When the flow is inhibited, a compressed gas mixture is obtained for use in expansion in jet devices and as a component of an air-fuel mixture with a proportion of oxidizing agent and combustion products, which provides fuel combustion and a decrease in the amount of nitrogen oxides in the combustion products of the periodic combustion chambers of the main thermodynamic circuit, as well as the jet combustion chamber compressor.

 In each thermodynamic cycle, the combined reactive mass is obtained by using additional masses of energy from one pulse of the jet of products of combustion from the periodic combustion chamber and the energy of at least one pulse of pre-compressed atmospheric air or other gases, which are sent after a calculated time interval after combustion products to increase the temperature and potential energy of these gases before expansion and simultaneously with lowering the temperature of the flow path of the thermodynamic circuit.

 The energy from the combustion of fuel in the periodic combustion chambers of the main thermodynamic circuit is used, directing along an additional - second thermodynamic circuit, the channels of which are parallel to the channels of the main circuit, the working fluid from another source, for example, atmospheric air or compressed air, or other gases having a temperature close to the ambient temperature, for contact with the heat transfer surface of the walls of thermally stressed structural elements through which it is heated, simultaneously but cooling these walls, performing the functions of a heater of the working fluid at constant pressure.

 To supply the working fluid to the second thermodynamic circuit, the kinetic energy of the reactive mass flowing out from the jet devices of the jet adaptive engine and creating a vacuum at the inlet of the additional mass connecting devices is used, due to which the working fluid, for example atmospheric air, enters this connecting device to form the combined reactive mass, and while moving along the radial channels of the rotating rotor, it is compressed due to centrifugal force.

 Depending on the magnitude of the attachment coefficient during the sequential addition of additional masses, the temperature is reduced, as well as the flow rate of the combined reactive mass and the rotational speed of the rotor of the jet-adaptive engine at steady state to a design level at which they provide the necessary reduction in thermal stress of the flow path and the operability of the power shaft bearings without the use of a forced lubrication system.

 The bearings of the power shaft are fixed on the shaft of the blade turbine, which is used to utilize the kinetic energy of the combined reactive mass remaining after creating a moment on the shaft of the jet adaptive engine, and these shafts are aligned coaxially inside each other and rotate in one direction to reduce the estimated speed of rotation of the bearings on steady state by reducing the speed difference between their outer and inner rings.

 Part of the available kinetic energy of the combined reactive mass remaining after the thrust by the rotating nozzle apparatus of the previous stage of the rotor of the jet adaptive engine creates thrust, is disposed by unrolling the jet in the guide apparatus and directing it to the blades of the next blade stage to obtain additional torque on the shaft.

 Part of the available kinetic energy of the combined reactive mass remaining after creating the moment on the shaft of the jet adaptive engine is disposed of, while the jet acts on the rotor blades of the first stage of the biotational turbine, which is rotated in the opposite direction and kinematically coupled to the rotor shaft of the jet adaptive engine through the differential planetary gear with a gear ratio providing a calculated reduction in the peripheral speed of the blades of the first stage of the biotational turbine with respect to to the peripheral speed of the rotating nozzle apparatus of the jet adaptive engine, to increase the force of the jet on the blades of the biotational turbine and the moment on the rotor shaft of its first stage. This moment through the differential planetary gear is summed up with the moment created on the rotor shaft of the jet adaptive engine. In addition, at least one single-stage rotor of the second stage of the biotational turbine is located on the output shaft of this planetary gear carrier, rotating in the direction opposite to the rotation of the first stage. The moment formed by the action of the jet on its blades is also summarized by combining all three power flows into one through a differential planetary gear and providing the optimal ratio of the increase in the force of the jets on the blades of the steps of the biotic turbine with the efficiency of these stages depending on their rotation speed, while the total power is transmitted to the consumer through one or several output shafts at the same time.

 The total power generated on the output shaft of the carrier of the differential planetary gear is transmitted to the consumer through a gearbox with a gear ratio that provides an additional increase in torque on the output shaft and a decrease in its rotation speed at steady state to the calculated value.

 The total power generated on the output shaft of the differential planetary gear carrier is transmitted through the central gear of the input shaft of the additional differential planetary gear and its satellites to the rotor of the first stage of the additional biotational turbine, and through the carrier shaft to the rotor of the second stage of this turbine mounted on it. Due to the gear ratio, the rotor speeds are reduced and synchronized and the moment on their shafts is increased, and due to the remaining kinetic energy of the combined reactive mass flowing from the second stage blades of the previous biotative turbine and acting on the blades of both stages of the additional biotic turbine, they create an additional total moment for the shafts of her rotors. To transfer power to the consumer, one of the output shafts is used, for example, to drive propeller blades, a single-row rotor fan, or both at the same time - a double-row rotor fan. In this case, the kinetic energy of their rotation is converted into the kinetic energy of the jet stream, which creates the jet propulsion of the power plant as a propulsion device.

 When the combined reactive mass expires from the last stage of the biotational turbine, for example, centrifugal, it is guided through the channels located inside the fan blades or fan rotor, mounted on the output shaft of the additional differential gear carrier, to form reactive thrust when it flows out of their peripheral part, and additional rotational moment.

 The combined reactive mass, the kinetic energy of which was used to perform useful work, is used in the following thermodynamic cycles as additional masses. To do this, the exhaust channel of the power plant is connected to the input of the connection devices, forming a closed thermodynamic circuit in which under the action of rarefaction obtained due to the kinetic energy of the jets flowing from the jet devices into the accession chambers of additional masses, the gases exhausted in previous cycles moving along the exhaust channel into the external environment, they enter the connection devices and form a reactive mass combined with the products of combustion of this cycle. With an increase in the total mass of exhaust gases in a closed thermodynamic circuit due to the products of combustion, the excess is displaced through the exhaust channel through the exhaust channel, the mass of which from the total combined reactive mass of the thermodynamic cycle, which creates a moment on the power shaft, is 1 / m, where m - the value of the coefficient of accession of additional masses.

 Due to the kinetic energy of the jet stream, which creates a vacuum at the entrance to the device for attaching additional masses, they form a cyclically repeating circular motion of the exhaust gases in a closed thermodynamic circuit, in which they are mechanically cleaned with a filter and / or neutralized by a catalytic converter to reduce the emission of toxic substances, at the same time, by repeating the cycles of passage of exhaust gases through them, they improve the quality of cleaning and / or increase the efficiency of neutralization and exhaust.

 When using devices for connecting additional masses, blade stages of the rotor of the jet-adaptive engine and / or blade turbines that perform useful work due to the kinetic energy of the reactive mass flowing from the jet devices, as well as using a closed thermodynamic circuit, the speed of supersonic pulses of jet jets of products is gradually reduced combustion to a design level that provides a reduction in sound effect when exhaust gases are released into the atmosphere to regulatory requirements s without the use of additional external systems jamming.

 The power on the output shaft of the power plant is provided through the combined use of a jet adaptive engine and at least one engine of a different operating principle, for example an electric motor, and they are included in the operation together or independently.

 The power on the output shaft of the power plant is provided, using compressed air, which is sent from the pneumatic accumulator through a mechanical or pneumatic device, which supplies it to the critical section, to obtain the active jet flowing out during the sequential connection of the nozzle apparatus from the jet devices jet nozzles in a pulsed mode.

 The power of the jet-adaptive engine of the power plant is regulated by changing the frequency of the pulses of the jet, which is active during the sequential addition of additional masses by changing the frequency of the combustion cycles in the periodic combustion chambers and / or by changing the frequency of the pulsed supply of compressed air.

 The technical result, which provides a solution to the problem in terms of another variant of the method of converting energy in a power plant, is to: increase the efficiency of use of the kinetic energy of the jet stream remaining after the moment is formed on the power shaft of the power plant, by utilizing, converting, accumulating and consuming it to the necessary moment to do useful work; reducing fuel consumption, improving environmental performance and increasing the power of the power plant at peak times due to the use of utilized and stored energy; using the specific power of the kinetic energy accumulator during the initial accumulation of energy by an inertial mass to ensure continuous operation of the power plant without burning fuel and exhaust gases; reducing energy costs in a discrete process of compressing atmospheric air in a centrifugal compressor and consuming compressed air in a predetermined mode while simultaneously performing the compressor rotor of an additional storage and energy source function for compressing; increasing the speed of rotation of the centrifugal compressor without replacing the bearings of the shaft of its rotor with faster ones and without using forced lubrication systems while reducing the speed of the turbine driving it into rotation and increasing the force of the jet impact on its blades; increasing efficiency and environmental friendliness, especially in urban driving conditions, by creating conditions for accelerating the vehicle at the beginning of its movement without energy consumption to maintain the speed of the power shaft at idle while reducing the time required to accelerate; reducing fuel consumption due to the recovery of energy spent during acceleration of the vehicle, its accumulation of inertial mass, conversion and use at the right time; reducing the oxidizer consumption for burning fuel during operation of the power plant under water by compressing the gases exhausted in previous cycles and using them as an additionally connected mass in the next cycle instead of atmospheric air when creating a combined reactive mass in the process of sequential connection at elevated pressure in thermodynamic circuit; increasing the amount of useful work performed due to the potential energy of the exhaust gases after bleeding them under pressure from a closed thermodynamic circuit with subsequent expansion, performing useful work and discharge into the environment with less pressure; increase the resource of work under water due to the use of energy accumulated by the inertial mass for conversion into electrical energy and production by hydrolysis of hydrogen and oxygen for thermodynamic cycles; reducing exhaust toxicity by increasing the rate of chemical reactions in the process of neutralizing exhaust gases at elevated pressure and increased contact time of the reactants with the catalyst; improving environmental friendliness, energy efficiency and expanding the scope of application of the power plant due to the simultaneous development of "cold" and power on the power shaft without the emission of exhaust gases into the environment; increasing the moment on the power shaft while cooling the connected masses of atmospheric air for the use of "cold" by consumers and utilization of the remaining kinetic energy of the combined reactive mass; cooling atmospheric air to low temperatures at which the moisture contained in it is frozen in the form of ice crystals and trapped for further use of water after thawing.

 The essence of the invention in terms of another variant of the method of converting energy in a power plant is as follows: a method of converting energy in a power plant, in which a torque is generated on the power shaft of the machine-engine by using the kinetic energy of the reactive mass flowing out of the jet device, and part of the disposable the energy remaining after creating the moment on the power shaft is disposed of, and the outflow of the reactive mass is directed to the blades of the rotor of the blade turbine, which is kinematically is not connected with the power shaft, and is continuously converted into kinetic energy of rotation of devices kinematically connected to this turbine and having an inertial mass, with the help of which it accumulates and, if necessary, is converted into electrical energy and / or potential energy of compressed gas using the energy received during conversion and / or its accumulation with subsequent use, while using sensors control the permissible design limit of the speed of rotation of the inertial mass, in excess of They increase the expenditure of stored energy.

In special cases, the implementation of the method
The utilized energy accumulated by the inertial mass is used to increase the power on the power shaft in excess of the power obtained due to the energy of the reactive mass with combustion products.

 The utilized energy accumulated by the inertial mass is used when generating power on the power shaft and / or providing energy to external consumers to partially or completely replace the energy received from burning fuel, in which, due to control of a discrete combustion process, fuel combustion and emission are simultaneously reduced or completely stopped. combustion into the atmosphere.

 When starting the power plant, the initial accumulation of kinetic energy by devices with inertial mass is carried out by rotating them using an electric motor due to external sources of electricity.

 When starting the power plant, the initial accumulation of kinetic energy by devices having an inertial mass is carried out by rotating them due to the kinetic energy of the reactive mass from the nozzle apparatus, which is sent to the blades of the turbine rotor, kinematically not connected with the power shaft, and converted into kinetic energy of rotation of the inertial mass kinematically connected to rotor devices.

 A compressor rotor is used, the mass of which is selected from the condition that it simultaneously performs the functions of a device having an inertial mass that accumulates kinetic energy and its discrete controlled conversion to potential energy, compressed in the same gas compressor. At the same time, compressed gases are pumped through the non-return valve into the pneumatic accumulator to the upper calculated pressure level, above which one pneumatic valve blocks the access of gases to the compressor, and through the other, the remaining compressed gas is released in the volume between the inlet of the pneumatic accumulator and the outlet of the compressor, whose rotor after This rotates idle, without spending the energy of the inertial mass on compression, until the pressure drops to the calculated level at which the gas supply to the compressor inlet is resumed.

 The rotor speed of the compressor is increased relative to the speed of the blade turbine rotating it due to the kinematic connection between them through a planetary gear, reducing the peripheral speed of the turbine blades relative to the speed of the reactive mass flowing from the previous stage of the rotor of the jet-adaptive engine after the moment on its shaft is generated, and increase the force of its impact on these blades. The compressor shaft and the blade turbine shaft are located one inside the other and rotate through the planetary gear in one direction. In this case, the difference in the rotational speeds of the outer and inner rings of the compressor shaft bearings is reduced by the value of the rotational speed of the shaft of the blade turbine on which these bearings are mounted.

 An electric generator is used, the mass of which is selected from the condition that it performs the functions of a device having an inertial mass for accumulating kinetic energy, which is converted into electrical energy in the same electric generator by connecting a load to it.

 At the beginning of the vehicle’s movement, the moment required to bring the power shaft of the rotor of the jet-adaptive engine of its power plant from a stationary state into rotation is created using the discreteness of the processes of fuel combustion and the supply of the working fluid to the jet devices to connect to them at any given time the estimated number of chambers of periodic combustion and other autonomous energy sources, including those formed due to the energy accumulated by the inertial mass, and supplying the necessary the number of working fluid with calculated thermodynamic characteristics for the formation of the total reactive mass, providing a given value of the moment on the power shaft, while due to the low inertia and the inverse dependence of the moment on the shaft on the rotational speed of the rotor of the jet adaptive engine reduce the time required to accelerate the vehicle after the start of movement.

 For a given reduction in speed or movement under the influence of external forces, the kinetic energy accumulated by the mass of the vehicle is converted through its mover into the kinetic energy of rotation of the rotor of the traction electric motor included in the generator mode and / or of the compressor rotor, in which gases are compressed and directed through the nozzle device on the turbine blades for conversion into kinetic energy of the inertial mass and its accumulation, and / or compress in the radial channels of the rotor of the jet adaptive engine, and when it expires NII from its rotating nozzle apparatus act on the blades of a blade turbine to convert and store energy.

 The operation of the power plant in an environment with a pressure exceeding atmospheric is ensured by the energy accumulated by the inertial mass, which is used to drive a compressor that creates a vacuum in the exhaust gas region, while simultaneously compressing the exhaust gas in the exhaust channel, which is connected to the inlet of the connection device additional masses of the jet adaptive engine and form a closed thermodynamic circuit in which the exhaust gases from previous cycles are used as additional x mass committing cyclically repeating the process of successive addition, under elevated pressure at the inlet to the adding device, to the reaction mass of combustion products in this series, the effluent from the ink jet devices and the combined expiration of the reaction mass to a reduced pressure. To exhaust excess exhaust gases, the exhaust channel is connected to the external environment through a non-return valve and some of the compressed gases are vented through it if the pressure in the channel exceeds the pressure of the external medium.

 When working underwater, the exhaust gases compressed in the exhaust channel of a closed thermodynamic circuit, at the expense of part of the kinetic energy accumulated by the inertial mass, are at least partially vented through the non-return valve into the pneumatic accumulator and accumulated in it to the design pressure, and when pressure is reduced, it is used as a working fluid for performing useful work during their expansion with subsequent release into the external environment.

 When working underwater, part of the energy of the inertial mass is converted into electricity to create a moment on the power shaft using an electric motor, it is accumulated in storage devices and / or hydrolyzed to partially replace organic fuel and compressed air with hydrogen and oxygen and to use part of the oxygen in life support systems.

 In a closed thermodynamic circuit, due to part of the kinetic energy accumulated by the inertial mass, cyclically repeating circular motion of the exhaust gases is formed and, at an increased pressure in the exhaust channel, they are mechanically cleaned with a filter and / or neutralized by a catalytic converter to reduce the emission of toxic substances. By repeating the cycles of passage of the exhaust gases through them, they improve the quality of their purification and / or increase the contact time of the reactants with the catalyst, which, along with increased pressure, increase the efficiency of neutralization.

 Atmospheric air is compressed in the compressor due to the energy accumulated by the inertial mass, then it is accumulated in a pneumatic accumulator, from which it is directed directly or through a heat exchange device to the jet nozzles of the jet adaptive engine at the right time, and, expanding in the nozzles, they lower its temperature and direct for cooling the elements of the power plant and / or external objects, and then at least partially returned to the compressor for re-compression and the compressed air is again sent to the pneumatic accumulator, sample Zuy closed refrigeration circuit, which, along with the development of "cold", is used to provide power to the power shaft without emission of exhaust gases into the outer environment.

 Compressed and low-temperature air from a closed refrigeration circuit is used, for example, to form a fuel-air mixture or provide external consumers. The consumed mass of air is replenished from the atmosphere, creating due to the kinetic energy of the jet formed during the expansion of compressed air from the pneumatic accumulator in the jet nozzles, rarefaction at the inlet of the devices for connecting additional masses for the inflow of atmospheric air, which is used as an additional mass to be connected in the process of joining. This creates a combined reactive mass that increases the moment on the power shaft, utilize part of its kinetic energy remaining after creating the moment, and then direct consumers to use part of the “cold” and / or to the input of additional mass connecting devices for the next stage of the jet adaptive engine rotor and / or compressor input.

 The air supplied to the input of the devices for connecting additional masses from the atmosphere, when periodically replenishing the amount consumed by external consumers from the refrigeration circuit, is cooled to the temperature during the connection, at which, during the expiration of the jets, the moisture contained in it is crystallized, and the crystals are trapped and concentrated in the volume located before entering the compressor. After the outflow of low temperature air ceases, ice crystals under the action of heat transferred through the heat-conducting structural elements of the thermodynamic circuit and / or under the influence of specially heated elements melt, and the resulting water is collected in containers.

 The technical result, which provides a solution to the problem in terms of the method of converting energy in an adaptive jet engine, consists in: increasing the combined reactive mass, compared with the initial mass of the active jet and the moment on the power shaft, without additional fuel energy consumption, as well as adapting the engine to multi-mode application conditions to achieve optimal efficiency by controlling the total reactive mass and the process parameters of adding additional masses upon receipt of the combined reactive mass with calculated thermodynamic characteristics; reducing inertial mass and reducing the necessary heat resistance of turbine blades by lowering the temperature of the combined reactive mass; increasing the moment on the power shaft due to the simultaneous use of fixed and rotating nozzle devices, as well as a multi-stage rotor; increasing adaptability through the use of inkjet devices for the formation of a jet stream that performs the function of the active in the process of joining additional masses with various parameters; in increasing the efficiency when used as an inkjet device in the process of sequential connection of additional masses of the detonation combustion chamber; increasing the moment on the power shaft due to the organization of the process of parallel connection of additional masses in the connection device; increasing the moment on the power shaft due to the organization of the process of sequential connection of additional masses in the connection device; increasing the moment on the power shaft due to the organization of the process of sequential connection of additional masses in the connection device, the input of which is connected directly to the radial channel for supplying the attached working fluid; increasing the moment on the power shaft due to the organization of the process of sequential addition of additional masses in the attachment device and at the same time reducing in this process the energy of the main working fluid and losses due to the use of pulses generated by the second working fluid with lower potential energy for preliminary acceleration of the attached masses; increasing the moment on the power shaft due to the organization of the process of sequential addition of additional masses in the attachment device and at the same time reducing in this process the energy of the main working fluid and losses due to the use of the second working fluid with lower potential energy, forming a stationary expiring jet stream, for preliminary acceleration of the attached masses; increasing the moment on the power shaft due to the organization of the process of joining additional masses when using two connection devices at the same time; automatic optimization of the costs of the main working fluid by changing the critical cross section of the jet nozzles depending on the magnitude of the centrifugal force in various operating modes; the increase in specific power when using the air blades of the propulsion device of the vehicle as a rotor and the kinetic energy of the jet stream remaining after creating the torque to create traction additional to the thrust of the propulsion device; expanding the scope due to the simultaneous creation of power on the shaft, performing the functions of an expander and an air cooler, as well as a pump, a jet generator and a centrifugal compressor.

 The essence of the method of converting energy in an adaptive jet engine is as follows: in a method in which the kinetic energy of a reactive mass flowing out of a jet device is used to generate torque on the rotor shaft of a jet engine, and several different ones are used to produce reactive mass in a jet engine according to its thermodynamic characteristics of the working fluid. Due to the main working fluid with greater potential energy, a jet stream is formed in the jet device, which is sent to the additional mass attachment device and used as an active jet in the process of adding additional masses, and the other working fluid with lower potential energy than the main one is directed to the input of the same device for attachment as additional masses and due to the partial transfer of the kinetic energy of the active jet, accelerate it during the connection Combining the two working bodies in one stream to create a combined reactive mass. Moreover, the magnitude and speed of the combined reactive mass is controlled by changing the number and parameters of the inkjet devices and attachment devices involved in the process of its creation, by connecting sources of the working fluid through separate channels and changing the thermodynamic characteristics of the working fluids supplied to each involved device or to groups of devices , with the calculated parameters for this operating mode, as well as changing the parameters of the processes of joining additional masses, adjusting the jet adaptive engine to achieve optimal efficiency when generating total torque in various operating modes, thereby adapting it to the conditions of multi-mode application.

In special cases, the implementation of the method
Obtained in the process of joining additional masses, the combined reactive mass flowing out of at least one device for joining the additional masses of the fixed nozzle apparatus is sent to the blades of at least one blade stage of the rotor of the jet adaptive engine.

 The expiration of the combined reactive mass obtained during the joining of additional masses is carried out from the additional mass connecting devices of the nozzle apparatus located at least at one level of the outer part of the impeller of at least one rotor stage of the jet adaptive engine to create reactive thrust and torque on the shaft. In this case, the main working fluid is fed into the jet devices of the rotating nozzle apparatus to create a jet stream that performs the function of the active mass during the addition of additional masses via the radial channels of the stage.

 The moment on the shaft of the jet adaptive engine is obtained due to the simultaneous action of the combined reactive mass from the nozzle apparatus on the blades of at least one blade stage and the expiration of the combined reactive mass from the rotating nozzle apparatus of at least one stage of the same rotor of the jet adaptive engine.

 An additional moment on the shaft of the jet-adaptive engine with a multi-stage rotor is formed by directing the jet flowing from the blades or the rotating nozzle apparatus of the previous stage through the guide apparatus to the blades of the next rotor blade stage or to the input of the devices for connecting additional masses of the stage with the rotating nozzle apparatus as additional mass

 To increase the moment on the shaft, the jet stream flowing out of the previous stage is directed through the guide apparatus to the blades of the next rotor stage, and after the expiration from the blades, it is directed to the input of additional massing devices of the rotating nozzle apparatus fixed to the same rotor stage after the blades in the direction the expiration of the jet, as additional masses.

 For the formation of jet jets used in the processes of joining additional masses as active, jet devices of various operating principles are used, for example, electro-jet, jet nozzles, detonation combustion chambers, moreover, a jet stream from these devices is sent directly to the device for joining additional masses or through a radial channel.

 Jet jets used as active jets are formed in detonation combustion chambers, in which the combustion products are directed to form jet jets flowing towards each other at the focal point of the spherical part of the detonation combustion chamber, and compressed air-fuel mixture is fed through parallel channels the jet of which is directed to the same point for the collision of jets, causing a local increase in temperature and pressure and initiating a self-oscillating detonation process Nogo combustion to form a high detonation wave propagating in the opposite direction from the combustion chamber of the detonation of the spherical portion, and with high kinetic energy overclocking the combustion products, and the process continues until the termination of supply of the combustion products or fuel mixture, and begins again when resuming supply.

 The main working fluid, which generates a stationary flowing jet through a jet device, is sent to an additional mass connecting device, the input of which communicates with the atmosphere or with another source of additional masses, which in the process of parallel connection are ejected by this jet stream, transferring some of the energy to them due to turbulization and mixing flows in the device connecting additional masses.

 The potential energy of the main working fluid in the jet device is converted into the kinetic energy of the pulses of the jet stream, the expiration of which is sent to the device for attaching additional masses and create a vacuum in it, which is stored for the period of time necessary for the successive influx of the estimated number of additional masses behind each pulse of the jet stream. which in the process of sequential connection accelerate and form a united reactive mass.

 The potential energy of the main working fluid in the jet device is converted into the kinetic energy of the pulses of the jet stream, which is sent to the device for attaching additional masses, and atmospheric air or another working fluid is supplied as additional masses through a channel connected directly to the input of the same device and, increasing in the process of sequential addition of their kinetic energy due to the energy of the main working fluid, form a united reactive mass.

 To obtain pulses of a jet stream, which acts as an active jet in the process of sequential addition of additional masses, at least two working fluids with different thermodynamic characteristics are used, and pulses formed by a working fluid with lower potential energy are used to preliminarily accelerate additional masses with the goal of reducing losses by reducing the difference in meeting speeds during their subsequent interaction with the mass of the main working fluid with kinetic energy, as well as the relative reduction in the cost of its energy and increase the speed of the combined reactive mass.

 The potential energy of the main working fluid in the jet device is converted into the kinetic energy of the pulses of the jet, which performs the function of the active jet in the process of sequential addition of additional masses. Another working fluid with constant pressure and lower potential energy is sent to the same device through an annular jet nozzle to form a stationary flowing jet, the energy of which is used in the process of connecting additional masses entering the input of the same device between the pulses of the active jet to create constant rarefaction at the entrance to the device of connection and preliminary acceleration of additional masses in order to reduce energy losses during their subsequent interaction action with the mass of the main working fluid by reducing the speed difference.

 The process of adding additional masses is carried out sequentially, using two connection devices at a time, one after the other, while the jet stream flowing out after the process of adding additional masses from the first device performs the function of an ejection jet in the process of adding additional masses in the second device, at the same time an increase in moment due to an increase in the combined reactive mass reduces the rate of its expiration and the angular velocity of the jet adaptive motor of Tell to the calculated level.

 Under conditions of multi-mode application, when changing the rotor speed, automatically, due to a change in centrifugal force, the critical section area of the jet nozzles of the rotating nozzle apparatus is changed, adjusting the jet-adaptive engine to the flow rate of the main working fluid, in accordance with the required moment in a given mode, for example, when accelerating the vehicle during the start of movement requires the greatest power on the shaft, so the nozzle cross-sectional area is maximum, but it is reduced by moving p regulates nozzle member by the centrifugal force increases as the rotor speed set to a minimum cross-sectional area at steady state.

 After creating a moment on the shaft, the rest of the available kinetic energy of the reactive mass is used, controlling the direction of its expiration, to form traction applied to the attachment point of the jet adaptive engine.

 As the rotor of the jet-adaptive engine, a vehicle propulsion device is used, for example, propeller blades or fans, or fan fans, or part of their blades, and the estimated speed of rotation of the blades is provided by changing the parameters of the connection process and the estimated amount of the total combined reactive mass and its speed the outflow, while the kinetic energy remaining after creating the moment on the shaft is used to control the direction of the outflow of this reactive mass to create additional reactive thrust to the thrust created by the propulsion device of the vehicle.

A compressed working fluid with a temperature close to ambient temperature is expanded in the jet nozzles and cooled, depending on the degree of compression, to negative temperatures below -130 ^o C, while using a jet adaptive engine to create a moment on the shaft and perform the functions of an expander, and then in the process of attaching additional masses in the accession device, it is used to perform the functions of an air refrigerating machine with refrigerant - the main working fluid, cooling the additionally attached masses, moreover, they lower their temperature to the calculated one, with the possibility of its regulation within the limits depending on changes in the quantity, range of thermodynamic characteristics of the main working fluid and the coefficient of addition of additional masses m.

 When creating a moment on the shaft, the jet adaptive engine is simultaneously set to operate in pump mode to pump external gas masses due to the kinetic energy of the reactive mass flowing out from the jet devices and creating a vacuum at the inputs of the additional mass connecting devices, and when the power shaft is forced to rotate, centrifugal compressor and jet generator mode for compressing external gases in the radial channels of the rotor and converting their potential energy in jet nozzles into kinetic jet energy.

 The technical result, which provides the solution of the problem in terms of the method of energy conversion in a gas generator, consists in: providing in all thermodynamic cycles the calculated duration and amplitude of the pulses during the release of combustion products to increase the efficiency of the process of sequential addition of additional masses in the jet-adaptive engine of the power plant; the implementation of the fuel injection process without any synchronization with control systems and obtaining pressure for injection, providing high-quality atomization of fuel; while the gas generator performs the functions of a reciprocating compressor, the compressed air from which, along with the combustion products, is used to perform useful work in the power plant, as well as when blowing and forming the air-fuel mixture in the periodic combustion chamber to ensure autonomous operation of the gas generator; simultaneous performance by a gas generator of the functions of a jet propulsion device; at the same time, the gas generator performs the functions of a jet compressor, the gas mixture of which is used to perform useful work in the power plant, as well as when blowing and forming the air-fuel mixture in the periodic combustion chamber to ensure autonomous operation of the gas generator.

 The essence of the method of converting energy in a gas generator is that: in a method of converting energy in a gas generator to generate a working fluid, during which the pressure and the available work of expanding the combustion products are increased due to part of the process of fuel combustion in a closed volume of the periodic combustion chamber in each thermodynamic cycle the resulting increase in the potential energy of the combustion products during their partial expansion in the closed volume of the periodic combustion chamber, the work of moving y of the spool valve from its initial position, in which the spring acting on it is almost completely unclenched and the exhaust channel is closed, along its axis by the calculated distance, during which it compresses the spring, accumulating energy to ensure the spool valve returns to its original position - reverse, and open bore sections for the release of combustion products, after which, under the action of a compressed spring, the valve is stopped and the return stroke begins, during which fuel is sprayed under pressure and give compressed air, ensuring the mixing of the components of the air-fuel mixture for the next thermodynamic cycle, which begins after the spool valve returns to its original position and the air-fuel mixture ignites, while the necessary thermodynamic characteristics and the amount of combustion products generated per unit time are obtained depending on the purpose and modes of use gas generator due to: the set frequency of ignition of the air-fuel mixture, changes in the pressure of compressed air for its formation, changes in the volume of the periodic combustion chamber during the controlled filling of part of its internal volume with an incombustible mass, and, regardless of which (s) of these methods are used to change the parameters of the combustion products, a constant amount of fuel is provided in all thermodynamic cycles, and also the estimated duration and amplitude of the pulses upon their release, the values of which in this method of energy conversion do not depend on changes in the frequency of thermodynamic klov, which increases the efficiency of the process of sequential addition of additional masses, including in a jet adaptive engine, when using this method for the formation of an active jet.

In special cases, the implementation of the method
Due to the energy of the combustion products, during their partial expansion, the slide valve is moved and a vacuum is created in the volume associated with its direct passage through the closed check valve with the passage section for fuel injection, as well as with the open channel for supplying fuel from the fuel tank, from which this volume under the influence of the resulting vacuum flows in the estimated amount of fuel, which at the beginning of the movement of the spool valve during its return stroke is isolated, blocking the channel for its supply, and then due to An energy accumulated by a spring creates pressure in this volume, opens a check valve under the action of pressure and displaces the calculated amount of fuel through the passage section for its injection.

 During the release of combustion products from the periodic combustion chamber with a decrease in their pressure to the level of air pressure intended for purging, they begin to supply it to the chamber and continue it during movement and stop of the spool valve after the end of the forward stroke, before the start of the reverse, and end during reverse, at the beginning of the movement of the spool valve after closing the exhaust channel.

 The periodic combustion chamber is purged with air, which is compressed by the compressor piston, which is driven by the energy of the combustion products during movement of the slide valve during the forward stroke, and the air is compressed and supplied to this chamber to form the air-fuel mixture of the next thermodynamic cycle during the return stroke the same piston due to the energy accumulated by the spring.

 At the end of the direct stroke of the spool valve, the combustion products discharged from the periodic combustion chamber are sent to the jet device to generate pulses of the jet stream, while the gas generator simultaneously functions as a heat engine — a pulsating jet gas generator and a jet propulsion device.

 The combustion products of the re-enriched air-fuel mixture at the end of the direct stroke of the slide valve through the exhaust channel are directed to the detonation combustion chamber to form supersonic jet jets, which are angled towards each other to the focal point of the spherical part of the detonation combustion chamber. The air compressed by the compressor piston when moving the slide valve due to the energy of the combustion products, or compressed air from external sources, is supplied to the same point for the collision of the jets, causing a local increase in temperature and pressure and initiating a self-oscillating process of detonation combustion with the formation of high-frequency detonation waves propagating in the opposite side from the spherical part of the chamber, and with high kinetic energy dispersing combustion products. This process continues until the supply of combustion products or air ceases at the end of the forward stroke of each thermodynamic cycle and resumes with a given frequency of ignition of the air-fuel mixture in the periodic combustion chamber. In this case, the gas generator simultaneously performs the functions of a heat engine - a pulsating jet gas generator and a jet propulsion device.

 The pulses of the jet of products of combustion from the jet device of the chamber of the periodic combustion of the gas generator are sent to the device for connecting additional masses of the gas generator, in which during the sequential connection due to their kinetic energy they accelerate the mass of atmospheric air, combining it in the flow between pulses in the calculated proportion with the products of combustion. Prior to the start of the flow deceleration in the diffuser of the additional mass connecting device, due to the calculated parameters of the connecting process, the combined mass decreases below the speed of sound and the composition of the gas mixture allows it to be used as a component of the air-fuel mixture, which reduces the amount of nitrogen oxides in the combustion products. At the outlet of the diffuser, a compressed working fluid is obtained and sent through a non-return valve to the pneumatic accumulator to accumulate to the design level, above which the ignition of the air-fuel mixture in the periodic combustion chamber of the gas generator is stopped, and when the pressure drops below the design level, it is again ignited and the process continues.

 The working fluid from the pneumatic accumulator is guided through the channels through the pneumatic valves for use in the second thermodynamic circuit of the power plant and / or as a component of the air-fuel mixture of the periodic combustion chamber of the first thermodynamic circuit of the power plant and / or the periodic combustion chamber of the gas generator and / or for external consumption.

 In FIG. 1 shows a structural diagram of a variant of a power plant based on a jet adaptive engine for implementing the method of energy conversion; figure 2, 3 - diagram of the valves of the combustion chambers of the installation depicted in figure 1; figure 4, section aa in figure 1; figure 5 is a section bB in figure 1; in FIG. 6 - node D in figure 1; in FIG. 7 is a structural diagram of a power plant based on a jet adaptive engine for implementing a method of energy conversion; in Fig.8 - node a in Fig.7; Fig.9 is a section bB in Fig.7; in FIG. 10 is a schematic diagram of a lattice element of an ejector type nozzle apparatus; in FIG. 11-13 - forms of jet nozzles; on Fig - electroreactive inkjet device; on Fig - inkjet device with a radial channel for the periodic supply of combustion products; in Fig.16 - detonation combustion chamber; on Fig.17-22 - input form of the accession device, on Fig. 23-28 are forms of an attachment device; on Fig is a schematic diagram of a piston gas generator for implementing the method of energy conversion; in FIG. 30.31 - extreme positions of the fuel valve; on Fig - schematic diagram of a jet gas generator with a jet compressor.

In the drawings, the following notation
Snail 1 centrifugal flywheel compressor; pneumatic valve 2 for the release of residual compressed air from the cochlea; pneumatic accumulator check valve 3; filter and catalytic converter 4; the intermediate shaft 5 of the rotor of the blade turbine-compressor-flywheel; a rotating nozzle apparatus 6 of the refrigeration circuit of the second stage of the rotor of the jet adaptive engine; air accumulator 7; blades 8 of the thermodynamic circuit of the second stage of the rotor of the jet adaptive engine; pneumatic valve 9 for supplying compressed air from the pneumatic accumulator; pneumatic valve 10 plug inlet pipe; inlet pipe 11 of atmospheric air with an air filter and a plug; a jet device 12 of a rotating nozzle apparatus of a thermodynamic circuit of the first stage of the jet adaptive engine; a rotating nozzle apparatus 13 of the refrigeration circuit of the first stage of the rotor of the jet adaptive engine; rotating nozzle apparatus 14 of the thermodynamic contour of the rotor of the jet adaptive engine; rotor 75 of the jet adaptive engine; a pneumatic valve 16 for supplying air to the rotating nozzle apparatuses of the first stage of the rotor of the jet adaptive engine; check valve 77 for air supply; a chamber 18 for periodic combustion; spool valve spring 19; spool valve 20; a check valve 21 for supplying an oxidizing agent to the periodic combustion chamber; check valve 22 for venting exhaust gases; exhaust pipe 23; pneumatic valve 24; exhaust pipe cap; the first stage 25 of the rotor of the jet adaptive engine; the shaft 26 of the first stage of the rotor of the blade turbine-compressor-flywheel; the bearing 27 of the rotor shaft of the blade turbine-compressor-flywheel; the first stage 28 of the rotor of the blade turbine-compressor-flywheel; turbine blades 29 of the refrigeration circuit of the first stage of the rotor of a blade turbine-compressor-flywheel; compressor blades 30 of the second stage of the rotor of the blade turbine-compressor-flywheel; turbine blades 31 of the thermodynamic circuit of the first stage of the rotor of a blade turbine-compressor-flywheel; blades 32 of the guide vanes of a compressor of a blade turbine-compressor-flywheel; blades 33 of the second stage of the refrigeration circuit of the rotor of the jet adaptive engine; compressor blades 34 of the first stage of the rotor of a blade turbine — a flywheel compressor; pneumatic valve 35 for supplying cold air to external consumers; turbine blades 36 of the thermodynamic circuit of the second stage of the rotor of the blade turbine-compressor-flywheel; the second stage 37 of the rotor of the jet adaptive engine; turbine blades 38 of the second stage of the refrigeration circuit of the rotor of the blade turbine-compressor-flywheel; the second stage 39 of the rotor of the blade turbine-compressor-flywheel; bearings 40 of the rotor shaft of a centrifugal flywheel compressor; traction motor 41; gears 42; power shaft 43 of the jet adaptive engine; gear 44 of the rotor shaft of a blade turbine-compressor-flywheel; shaft 45 of the second stage of the rotor of the blade turbine-compressor-flywheel; rotor shaft 46 of a centrifugal flywheel compressor; electric generator rotor 47; the stator winding 48 of the generator; planetary gear 49, gear 50 of the generator shaft; rotor 51 of a centrifugal flywheel compressor.

 Blades 52 of the second stage of the birotational blade turbine; vanes 53 of the first stage of the birotational blade turbine; rotor 54 of the first stage of the biotic rotary blade turbine; the internal volume 55 of the first stage of the bi-rotational blade turbine with the differential planetary gear located therein; satellite 56 differential planetary gear; drove 57 differential planetary gears; differential gear planetary gear 58; rotor 59 of the second stage of the birotational blade turbine; planetary center gear 60; drove 61 planetary gears; satellite 62 planetary gear.

 Jet nozzles 63, a jet device 64 with a radial channel for the periodic supply of combustion products; electroreactive 65 inkjet devices; detonation chambers 66 of combustion; spherical part 67 of the detonation combustion chamber; focal point 68 of the spherical part of the detonation combustion chamber; jet nozzles 69 for the expiration of combustion products to the focal point; an input 70 of an attachment device for external masses; an input 71 of an attachment device for supplying external masses through a channel; an annular channel 72 for supplying a working fluid; annular jet nozzle 73 of the annular channel; an additional mass attachment device 74; diffuser 75 of the attachment device; attachment device 76 without diffuser; an attachment device 77 without an oblique slice diffuser; an attachment device 78 with an oblique slice diffuser; an attachment device 79 with a confuser and a diffuser and with an oblique cut; an attachment device 80 with a confuser and a diffuser; two-stage attachment device 81.

 Cross section 82 for injection of fuel under pressure; compressor piston 83; reciprocating compressor 84; an electromagnet 85; check valve 86; check valve 87; end area 88 of the spool valve; piston fuel valve 89; check valve 90; jet gas generator 91.

 In the proposed variant of the method (structural diagrams explaining the implementation of the method are shown in FIGS. 1-32 in the process of fuel combustion in the closed volume of one or more chambers 18 of periodic combustion (FIG. 1,7), several times in each thermodynamic cycle, depending on the degree of precompression and the composition of the air-fuel mixture, increase the potential energy and the available work of expanding the combustion products.Then through the passage sections C of the spool valve 20 (Fig. 2,7) through the channels b1, B2 (Fig. 2,3,7) and B3 (Fig. 4.7) about combustion ducts are sent to jet devices 12 (Figs. 1, 4, 7, 9, 10) of a rotating nozzle apparatus 14 (Figs. 1, 7, 10) of an ejector type located on the outer part of the impeller of the rotor stage 25 (Fig. 1) 15 jet-adaptive engine (Fig. 1,7). In the inkjet devices 12, the resulting increase in potential energy is converted into additional kinetic energy of the pulse of a supersonic jet of combustion products. This jet through the input 71-73 (Fig.17-22) expires in the device 76-80 joining additional masses (Fig.23-27) nozzle apparatus 14 ejection polar type with supersonic velocity and movement creates a vacuum behind required for supplying to the input 71-73 of the additional gas mass and implementation of a serial connection, wherein the mass is accelerated by transmission of a part of the combustion products jet pulse energy. As a result, at the exit from the device 76-80, a combined reactive mass is obtained that increases the reactive thrust of the rotating nozzle apparatus 14 and the torque on the power shaft 43 (Fig. 1.7). In the proposed method, the well-known “Phenomenon of an abnormally high thrust increase in a gas ejection process with a pulsating active jet” is used, diploma 314, discovery - 2.07.1951, authors Kudrin OI, Kvasnikov A. V., Chelomey V.N. This process of sequential attachment of additional masses is fundamentally different from the ejection process of parallel attachment, since it is not based on the friction of gas flows. In this regard, its efficiency and coefficient m are higher. Depending on the thermodynamic characteristics of the jet flowing out of the jet devices 12, and the design parameters of the device 74 for connecting the rotating nozzle apparatus 14, the coefficient m (the ratio of the attached mass to the active mass) reaches 50 or more and provides an almost “cold” exhaust. This coefficient is several times higher than that of modern turbofan engines with jet engines and is comparable with the coefficient m of turbofan engines having the highest propulsion efficiency. In the set mode of the cruising rotational speed of the rotor of the jet adaptive engine 75, when it is necessary to create the greatest torque on the power shaft, the increase in the reactive thrust of the rotating nozzle apparatus 14 as a result of the process of sequential addition of additional air masses without additional energy costs reaches 120-140% with respect to initial thrust of jet nozzles. A comparative analysis of the parameters of the process of converting fuel energy in turboshaft gas turbine engines of comparable power, when receiving and using the same amount of reactive mass per unit time, shows that in engines operating on the Brighton thermodynamic cycle with heat supply at constant pressure, more than 50% of the available energy constitute losses due to its thermodynamic imperfection. So, to obtain a reactive mass, energy is spent on the mechanical work of compression in the compressor of the entire mass of atmospheric air involved in the formation of a jet stream, with losses on the efficiency of the turbocompressor, and in the process of continuous combustion, in which the entire compressed mass of air is involved, due to the influence of hydraulic losses, her pressure goes down. Also, losses arising under the influence of viscosity forces increase during the expansion of the entire mass of compressed air during the formation of a reactive mass. In this case, most of the kinetic energy of the jet stream is first used to drive a turbocharger that provides a continuous process of compressing the air to produce it, and only then it is sent to perform the useful work of the thermodynamic cycle - creating a moment on the power shaft of a one- or two-stage blade turbine, which is used 1 / 7-1 / 5 of the available fuel energy. After creating the moment, part of the thermal and kinetic energy of the reactive mass remaining unused is dissipated in the atmosphere, and the greater the degree of compression and the temperature of heating the air before expansion, the greater the share of losses with the output speed in the amount of available energy of the fuel introduced into the engine. To reduce these losses, it is necessary to use multi-stage rotors and recovery systems, which dramatically increases the inertia and mass of turboshaft gas turbine engines and narrows their scope. In the thermodynamic cycle of the proposed method compresses the calculated mass of air necessary only for the formation of pulses of the active stream, which is m times less than that obtained as a result of the process of sequential addition of the combined reactive mass, which creates thrust. Therefore, to compress less mass to the same degree of pressure increase and heating, m times less energy is required. In addition, after ignition of the air-fuel mixture in the periodic combustion chamber, a pressure increase is obtained without energy consumption for the operation of mechanical compression, but only by organizing the combustion process and increasing the temperature of the combustion products in a closed volume. In this regard, another 3-6 times (depending on the composition of the air-fuel mixture) reduce the degree of precompression before igniting the air-fuel mixture and obtaining the calculated pressure of the combustion products and, accordingly, reduce the energy costs already reduced by a factor of an additional factor of one . As a result of reducing the mechanical work of compression in the thermodynamic generator cycle and increasing the potential energy of the combustion products, which is used to increase the kinetic energy of the active jet, which performs useful work in the process of sequential addition of additional masses, the efficiency of the power plant is increased when creating power on the power shaft by a value proportional to the difference in energy consumption for compression and heating of air to form a reactive mass, and the amount of loss in efficiency of devices, stvlyayuschih these processes, as compared to the Brayton thermodynamic cycle. Moreover, they also reduce the speed loss of jet exhaust and heat loss with exhaust gases. In addition, by decreasing in proportion to the increase in m the mass of air compressed in the compressor, the required design power and the mass of the compressor are reduced, thereby additionally increasing the specific power of the power plant based on the jet adaptive engine and expanding its possible applications. For example, for efficient use not only in various stationary systems, but also for driving propulsion devices of various types of vehicles or for driving powerful mobile electric generators or other mobile systems.

 To obtain the necessary moment on the shaft 43 of the rotor 15 of the jet adaptive engine control the thrust force. For this purpose, for example, jet nozzles 63 (FIGS. 11–13), or electro-reactive inkjet devices 65 (FIG. 14,), or a jet device 64 with a radial channel for periodic supply of combustion products (FIG. 15), or detonation chambers are used combustion 66 (Fig. 16) with attachment devices, changing their number and parameters by connecting through separate channels to each device or to groups of devices corresponding in their parameters to a given operating mode, periodic combustion chambers 18 and sources are additionally connected th gas mass to change the magnitude and speed of the combined reactive mass, optimizing energy costs and reducing speed and heat losses of jet exhaust.

 To obtain the required moment on the shaft 43 of the rotor 75 of the jet-adaptive engine, the reactive thrust force is controlled by changing the frequency of thermodynamic cycles in the periodic combustion chambers 18 and, accordingly, the mass and thermodynamic characteristics of the combustion products 12 supplied to the jet devices 12 involved, parameters of the connection processes and the coefficients of attachment of additional masses m involved in the process of creating the combined reactive mass of devices 76-81 attachment, to change the magnitude and speed of the combined reactive mass. At the same time, during the combustion process, the amount of fuel in the composition of the air-fuel mixture does not change, preserving its calculated composition and not increasing the emission of toxic substances into the atmosphere, including during transient modes, for example, sharply increasing the frequency to obtain the rated power if necessary to accelerate the vehicle. Moreover, in the steady state, when the set speed is reached, without changing the amount of fuel in the thermodynamic cycle, the degree of compression of the air is increased, for example, due to additional compression of the incoming flow, while depleting the air-fuel mixture and increasing efficiency.

 The moment on the rotor shaft 15 of the jet adaptive engine is obtained due to the expiration of the combined reactive mass from the rotating nozzle apparatus, for example, the 13 rotor stage 25 and the simultaneous action of the combined reactive mass from the stationary nozzle apparatus (not shown) on the blades 8 of the blade stage 37 of the same rotor. Moreover, the turbine blades and the impeller disk to reduce inertia can be made of lightweight non-heat resistant material.

 Simultaneously with the combined reactive mass obtained in the process of sequential addition of additional masses, to create a moment on the power shaft 43 of the rotor 15 of the jet adaptive engine, the reactive mass obtained in another way is also used, for example, by supplying compressed air from the pneumatic accumulator 7 to the critical section of the jet nozzles 63 of the rotating nozzle apparatus 13, located on the stage 25 of the rotor 15. In this case, the moment is formed due to the stationary expiration of the active jet in the process parallel to connecting additional masses in devices 74-80 for connecting rotary nozzle apparatuses 13.6 and summarize with the moment formed by a fixed nozzle apparatus or rotating nozzle apparatus 14. The use of pneumatic accumulators 7 and other autonomous sources of the working fluid for the formation of reactive mass allows increasing the power of the power plant at peak loads.

 The air for the formation of the air-fuel mixture and for other purposes, including for external consumers, is compressed without decreasing the traction force and the moment on the power shaft 43, and part of the available energy of the reactive exhaust of the rotating nozzle apparatus 14 remaining after creation is used for compression torque on the shaft 43, disposing of it and increasing the efficiency of the power plant. For this, the jet of the combined reactive mass is directed to the blades 31 and 36 of the first 28 and second 39 stages of the blade turbine and is converted into kinetic energy of rotation of the shaft 26 of its rotor, which is connected through the shaft 5 to the shaft 45 of the second stage 39 of the same rotor, and the shaft 45 is connected through a planetary gear 49 with a rotor 51 of a centrifugal compressor (Fig. 1). After compression in a centrifugal compressor, the air through the cochlea 1, valve 3 of the pneumatic accumulator 7 and pneumatic valve 9 along the channel a is sent to the chamber 18.

 Air can also be compressed by using part of the increase in pressure of the combustion products obtained without the expense of energy for mechanical compression, but only by organizing the combustion process of the air-fuel mixture with increasing temperature in the closed volume of the chamber 18 of periodic combustion of the gas generator with a reciprocating compressor (Fig. 29). Why, under the action of the pressure of the combustion products, the valve is moved to the area of the end surface 88 of the spool valve 20 and, acting on the piston 83 of the compressor 84, the spring 19 is compressed. When the piston 83 is moved, the air is compressed in the volume of the compressor 84 to perform useful work when it expands the same thermodynamic cycle. For example, the periodic combustion chamber 18 is cooled and / or blown by combining the bore passages a6 of the slide valve 20 and a5 of the chamber body. At the same time, a vacuum is created in the volume formed behind the moving piston 83 for supplying atmospheric air to it through a non-return valve. After the combustion products are released from the chamber 18 through section C, the piston 83 is returned to its original position due to the energy accumulated by the spring 19, and during its return stroke, the air received through the check valve 87 is compressed, which is directed through the check valve 21 to the periodic combustion chamber 18 for the formation of the air-fuel mixture of the next thermodynamic cycle.

 In order to simplify and increase the reliability of the power plant, the air can also be compressed in the jet compressor (Fig. 32) due to the kinetic energy of the combustion products flowing out from the jet device 12 of the chamber 18 of the periodic combustion of the gas generator 91. For this, the attached mass of air is accelerated in the connection device 80, and then the combined mass is compressed when it is braked in the diffuser 75, obtaining a compressed gas mixture with a proportion of oxidizing agent and combustion products, which, when used as a component, is air-fuel mixture provides combustion and reduction of nitrogen oxides in the combustion products. The resulting mixture is used to perform work when it expands in the same thermodynamic cycle or is directed through a non-return valve 3 to a pneumatic accumulator 7, is accumulated in it to the design pressure and is used at the necessary time, including by feeding through a pneumatic valve 9 through channel a to form a fuel-air mixture in the chamber 18 of periodic combustion of the thermodynamic circuit, as well as through channel a7 into the chamber 18 of the jet compressor.

 To increase the efficiency of using thermal energy obtained from the combustion of the air-fuel mixture, to reduce the specific fuel consumption and thermal stress of the chamber 18, channels B1-B3, in each thermodynamic cycle, the combined reactive mass is obtained when one pulse of the reaction jet of combustion products from the chamber is used in the process of sequential addition of energy 18 and one or more pulses of a jet of pre-compressed jet (for example, due to the moment of utilization of the jet energy of the jet or potential energy of the combustion products when they partially expand in the volume of the chamber 18 of the gas generator with a reciprocating compressor, or the kinetic energy of the combustion products from the jet device 12 of the chamber 18 of the jet gas generator 91 and additionally compressed in the radial channels of the rotating rotor 15 of the jet adaptive engine) atmospheric air or other gases, which through the passage section C1 of the spool valve 20 before the pulse of combustion products from the chamber 18 and / or after it I direct t through the same channels b1-b3 and simultaneously with a decrease in their thermal stresses increase the thermal and potential energy of the compressed gases before expansion, for example, in jet nozzles 63.

 In addition, the thermal energy from the combustion of the air-fuel mixture in the chamber 18, along with the use of the main thermodynamic circuit, preventing its dispersion through the heat-conducting structural elements to the external environment, is used in the second thermodynamic circuit, which is formed by directing along parallel channels, for example, a2 insulated from external environment, another working fluid having a temperature close to ambient temperature, atmospheric pressure or pre-compressed, as in the previous case e. This working fluid in contact with the walls of thermally stressed structural elements, for example, chamber 18, channels B1-B3, inkjet devices 12 of the rotating nozzle apparatus 14, is heated through their heat transfer surfaces and at the same time cool these elements, which perform the functions of a heater with constant pressure with respect to the working fluid .

 To supply the working fluid to the second thermodynamic circuit, the kinetic energy of the reactive mass flowing out from the inkjet devices 12 of the jet adaptive engine 15 is used and creates a vacuum at the inlet 70.71 of the attachment device 74, due to which the working fluid enters this device to form a united reactive masses.

 Moreover, before entering the attachment device 74, the working fluid is compressed in the radial channels a2 of the rotating rotor 15 of the jet adaptive engine. The thermal energy obtained without additional costs of the air-fuel mixture is used in the same way as the increased potential energy of the working fluid when it is expanded to increase the reactive mass and power of the jet-adaptive engine in various operating modes of the power plant (Fig. 1.7). For example, to reduce the acceleration time of the vehicle, and in steady state, to maintain a given speed while minimizing the energy costs of the main thermodynamic circuit due to its temporary shutdown.

 Simultaneously with an increase in reactive mass, depending on the value of the coefficient m, in the process of joining they reduce the rate of its expiration, reducing speed losses and the rotational speed of the rotor 15 of the jet adaptive engine at steady state to a design level at which shaft bearings 43 can be used without the use of forced lubrication systems simplifying the design of the power plant and increasing its reliability. If it is necessary to further reduce the estimated speed of rotation of the bearings in the steady state, their outer or inner rings are fixed, for example, on the shaft of a blade turbine designed to utilize the energy of the reactive mass after creating torque on the shaft, both shafts rotate in the same direction and placed on one axis one inside the other, reducing the speed difference between the outer and inner rings of the shaft bearings 43.

 Part of the available kinetic energy of the combined reactive mass remaining after thrust by the rotating nozzle apparatus 14 of the previous stage of the rotor 15 of the jet adaptive engine is disposed of by deploying the jet in the guide apparatus or in the vanes 31 of the stage 28 and directing them to the vanes 8, following the course of the jet, blade stage 37 of the rotor of the jet adaptive engine 15 for impact on them and obtain additional torque on the shaft 43.

 To increase the efficiency of using the available kinetic energy of the reactive mass remaining after the creation of the traction force by the rotating nozzle apparatus 14 and the torque on the shaft 43 of the rotor 15 of the jet adaptive engine (Fig. 7), the jet is sent directly to the blades 53 of the first stage 54 of the biotational turbine, and its rotor is kinematically coupled to the shaft 43 of the rotor 15 of the jet adaptive engine through a differential planetary gear located in volume 55 with a gear ratio that provides a calculated reduction e of the first stage 54 birotativnoy rotational speed of the turbine and, accordingly, its circumferential speed of the blades 53 rotating in a direction opposite to the rotation direction of the rotor of the rotary nozzle unit 14, 75 jet-adaptive engine. By reducing the difference in these speeds and increasing the speed of the reactive mass relative to the blades 53, the force of its action on these blades and the torque on the shaft of the first stage 54 of the biotational turbine are increased. This moment through the satellites 56 and the central gear 58 is summed with the moment created on the shaft 43 due to the reactive thrust of the rotating nozzle apparatus 14. The carrier shaft 57 of the first stage 54 of the biotational turbine is connected with the rotor of its second stage 59, rotating in the opposite direction. The moment formed by stage 59 when the jet acts on its blades 52 on the carrier shaft 57 is also summarized by combining all three power flows into one through a differential planetary gear and providing the optimal ratio of the increase in the force of the jet on the blades 53.52 stages 54.59 of the biotic turbine with the efficiency of these steps, depending on the speed of their rotation. The resulting total power, depending on the specific design, can be transmitted to the consumer simultaneously through several or through any of the three shafts.

 In order to maintain the high efficiency of the biotational turbine and obtain the calculated rotation speed and torque on the output shaft of the power plant, which are required directly to drive the vehicle propellers, the total power generated on the output shaft of the carrier 57 is transmitted to the consumer through a gearbox, for example, another planetary gear located with a biotic turbine and a rotor 15 of the jet adaptive engine in the total volume of the power plant housing (Fig. 7). For this purpose, the carrier shaft 57 is connected through the central gear 60 and the satellites 62 to the carrier 61. For example, a structure with such an arrangement can be placed in a volume not exceeding the internal space of the vehicle’s wheel disk and transmit power for its drive without additional transmission, to including for reverse.

 Along with increasing the torque on the output shaft with the use of an additional gear, the part of the available kinetic energy of the reactive mass remaining after expiration from the blades 52 of the second stage 59 of the biotational turbine is also used. For this, the total power generated on the output shaft of the carrier 57 of the differential planetary gear is transmitted through the central gear 60 of the input shaft and the satellites 62 to the rotor of the first stage of the additional biotational turbine with an additional differential planetary gear (not shown), and through the shaft of its carrier to the fixed on it is the rotor of the second stage of this turbine. Due to the gear ratio of the additional differential planetary gear, the rotational speeds of the rotors are reduced and synchronized and the moment on their shafts is increased, and due to the remaining kinetic energy of the reactive mass flowing out from the blades 52 of the second stage 59 of the previous biotative turbine and acting on the blades of both stages of the additional biotative turbine, create an additional total moment on the shafts of its rotors. To transfer power to the consumer, one shaft is used as an output for propeller blades or a single-row rotor fan, or both shafts are used simultaneously with power sharing to drive a two-row rotor fan, converting the kinetic energy of rotation into kinetic energy of a jet stream, creating a jet propulsion of the power plant as a propulsor.

 The reactive mass flowing from the last stage of the biotational turbine is guided through the channels located inside the fan blades or fan fan, mounted on the output shaft of the carrier of an additional differential transmission, for the outflow from the peripheral part of the blades and the formation of reactive traction, and additional torque on the shaft.

 As a result of the use of a bi-turbine turbine with a differential planetary gear to use the kinetic energy of the jet of a rotating nozzle, which remains after the moment is formed on the power shaft of the jet-adaptive engine, they increase the efficiency and specific power of the power plant, as well as get additional advantages when assembling and using it for drive various propulsion vehicles.

 The combined reactive mass, the kinetic energy of which was used to perform useful work, is used in the following thermodynamic cycles as an additionally attached mass. For this, the exhaust channel b5 (Fig. 1) of the power plant is connected through the pneumatic valve 10 to the inputs of 70.71 devices 74 for connecting additional masses of the rotating nozzle apparatus 14 (Fig. 1.10) and form a closed thermodynamic circuit. Under the action of rarefaction obtained due to the kinetic energy of the jet flowing out of the jet devices 12, for example, into the device 78 for adding additional masses (Fig. 25), the exhaust gases moving along the exhaust channel b5 with the pneumatic valve 24 open (Fig. 1) into the external environment enter the device 78 attachment for the formation of a reactive mass, combined in this cycle with the products of combustion. With an increase in the total mass of exhaust gases in a closed thermodynamic circuit due to the amount of products of combustion, their surpluses are displaced from the exhaust channel b5 through an open pneumatic valve 24, the mass of which is from the total combined reactive mass of the thermodynamic cycle, which creates a moment on the power shaft, equal to 1 / m, where m is the value of the coefficient of accession of additional masses.

 Thus, in comparison with a gas turbine engine with a thermodynamic cycle at constant pressure, along with a reduction in the cost of energy for compression and heating of atmospheric air, when creating adequate power, an amount of m times less atmospheric air is required.

 Moreover, in a closed thermodynamic circuit due to the kinetic energy of the jet stream, which creates a vacuum at the inputs of 70.77 devices for connecting additional masses 69, form a cyclically repeating circular motion of the exhaust gases. A filter for mechanical cleaning and a catalytic converter 4 are installed in their exhaust channel b5 on their way to reduce the emission of toxic substances. By increasing the number of cycles, they improve the quality of exhaust gas purification and increase the efficiency of their neutralization. In addition, an increase in the contact time of the reagents makes it possible to use less expensive elements rather than rare-earth and noble metals as catalysts.

 When using devices 76-81 connecting additional masses (Fig. 23-28), blade stages 37 of the rotor 15 of the jet adaptive engine and / or biotative and other blade turbines that perform useful work due to the kinetic energy of the reactive mass flowing from the jet devices 12 when exhaust gas is exhausted through exhaust channel b5 through an open pneumatic valve 24 into the atmosphere, the speed of supersonic pulses of the jet of combustion products is gradually reduced to a design level that reduces noise e effect to regulatory requirements without the use of additional external jamming systems.

 The required power on the output shaft 43 of the power plant is obtained through the combined use of an adaptive jet engine and an engine of a different operating principle, for example, an electric motor 41, and they are included in the operation together or independently.

 The necessary power on the output shaft 43 of the power plant is obtained using compressed air that is sent from the pneumatic accumulator 7 through mechanical means to form an active jet flowing out during the sequential connection from the jet devices 12 of the nozzle apparatus 14, along with the products of combustion from the chamber 18 of periodic combustion or a pneumatic device (not shown) providing its supply to the critical section of the jet nozzles in a pulsed mode.

 The power of the jet adaptive engine 15 of the power plant (FIG. 1) is controlled by changing the pulse frequency of the jet, which is active during the sequential addition of additional masses, by changing the frequency of the combustion cycles in the periodic combustion chambers 18 and changing the frequency of the pulsed compressed air supply.

 After creating the moment on the shaft 43, part of the energy of the reactive mass is utilized by directing the jet onto the blades 31,29,36,38 stages 28,39 of the rotor of the blade turbine-compressor-flywheel (Fig. 1), which is not connected with the shaft 43, and accumulate in the form the kinetic energy of rotation of the stages 28.39 of its rotor, as well as the planetary gear 49, the rotor 51 of the centrifugal flywheel compressor, the gear 44.50 and the rotor 47 of the electric generator with inertial mass. The energy accumulated by the inertial mass of these devices is converted into electrical energy by connecting the load to the winding 48 of the rotor 47 of the electric generator, which is connected through the gears 50 and 44 to the shaft 45 of stage 39. This energy is also converted into potential energy of compressed gas, supplied for compression to the input of the centrifugal rotor 51 a flywheel compressor with open pneumatic valves 9 and / or 16 through channels a and a3 through rotating nozzle apparatuses 13 and 6, blades 29.33.38 and volume X atmospheric air. Compressed air as well as electricity is used to perform useful work, as well as to provide external consumers directly at the time of its generation and / or accumulate, respectively, in the pneumatic accumulator 7 and / or electric accumulators. In this case, the permissible design limits of the rotational speed of the rotors 28,39,51 are monitored by sensors and supported, increasing when the permissible limits are exceeded, the amount of energy spent by the inertial mass is consumed by its conversion, thereby reducing the speed to the design level.

 The accumulated energy of additional sources is used autonomously and together with the energy accumulated by the inertial mass, converting it when additional power is required on the shaft 43 in excess of the power obtained due to the kinetic energy of the reactive mass containing combustion products and flowing out from a stationary nozzle apparatus and / or rotating nozzle apparatus 14 of the main thermodynamic circuit. It is also used to partially replace the energy received from burning fuel in the periodic combustion chambers 18 or to completely replace it, in which, by controlling a discrete combustion process, the burning of fuel and the emission of combustion products into the atmosphere are reduced or completely stopped.

 Thus, due to the utilization of the kinetic energy of the jet stream remaining after creating the moment on the power shaft 43 and its additional conversion, they reduce fuel consumption and, replacing its energy with the utilized one, increase the efficiency and improve the environmental characteristics of the power plant, as well as increase its power in moments of peak loads.

 When starting the power plant, the initial inertial mass of kinetic energy is accumulated to the calculated level by rotating the stages 28.39 of the rotor of the blade turbine-compressor-flywheel (Fig. 1.4) and the rotor 51 of the centrifugal compressor-flywheel by connecting the winding 48 of the electric generator included in electric motor mode, to external sources of electricity. The resulting moment is transmitted through gears 50.44 to the shaft of the rotor of the blade turbine-compressor-flywheel and to the shaft 49 of the rotor 51 of the rotor 51 of the centrifugal compressor-flywheel. In the absence of external sources of electricity, the initial accumulation is carried out due to the kinetic energy of the reactive mass from a fixed nozzle apparatus and / or a rotating nozzle apparatus 14 of the rotor 75 of the jet adaptive engine. This jet is directed to the blades 31,36 and converted into kinetic energy of all devices with inertial mass. In this case, depending on the calculated value of the inertial mass and the speed of its rotation gained at start-up, it is possible to accumulate an amount of energy exceeding, for example, the energy reserve of an electric vehicle of comparable load capacity for its mileage without recharging electric accumulators, and the specific power of the inertial mass as an energy storage ten times higher.

 The mass of the rotor 51 of the centrifugal flywheel compressor is selected from the condition that it performs the functions of a device having an inertial mass that accumulates kinetic energy, which allows to increase the efficiency of the compressor design and simplify its production technology due to the absence of mass restrictions. Part of the energy of the inertial mass of the rotor 51 is used in the same compressor to convert compressed air into potential energy. After compression, air through the check valve 3 is pumped into the pneumatic accumulator 7, which is used as a source of compressed air with controlled distribution and consumption. The air is accumulated in the pneumatic accumulator 7 to the upper calculated pressure level controlled by the sensor, above which the pneumatic valve 16 blocks the access of atmospheric air entering through channel a3 through the device 74 for connecting the rotating nozzle apparatus 13, blades 29.33.38, volume X to the input of the rotor 51 centrifugal compressor. At the same time, through the pneumatic valve 2, the remaining compressed air is discharged from the cochle 1. In this case, the rotor 51 of the centrifugal compressor-flywheel continues to rotate idle, without spending the energy of the inertial mass for compression. In the process of consuming compressed air through the pneumatic valve 9, when the pressure in the pneumatic accumulator 7 decreases below the calculated level, the pneumatic valve 16 is opened to supply atmospheric air to the inlet of the rotor 51 of the centrifugal compressor-flywheel and only then continue the compression process until the air supply is stopped at the next exceeding of the calculated pressure level in the pneumatic accumulator 7. As a result of a discrete compression process, the energy of the inertial mass is effectively consumed, ensuring the flow of compressed air in a given mode, for example To form a fuel-air mixture in a batch inclusion calculated amount of combustion chambers 18 and / or the use of the second circuit as the thermodynamic working fluid and / or by using external consumers. In this case, the volume of consumption of compressed air can vary from the minimum necessary to the maximum, limited by the capacity of the centrifugal flywheel compressor.

 To improve the efficiency of the process of utilization of the kinetic energy of the reactive mass remaining after the creation of the torque on the shaft 43, as well as the process of its accumulation by the inertial mass, due to planetary gear 49, the rotational speed of the stages 28.39 of the rotor of the blade turbine-compressor-flywheel (Fig. 1) reduce relative to the rotational speed of the inertial mass of the rotor 51 of the centrifugal flywheel compressor.

 By increasing the rotational speed of the rotor 51 of the centrifugal flywheel compressor, they increase the efficiency of the compressor, as well as its efficiency as an energy storage device, while increasing the speed of the reactive mass relative to the peripheral speed of the blades 31.36 and the force of the mass acting on these blades to increase the efficiency of the disposal process. The shaft 45 of the blade turbine-compressor-flywheel is located inside the shaft 46 of the rotor 51 of the centrifugal compressor-flywheel and both shafts are rotated through the planetary gear 49 in one direction, and the difference between the rotational speeds of the outer and inner rings of the bearings 40 of the shaft 40 of the rotor 51 of the rotor 51 of the centrifugal compressor is the flywheel is reduced by the value of the rotational speed of the shaft 45, on which these bearings are mounted, and, despite the high rotational speed of the compressor rotor 51, bearings 40 are used with the same limiting rotational speeds as the bearings 27, and also without forced lubrication systems, thereby reducing the mass of the power plant and simplifying its design and operation.

 The mass of the rotor 47 of the electric generator is selected from the condition that it performs the functions of a device having an inertial mass for accumulating kinetic energy, which is converted into electric generator in the same electric generator for use by a traction motor 41, which transmits torque through the gears 42 to the shaft 43, as well as to provide other consumers electricity, including external, and / or for accumulation and use at the right time.

 After a temporary stop of the propulsion device, or when the vehicle is moving by inertia, or a predetermined decrease in speed, the energy is not spent on the forced rotation of the shaft 43 without performing useful work, thereby excluding the "idle" mode. At the beginning of the vehicle’s movement, the moment necessary to bring the power shaft 43 from a stationary state into rotation is created using the discreteness of the fuel combustion process and the supply of the working fluid to the inkjet devices 12 to connect to them at any given time the estimated number of cameras 18 for periodic combustion and other autonomous energy sources, including those generated due to the energy accumulated by the inertial mass, and supplying the necessary amount of a working fluid with calculated thermodynamic nature sticks for the formation of the total reactive mass flowing out from the involved jet devices 12 and devices 74 connecting the rotating nozzle apparatus 14, providing a given moment on the power shaft 43. At the same time, due to the low inertia and the inverse dependence of the moment on the shaft 43 on the rotational speed of the rotor 15 jet adaptive engine reduce the time required to accelerate the vehicle after the start of movement. Thus, they further increase the efficiency and environmental friendliness of the vehicle, especially in urban traffic conditions.

 In addition, for a given reduction in speed or movement under the action of external forces, the kinetic energy accumulated by the mass of the vehicle is converted through its mover into the kinetic energy of the rotor of the traction motor 41 included in the generator mode and / or of the compressor rotor (not shown), in which the gases are compressed and sent through the stationary nozzle apparatus to the blades 29.31 and 38.36 of stages 28.39 for conversion into kinetic energy of the inertial mass and / or through the shaft 43 into the energy of rotation of the rotor 15 of the jet adaptive engine, in which the radial channels of compressed gases and a reaction mass from its rotating nozzle devices 14,13,6 also directed to the energy conversion, its inertial mass storage and use, with a corresponding reduction in the fuel mixture flow.

 The operation of the power plant in an environment with a pressure exceeding atmospheric, for example, under water, is ensured by using the energy accumulated by the inertial mass of the stages 28.39 of the rotor of the blade turbine-compressor-flywheel and the rotor 51 of the centrifugal compressor to simultaneously create a vacuum in volume 6 of the exhaust channel b5 located to the compressor blades 34, into which the reactive mass flows out of the rotating nozzle apparatus 14, and the compression of the exhaust gases due to the energy of the inertial mass in the exhaust channel B5, located behind the compressor blades 34,30. For this, the inputs of 70-73 devices 74-80 for connecting a rotating nozzle apparatus 14 through compressor blades 34,30 by a pneumatic valve 10 are connected to a volume of 6, forming a closed thermodynamic circuit. In this circuit, the gases exhausted in previous cycles are used as a mass to be attached, which performs a cyclically repeated process of sequential connection, with their increased pressure at the inlet to the devices for connecting the rotating nozzle apparatus 14, to the reactive mass flowing out of the jet device 12 and consisting of combustion products of this cycle, and ensure the flow of the combined reactive mass into the volume b6 with reduced pressure, further increasing the thrust of the rotating nozzle apparatus 14 and cop on the shaft 43 of the rotor 15 of the jet adaptive engine. To exhaust excess exhaust gas, exhaust channel B5 is connected to the external environment through a non-return valve 22 and bleeds part of the compressed gases through it after the pressure created behind the compressor blades 34.30 exceeds the pressure of the external medium and the bleed is completed when it is equalized with the pressure outdoor environment. Due to the fact that the mass of the combustion products necessary for the formation of active jet pulses during the sequential addition of additional masses is less by a factor m than the combined reactive mass creating a moment on the power shaft 43, the actual flow rate of air or other oxidizing agent decreases in comparison with turbo-type gas turbine engines with a thermodynamic cycle at constant pressure (with equal consumption of reactive masses per unit time and equal power), is proportional to an increase in the coefficient m, and accordingly It consumes a much lower power piston internal combustion engine. Thus, when the pressure overboard does not exceed the maximum pressure created by the compressor due to the energy of the inertial mass, both previously accumulated, for example, due to external energy sources, and accumulated during the operating mode of the jet adaptive engine, it is possible to burn fuel during operation under water and spend on the execution of the same amount of work a much smaller amount of oxidizing agent.

 After the exhaust gases are compressed in the exhaust channel b5 of a closed thermodynamic circuit, they can be directed through an adjustable non-return valve to the receiver (not shown), accumulated in it to the design pressure, and if the pressure decreases overboard, at the right time it can be used as a working fluid to make a useful work, for example, expansion in the inkjet devices 12 with subsequent release into the external environment.

 When working underwater, part of the energy of the inertial mass is converted into electrical energy and used to create moments on the power shaft 43 by the electric motor 41, and / or accumulated and / or hydrolyzed to partially replace fossil fuels and compressed air with hydrogen and oxygen and use some of the oxygen in life support systems.

 In a closed thermodynamic circuit, due to part of the kinetic energy accumulated by the inertial mass, cyclically repeating circular motion of the exhaust gases is formed and they are mechanically cleaned with a filter and neutralized by a catalytic converter 4 to reduce the emission of toxic substances in the emission. To do this, the blades 34.31 stages 39.28 compress the exhaust gases, increasing the pressure in the exhaust channel b5, under the influence of which they enter the input, for example, 73 devices 78 connecting a fixed nozzle apparatus or a rotating nozzle apparatus 14 of the rotor 15 of the jet adaptive engine. By repeating the cycles of passing through the filter and the exhaust gas neutralizer 4, they improve the quality of mechanical cleaning, as well as increase the contact time of the reactants with the catalyst, which, along with increased pressure, increase the rate of chemical reactions and the efficiency of neutralization.

 The energy accumulated by the inertial mass is used to generate “cold” and create power on the power shaft without emitting exhaust gases into the environment, for example, when working under water. For this, atmospheric air is preliminarily compressed in the rotor 51 of the centrifugal flywheel compressor and then accumulated in the pneumatic accumulator 7. At the necessary moment, directly or through a heat exchange device (not shown), compressed air from the pneumatic accumulator 7 is sent to the jet nozzles 63 of the jet adaptive engine 15, expanding in the nozzles, create a jet stream, the moment on the shaft 43 and lower the temperature of the air, which is then used to cool the elements of the power plant or sent through a pneumatic valve 35 for cooling external objects, then at least partially recycled to the compressor rotor 51 for recompression and re-directed to the accumulator 7, forming a closed refrigerant circuit.

 The consumed mass of air is replenished from the atmosphere, creating due to the kinetic energy of the jet formed during the expansion of compressed air from the pneumatic accumulator 7 in the jet nozzles 63, a vacuum, for example, at the inlet 70 of the device 77 for adding additional masses for the inflow of atmospheric air, which is used as an additional the mass to be attached in the process of joining. As a result of this process, a combined reactive mass is created that increases the moment on the power shaft 43, and a part of its kinetic energy remaining after creating the moment is disposed of, and after the recycling process, it is sent to consumers to use part of the “cold” and / or to the inputs of connection devices 70-73 the next stage 37 of the rotor 15 of the jet adaptive engine and then to the input of the compressor rotor 51 for re-compression.

 Atmospheric air entering the inputs 70-71 of the device 74 connecting rotary nozzle devices 13.6, with periodic replenishment of the air consumed from the refrigeration circuit, during the process of connection it is cooled to a temperature at which the moisture contained in the air is frozen during the expiration of low-temperature jets in the form of ice crystals and catch, concentrating in volume X, located before the entrance to the rotor 51 of the centrifugal compressor-flywheel. When pneumatic valves 9 and 16 block the access of air, the outflow of low-temperature air ceases, and ice crystals melt under the action of heat transmitted through the heat-conducting structural elements of the thermodynamic circuit and / or under the action of specially heated elements, and the resulting water is sent to a container for use in the field or electrolysis on board a vehicle, also provided by energy stored by inertial mass.

 To obtain a reactive mass that generates a torque on the power shaft 43 of the rotor 51 of the jet adaptive engine (Fig. 1, 7), several working fluids with different thermodynamic characteristics are used. Due to the main, with greater potential energy, for example, from the chamber 18 of periodic combustion or the pneumatic accumulator 7, a jet stream is formed through the jet device 12, flowing out, for example, through the entrance 70 to the connection device 74. Another working fluid, for example atmospheric air, is also directed to the inlet 70 of the attachment device 74. In this device, due to the partial transfer of kinetic energy of the jet of the main working fluid, which performs the function of the active jet in the process of adding additional masses, the kinetic energy of the additional masses of the working fluid being added is increased, accelerating it and then combining both working bodies in one stream. As a result of this process, depending on the attachment method, the thermodynamic characteristics of the working fluid and the geometric parameters of the attachment devices 74, the magnitude of the combined reactive mass increases compared to the initial mass of the active jet and the moment on the shaft 43 of the rotor 15 of the jet adaptive engine without additional fuel energy consumption . In this case, the magnitude and speed of the combined reactive mass is controlled by changing the number and parameters of the inkjet devices 12 and attachment devices 74 involved in the process of its creation, by connecting the working fluid sources through separate channels b1, b2, b3, b4 and changing the thermodynamic characteristics of the working fluids supplied from these sources to each involved device or to groups of devices, with the calculated parameters for this operating mode, as well as changes in the parameters of the processes of connecting additional m ass, adjusting the jet-adaptive engine to achieve optimal efficiency when generating the total moment in various operating modes, thereby adapting it to the conditions of multi-mode application. For example, at the beginning of the vehicle’s movement, when it is necessary to sharply increase the power, to create a united reactive mass, more inkjet devices are connected and a larger total combined reactive mass with a lower flow rate is obtained than in driving modes in which the total combined reactive mass is reduced and increased its speed, because in order to overcome the resistance at the steady state mode of movement of the vehicle it is required to slightly accelerate or support amb achieved speeds. In modes with a given constant energy consumption, to adapt the jet-adaptive engine to load changes, the nature of the dependence of the moment value on the rotor speed is used, getting the maximum moment at the rotor speed equal to zero with its automatic decrease, as the rotor speed increases, it is proportional to the decrease the difference in the velocity of the expiration of the reactive mass and peripheral speed. For example, when with increasing resistance to movement and constant energy consumption for generating power on the shaft 43, the speed of the ground vehicle decreases and, accordingly, the rotational speed of the rotor 15 of the jet-adaptive engine associated with its propulsion device is simultaneously automatically (without changing gear ratios for power transmission mover and interruptions in work) increases the moment to overcome it, and with a decrease in resistance - on the contrary, the speed increases and the moment decreases.

 The combined reactive mass obtained in the process of attaching additional masses flowing out of the fixed nozzle apparatus attachment device 74 (not shown) is sent to the blades of the 8.33 blade stage 37 of the rotor 15 of the jet adaptive engine.

 The expiration of the combined reactive mass obtained in the process of joining the additional masses is carried out from devices for connecting rotary nozzle devices 74 located at different levels of the external parts of the impellers of stages 25.37 of the rotor 15 of the jet adaptive engine to create reactive thrust and torque on the shaft 43, the main the working fluid is fed into the jet device 12 of the rotating nozzle apparatus to create a jet stream, which performs the function of an active in the process of attaching additional m ass, on the radial channels of these steps.

 The moment on the shaft 43 of the rotor 15 of the jet adaptive engine is obtained due to the simultaneous action of the combined reactive mass from the fixed nozzle apparatus, for example, on the blades 8 of the blade stage 37 and the expiration of the combined reactive mass from the rotating nozzle apparatus 13 of the stage 25 of the same rotor 15 of the jet adaptive engine.

 An additional moment on the shaft 43 with a multi-stage rotor 15 of the jet-adaptive engine is formed by directing a jet flowing, for example, from a rotating nozzle apparatus 14 (Fig. 1.4) of the previous stage 25, through the blades 31, which play the role of a guide apparatus, on the blades in the next stage 37 of the rotor 15.

 To increase the moment on the shaft 43, a jet stream flowing out of the previous stage 25 (Fig. 1,5), through the blades 29, acting as a guide apparatus, is sent to the blades 33 of the next stage 37 of the rotor 15, and after expiration from the blades 33 as attached the mass is directed to the input 70 of the device 74 for connecting a rotating nozzle apparatus 6 located at the same stage 37 of the rotor 15 behind the blades 33 in the direction of the jet.

 To form reactive jets that are used as active jets, jet devices 12 of various operating principles are used, for example, electroreactive 65 (Fig. 14), jet nozzles 63 (Fig. 11-13), detonation combustion chambers 66 (Fig. 16) . A jet stream from these devices is sent directly to the inputs 70-73 (Fig. 17-22) of the attachment devices 76-81 (Fig. 23-28) and / or through the radial channel 64 (Fig. 15).

 When these jets are formed, for example, in detonation combustion chambers 66 (Fig. 16), the combustion products along the annular channel B2 through the jet nozzles 69 are directed towards each other at the focal point 68 of the spherical part 67 of the detonation combustion chamber 66 in the form of jet jets. A parallel air-fuel mixture is fed through a parallel channel a2, the jet of which is directed to the same point 68 to collide the jets, causing a local increase in temperature and pressure and initiating a self-oscillating detonation combustion process with the formation of high-frequency detonation waves propagating in the opposite direction from the spherical part 67 of chamber 66 , and with high kinetic energy dispersing combustion products. The process continues until the supply of combustion products or air-fuel mixture ceases and continues when the supply is resumed.

 The potential energy of the main working fluid, for example, from the pneumatic accumulator 7, in the jet device 12 is converted into the kinetic energy of a jet stream stationary expiring into the attachment device 74, for example, a rotating nozzle device 13. The input 71 of the device 74 through channels a3 through the pneumatic valve 16 and the inlet pipe 11 connect with the atmosphere. At the same time, the rotating nozzle apparatus 13 increases thrust according to the principle of ejectors operating in the parallel connection mode, transferring part of the energy of the ejection jet to the attached air masses due to turbulization and mixing of flows in the additional mass connecting device 74.

 The potential energy of the main working fluid in the jet device 12 is converted into the kinetic energy of the pulses of the jet stream. When the gas mass moves in the attachment device 74-80, a vacuum is created after it, which is maintained for the period of time necessary for successive flowing after each pulse from the gas mass of the main working fluid to the estimated amount of additional masses that accelerate due to energy during the attachment pulses of the jet stream, forming a combined stream in the device 74-80 attachment and the combined reactive mass at its output. This process is the interaction of the separated gas masses of the pulses of the jet stream with additional masses of gas flowing in under the action of the vacuum generated by the pulse and pushed out by the next pulse, i.e. it is a process of sequential addition of additional masses, which in its mechanism is fundamentally different from the ejection process, since it is not based on the friction of gas flows, and therefore the efficiency of this process is higher, and the increase in the momentum of the jet stream of the combined mass is up to 120% or more from the original the magnitude of the pulse of the jet of the main working fluid, depending on the thermodynamic characteristics of the working fluid and the geometric parameters of the device 74 attachment.

 The potential energy of the main working fluid in the jet device 12 is converted into the kinetic energy of the pulses of the jet stream, each of which forms a vacuum in the device 74-80 for adding additional masses. On channel a2, connected directly to the input 71 of the same device, atmospheric air or another working fluid enters due to the formed vacuum. In the process of joining, due to the energy of the pulses of the main working fluid, the kinetic energy of the working fluid supplied through channel a2 is increased, forming a combined flow in the connecting device 74-80 and a combined reactive mass at its output. This process is comparable to the process taking place in a ramjet pulsating dual-circuit jet engine.

 To obtain pulses of a jet stream, which form a vacuum in the attachment device 74 during the sequential addition of additional masses, two working fluids different in their thermodynamic characteristics are used, which feed, for example, through channels b1-b3 to the critical cross section of the jet nozzles 63 from various sources with a calculated frequency and sequence. The pulses formed by the working fluid with less potential energy are used to preliminarily accelerate additional masses in order to reduce losses by reducing the difference in the meeting speeds during their subsequent interaction with the gas mass of the pulse formed during the expansion of the main working fluid with a higher kinetic energy, as well as relative reducing the cost of its energy, increasing the coefficient m and the speed of the combined reactive mass.

 The potential energy of the main working fluid in the jet device 12 is converted into the kinetic energy of the pulses of the jet stream, forming in the device 74-80 joining additional mass rarefaction. Another working fluid with constant pressure and lower potential energy is directed through the a2 channel to the input of the same device through an annular jet nozzle 73 to form a jet stream stationary expiring parallel to the direction of the jet pulse expiration. The energy of a stationary flowing jet is used in the process of connecting additional masses entering the input 73 of the device 74-80 in the intervals between pulses to create a constant rarefaction at the entrance 73 to the device 74 of the connection and their preliminary acceleration due to ejection by this jet, in order to reduce energy losses in the subsequent interaction of additional masses with the mass of pulses due to a decrease in the difference in the meeting speeds and, as a result, a relative decrease in the kinetic energy of pulses increase the coefficient m and the speed of the combined reactive mass.

 The process of attaching additional masses is carried out sequentially in the device 81 (Fig.28), using simultaneously two device 74 attachment located in series one after another. The jet stream flowing out after the attachment process from the first device 74 performs the function of an ejection jet during the attachment process in the second device 74. Simultaneously with the increase in momentum, due to the increase in the combined reactive mass, its outflow rate and the angular velocity of the rotor 15 of the jet adaptive engine are reduced to the calculated level .

 In multi-mode applications, when the rotational speed of the rotor 15 of the jet adaptive engine changes, the critical section area of the jet nozzles 63 is automatically changed by changing the centrifugal force, adjusting it to the flow rate of the main working fluid in accordance with the required moment in a given mode. For example, when accelerating a vehicle during the start of movement, the greatest power on the shaft is required, therefore, the nozzle cross-sectional area in this mode is maximum. The cross-sectional area is reduced by moving the control element of the nozzle 63, for example, the central body, under the action of a centrifugal force, which increases as the rotational speed of the rotor 15 is set, to the minimum critical section area in steady state.

 When using a jet-adaptive engine in aircraft engines after creating a moment on the shaft 43, the remaining part of the available kinetic energy of the reactive mass can be used by controlling the direction of its outflow, for example, by means of an adjustable guide apparatus for the formation of reactive thrust.

 As the rotor 15 of the jet adaptive engine, a vehicle propulsion device is used, for example, propeller blades or fans, or propeller fans, or part of their blades, on which, for example, a rotating nozzle apparatus 14 is placed, which generates traction and torque on the shaft 43. Estimated speed of rotation the blades are provided without the use of a mechanical gearbox by changing the parameters of the joining process, the amount of the total combined reactive mass and its expiration rate. The kinetic energy remaining after creating the moment on the shaft 43 is used by controlling the direction of the outflow of this reactive mass to create additional thrust to the thrust created by the vehicle propulsion.

A compressed working fluid with a temperature close to ambient temperature is expanded in the jet nozzles 63 and cooled, depending on the degree of compression thereof, to negative temperatures below -130 ^o C, while using the rotor 15 of the jet adaptive engine to create power on the shaft 43 and fulfillment of functions - expander. Then, in the process of adding additional masses to the connection device 76-80, the engine is used to perform the functions of an air refrigerating machine with refrigerant - the main working fluid, cooling the additionally connected masses coming through the inputs 70-73 of the connection device 76-80. The air temperature is lowered to the calculated one with the possibility of its regulation within the limits depending on changes in the quantity, the range of thermodynamic characteristics of the main working fluid and the coefficient of addition of additional masses m.

 When creating a moment on the shaft 43, the jet adaptive engine is simultaneously set to operate in pump mode to pump external gas masses due to the kinetic energy of the reactive mass flowing out from the jet devices 12 into the attachment devices 74 and creating a vacuum at their inputs 70-73. When the shaft 43 is forced to rotate, for example, by an electric motor 41, it is set up to operate in a centrifugal compressor and a jet generator mode for compressing external gases in the radial channels a2, b3 of the rotor 15 and converting their potential energy in the nozzles 63 into the kinetic energy of the jet.

 To generate a working fluid by a gas generator, fuel is burned in a closed volume of the chamber 18 for periodic combustion (Fig. 29), increasing the pressure and the available work of expanding the combustion products in each thermodynamic cycle. Due to a part of the obtained increase in the potential energy of the combustion products, when they partially expand in the closed volume of the chamber 18, work is performed to move the spool valve 20 from the initial position, in which the spring 19 acting on it is unclenched and the passage section C used to exhaust the combustion products is closed into the exhaust channel b1 along its axis by the calculated distance. During the passage of this distance, the spring 19 is compressed, accumulating energy to ensure a return to the initial position - the reverse stroke of the slide valve 20 and open the passage section C for the release of combustion products. After it is opened under the action of the compressed spring 19, the valve 20 stops and the return stroke begins, during which a fuel is injected under pressure and compressed air is supplied through the non-return valve 21, providing mixing of the components of the air-fuel mixture for the next thermodynamic cycle that begins after the slide valve 20 returns to the initial position when igniting the air-fuel mixture in the volume of the chamber 18 of the periodic combustion of the gas generator, which is carried out after a given period of time . At the same time, the necessary thermodynamic characteristics and the amount of combustion products generated per unit time are obtained depending on the purpose and modes of use of the gas generator due to the set periodicity of ignition of the air-fuel mixture, changes in the pressure of compressed air for its formation, changes in the volume of the periodic combustion chamber with controlled filling of part of it internal volume fireproof mass. Moreover, regardless of which (s) of these methods are used to change the parameters of the combustion products, in all thermodynamic cycles they provide a constant amount of fuel injected, including in transition modes with a sharp change in the amount of working fluid produced per unit time, without increasing the emission toxic substances into the atmosphere. In steady state, with an increase in the degree of air compression, for example, due to additional compression of the incoming air flow, the air-fuel mixture is depleted and the gas generator is more economical. In addition, in all cycles also provide the estimated duration and amplitude of the pulses during the release of combustion products. In this regard, the use of this method for the formation of an active jet in the process of sequentially connecting additional masses in a jet adaptive engine increases the efficiency of the power plant. The values of these parameters in this method of energy conversion at a set design pressure in the combustion process and constant bore sections C can only change due to the opening and closing times of bore sections C, depending on the distance over which the spool valve 20 moves and the spring forces 19 having a calculated value, and independent of the change in the frequency of thermodynamic cycles, the range of which can be very wide, since each subsequent cycle can begin at any given time after the return The slide valve 20 is returned to its original position, and the return time can be up to thousandths of a second.

 Due to the energy of the combustion products, when they partially expand in the closed volume of the chamber 18, the slide valve 20 is moved. The valve 20, moving under the action of the pressure of the combustion products, at the calculated moment engages with the piston fuel valve 89 and starts its movement from the volume D along the axis on estimated distance (Fig.30.31). This volume during the direct stroke of the slide valve 20 is isolated from the bore 82 for fuel injection by the check valve 90, therefore, when the piston fuel valve 99 moves, the volume not occupied by fuel increases and a vacuum forms. At the end of the forward stroke of the slide valve 20, the piston fuel valve 89 opens a passage section C2, through which the volume D is connected to the channel T, which serves to supply fuel from the fuel line. Under the action of the resulting vacuum, the calculated volume D is filled with fuel from the channel T. During the return stroke, due to the energy accumulated by the spring 19, the spool valve 20, moving the piston fuel valve 89 to its original position, closes the passage section C2 with it and isolates the fuel entering the volume D, from channel T. Then, a pressure is created in the volume D by the piston fuel valve 89, under the influence of which the calculated amount of fuel filling this volume is displaced through the d channel through the check valve 90 for injection through the cross section 82. The fuel is supplied for the formation of the air-fuel mixture in the first thermodynamic cycle by forcing the slide valve 20 and compressing the spring 19 by the electromagnet 85. The fuel is sprayed to efficiently mix the air-fuel mixture due to the potential energy of the spring 19. Moreover, the dimensions of the chamber 18 allow place a spring for fuel injection under pressure of several tens or even hundreds of atmospheres. As a result, the fuel injection process is carried out without any synchronization with the control systems and pressure for injection is obtained, which ensures high-quality atomization of the fuel.

 The purge of the periodic combustion chamber 18 begins during the release of combustion products when their pressure decreases to the level of air pressure from an external source coming through the check valve 21. During movement and stop of the spool valve 20 after the end of the forward stroke, compressed air continues to flow before the start of the return stroke. into the chamber 18, displacing the remains of the combustion products and ensuring the duration of the purge process until, at the beginning of the return stroke, the slide valve 20 closes the passage sections From the exhaust channel.

 The purge of the chamber 18 of periodic combustion can be carried out by air, which is compressed by the piston 83 of the compressor 84, driven by the energy of the combustion products when moving the slide valve 20 during the forward stroke. It begins to be fed by combining the passage section a5 with the section a6, and also ends at the beginning of the return stroke of the slide valve 20. During the return stroke, the air entering the compressor 84 through the check valve 8 is compressed by the piston 83 due to the vacuum formed during its movement during the forward stroke. This air is directed through the check valve 21 into the chamber 18 to form a fuel-air mixture of the next thermodynamic cycle. When the piston 83 returns to its initial position, a vacuum forms after which the atmospheric air through the check valve 86 enters the volume of the compressor 84 to compress in the next thermodynamic cycle and purge the chamber 18 after the release of combustion products. As a result, the gas generator simultaneously performs the functions of a reciprocating compressor, the compressed air from which, along with the combustion products, is used to perform useful work in the power plant, as well as when blowing and forming the air-fuel mixture in the periodic combustion chamber 18 to ensure autonomous operation of the gas generator.

 At the end of the forward stroke of the slide valve 20, the combustion products are directed through the passage section C of the periodic combustion chamber 18 to the jet device 12 to generate jet pulses. The gas generator at the same time performs the functions of a heat engine - a pulsating jet gas generator and jet propulsion.

 The products of combustion of the re-enriched air-fuel mixture at the end of the direct stroke of the spool valve 20 through the passage section C and the exhaust channel b1 are sent to the detonation chamber 66 for the formation of supersonic jet jets, which are angled towards each other to the focal point 68 of the spherical part 67 of the detonation chamber 66 of combustion . The air compressed by the piston 83 of the compressor 84 when moving the spool valve 20 due to the energy of the combustion products, or compressed air from external sources, is fed through channel a2 through the jet nozzle to the same point 68 for the collision of the jet stream, causing a local increase in temperature and pressure and initiating self-oscillation process of detonation combustion with the formation of high-frequency detonation waves propagating in the opposite direction from the spherical part 67 of the chamber 66, and with high kinetic energy sculpt combustion products. This process continues until the supply of combustion products or air stops at the end of the forward stroke of each thermodynamic cycle and resumes at a predetermined frequency of ignition of the air-fuel mixture in the chamber 18 of periodic combustion. In this case, the gas generator simultaneously performs the functions of a heat engine - a pulsating jet gas generator and a jet propulsion device.

 The pulses of the jet of combustion products from the jet device 12 of the chamber 18 of the periodic combustion of the gas generator 91 (Fig. 32) are sent to the device 80 for connecting additional masses of the gas generator. In the process of sequential connection due to the kinetic energy of the pulses, they accelerate the mass of atmospheric air, combining it in the flow between the pulses of the jet stream in the calculated proportion with the combustion products. Before the flow is decelerated in the diffuser 75 of the attachment device 80, due to the calculated parameters of the attachment process, the combined mass is reduced below the speed of sound, as well as the composition of the gas mixture, which allows its use as a component of the air-fuel mixture, which reduces the amount of nitrogen oxides in the combustion products. At the outlet of the diffuser 75, a compressed working fluid is obtained and through the check valve 3 it is sent to the pneumatic accumulator 7 to accumulate to a design level, above which the ignition of the air-fuel mixture in the chamber 18 of periodic combustion of the gas generator 91 is stopped, and when the pressure drops below the design level, it is again ignited and continue the process. As a result, the gas generator simultaneously serves as a jet compressor, the gas mixture from the pneumatic accumulator 7 of which is sent through the channel a through the pneumatic valve 9 for use in the second thermodynamic circuit, and / or as a component of the air-fuel mixture of the chamber 18 for periodic combustion of the first thermodynamic circuit, and / or for the external consumption, and channel a7 is sent to the chamber 18 for periodic combustion of the gas generator 91 to ensure autonomous operation of the gas generator.

Claims (68)

 1. A method of converting energy in a power plant, in which the torque on the power shaft of the rotor of the jet engine is obtained due to jet propulsion created by the reactive mass of combustion products flowing out of at least one jet device, and to obtain the reactive mass, they spend energy on compression of atmospheric air in the compressor and its heating in the combustion chamber, characterized in that due to the increase in temperature during the combustion process in a closed volume of the periodic combustion chamber in each thermodynamic In the chemical cycle, the potential energy of the combustion products is increased several times, compared with the potential energy of the air-fuel mixture, which are then sent to the jet devices of a rotating nozzle apparatus of the ejector type, located at least at one level of the outer part of the impeller, at least one stage of the rotor of the jet-adaptive engine of the power plant, for converting the received potential energy into the kinetic energy of the pulse of a supersonic jet, expiring to it from the jet device into the device for attaching additional masses of this nozzle apparatus and creating in each thermodynamic cycle, following the gas mass of combustion products moving in this device at supersonic speed, a vacuum that is used to supply additional gas masses to the same device and carry out their process sequential connection between the pulses, in which these additional masses are accelerated by transferring to them part of the energy of the pulses of the jet combustion coils and receive the combined reactive mass creating reactive thrust and torque on the shaft, while proportionally to the increase in pressure during the combustion process and the magnitude of the additional mass addition coefficient m, the energy costs for compressing the air in the compressor and its heating in the combustion chamber are reduced.  2. The method according to p. 1, characterized in that to obtain the necessary moment on the rotopa shaft of the jet-adaptive engine, the reactive thrust force is controlled by changing the number and parameters of the inkjet devices with attachment devices, by connecting through separate channels to each device or to groups devices corresponding in their parameters to a given operating mode, periodic combustion chambers and sources of additional masses for changing the magnitude and speed of the combined reactive mass.  3. The method according to p. 1, characterized in that to obtain the necessary moment on the rotor shaft of the jet adaptive engine control the thrust force by changing the frequency of thermodynamic cycles in the periodic combustion chambers and, accordingly, the mass and thermodynamic characteristics of the combustion products supplied per unit time, parameters addition processes and addition coefficients of the additional masses m involved in the creation of the combined reactive mass of the devices to change the volume and velocity Inonii reaction mass, wherein the combustion process do not change the amount of fuel in the air-fuel mixture, and at steady state increase the degree of air compression, fuel mixture depleting.  4. The method according to any one of paragraphs. 1-3, characterized in that the moment on the rotor shaft of the jet adaptive engine is obtained due to the expiration of the combined reactive mass from the rotating nozzle apparatus of at least one stage of the rotor and the simultaneous action of the combined reactive mass from the fixed nozzle apparatus on the blades, at least at least one blade stage of the same rotor.  5. The method according to any one of paragraphs. 1-4, characterized in that at the same time as the combined reactive mass obtained in the process of sequential addition of additional masses, to create a moment on the power shaft of the jet adaptive engine, one also uses a reactive mass obtained in another way, for example, during stationary expiration of the working fluid from reactive nozzles or obtained in the process of parallel connection of additional masses due to their ejection by a stationary flowing jet.  6. The method according to any one of paragraphs. 1-5, characterized in that the air is compressed in the compressor of the dynamic principle of operation due to the part of the available kinetic energy of the combined reactive mass remaining after creating a moment on the shaft of the jet adaptive engine, this energy is utilized by directing the jet to act on the blades, at least , one turbine, the rotor of which is kinematically not connected with the power shaft and, converting into kinetic energy of its rotation, provide a compressor drive.  7. The method according to any one of paragraphs. 1-6, characterized in that the air is compressed in the compressor volumetric principle of operation due to part of the increase in potential energy of the combustion products obtained in the process of fuel combustion in a closed volume of the periodic combustion chamber, while due to the partial expansion of the combustion products inside the volume of the combustion chamber its spool valve and, acting on the compressor piston, compress the spring, as well as the air in the volume in front of the piston, and create a vacuum in the volume behind the moving piston for entry atmospheric air, and at the end of this stroke of the piston, combustion products are discharged from the combustion chamber, and compressed air is released from the compressor to expand them in jet devices, then the spool valve and compressor piston are returned to their original position due to the energy accumulated by the spring, and during the return the stroke of the piston compresses the incoming air, which is used to form the air-fuel mixture of the next thermodynamic cycle.  8. The method according to any one of paragraphs. 1-6, characterized in that the air is compressed in a jet compressor, forming a mixture of additional air masses with combustion products from the combustion chamber, due to the kinetic energy of which these additional masses are accelerated and combined in one stream, during braking of which a compressed gas mixture is obtained for use when expanded in jet devices and as a component of the air-fuel mixture with a proportion of oxidizing agent and combustion products, which provides fuel combustion and a decrease in the amount of nitrogen oxides in the products of combustion Nia periodic combustion chambers main thermodynamic loop power plant, as well as the combustion chamber of the jet compressor.  9. The method according to any one of paragraphs. 1-8, characterized in that in each thermodynamic cycle the combined reactive mass is obtained by using additional masses of energy from one pulse of the jet of combustion products from the periodic combustion chamber and the energy of at least one pulse of pre-compressed atmospheric air or other gases, which after a calculated period of time are directed after the combustion products to increase the temperature and potential energy of these gases before expansion rhenium and at the same time lowering the temperature of the flow path of the thermodynamic circuit.  10. The method according to any one of paragraphs. 1-9, characterized in that the energy from the combustion of fuel in the periodic combustion chambers of the main thermodynamic circuit is used, directing along an additional - second thermodynamic circuit, the channels of which are parallel to the channels of the main circuit, the working fluid from another source, such as atmospheric air, or compressed air , or other gases having a temperature close to ambient temperature, for contact with the heat transfer surface of the walls of thermally stressed structural elements through which e It is heated while cooling these walls, which act as a heater for the working fluid at constant pressure.  11. The method according to any one of paragraphs. 1-10, characterized in that the kinetic energy of the reactive mass flowing out of the jet devices of the jet adaptive engine and creating a vacuum at the inlet of the additional mass connecting devices is used to supply the working fluid to the second thermodynamic circuit, due to which the working fluid, for example atmospheric air enters this attachment device to form a united reactive mass, and during movement along the radial channels of the rotating rotor, it is compressed by centrifugal force.  12. The method according to any one of paragraphs. 1-11, characterized in that, depending on the magnitude of the coefficient of attachment in the process of sequential addition of additional masses, the temperature is reduced, as well as the flow rate of the combined reactive mass and the rotational speed of the rotor of the jet-adaptive engine at steady state to a design level at which they provide the necessary reduction thermal stress of the flow path and operability of the bearings of the power shaft without the use of forced lubrication system.  13. The method according to any one of paragraphs. 1-11, characterized in that the bearings of the power shaft are mounted on the shaft of the blade turbine, which is used to utilize the kinetic energy of the combined reactive mass remaining after creating the moment on the shaft of the jet adaptive engine, and these shafts are aligned coaxially inside each other and rotate into one side to reduce the estimated speed of rotation of the bearings in steady state by reducing the difference in speeds between their outer and inner rings.  14. The method according to any one of paragraphs. 1-13, characterized in that the part of the available kinetic energy of the combined reactive mass remaining after creating thrust by the rotating nozzle apparatus of the previous stage of the rotor of the jet adaptive engine is disposed of by deploying the jet in the guide apparatus and directing it to the blades of the next blade stage to obtain additional moment on shaft.  15. The method according to any one of paragraphs. 1-13, characterized in that the part of the available kinetic energy of the combined reactive mass remaining after creating a moment on the shaft of the jet adaptive engine is disposed of, while the jet acts on the rotor blades of the first stage of the biotic turbine, which rotate in the opposite direction and kinematically connect with the rotor shaft of the jet adaptive engine through a differential planetary gear with a gear ratio that provides a calculated reduction in the peripheral speed of the blades of the first stage of the birotative turbine, relative to the peripheral speed of the rotating nozzle apparatus of the jet adaptive engine, to increase the force of the jet on the blades of the turotative turbine and the moment on the rotor shaft of its first stage, and this moment is summed through the differential planetary gear with the moment created on the rotor shaft of the jet -adaptive engine, in addition, on the output shaft of the carrier of this planetary gear have at least a one-stage rotor of the second stage of the biotational turbine, rotating to the side, opposite to the rotation of the first stage, and the moment generated by the action of the jet on its blades is also summed up, combining all three power flows into one through a differential planetary gear and providing the optimal ratio of increasing the force of the jets on the blades of the steps of the biotic turbine with the efficiency of these stages, depending from their rotation speed, while the total power is transmitted to the consumer through one or several output shafts.  16. The method according to any one of paragraphs. 1-15, characterized in that the total power generated on the output shaft of the carrier of the differential planetary gear is transmitted to the consumer through a gearbox with a gear ratio that provides an additional increase in torque on the output shaft and a decrease in its rotation speed at steady state to the calculated value.  17. The method according to any one of paragraphs. 1-15, characterized in that the total power generated on the output shaft of the carrier of the differential planetary gear is transmitted through the central gear of the input shaft of the additional differential planetary gear and its satellites to the rotor of the first stage of the additional biotational turbine, and through the carrier shaft to the mounted on it the rotor of the second stage of this turbine, while due to the gear ratio reduce and synchronize the speed of rotation of the rotors and increase the torque on their shafts, and due to the remaining kinetic energy The combined reactive masses flowing out from the blades of the second stage of the previous birotative turbine and acting on the blades of both stages of the additional birotative turbine create an additional total moment on the shafts of its rotors, and to transmit power to the consumer, one is used as output shafts, for example, to drive air blades a screw, a single-row rotor fan, or both at the same time, a double-row rotor fan, while the kinetic energy of their rotation is converted into kinetic energy th jet, creating a jet propulsion of the power plant, as a mover.  18. The method according to any one of paragraphs. 1-17, characterized in that when the combined reactive mass expires from the last stage of the biotative turbine, for example, centrifugal, it is guided through the channels located inside the fan blades or fan fan, mounted on the output shaft of the carrier additional differential transmission, for the formation of reactive thrust, expiration from their peripheral part, and additional torque.  19. The method according to any one of paragraphs. 1-18, characterized in that the combined reactive mass, the kinetic energy of which was used to perform useful work, is used in the following thermodynamic cycles as additional masses, for which the exhaust channel of the power plant is connected to the input of the connection devices, forming a closed thermodynamic circuit in which under the action of rarefaction obtained due to the kinetic energy of the jets flowing from the jet devices into the additional mass attachment chambers that have worked in previous cycles the basics moving along the exhaust channel into the external environment enter the connection devices and form a reactive mass combined with the products of combustion of this cycle, and when the total mass of exhaust gases in the closed thermodynamic circuit increases due to the combustion products, the surplus is displaced into the external environment through the exhaust channel, the mass of which from the total combined reactive mass of the thermodynamic cycle, creating a moment on the power shaft, is a part equal to 1 / m, where m is the value of the coupling coefficient to masses.  20. The method according to any one of paragraphs. 1-19, characterized in that due to the kinetic energy of the jet, creating a vacuum at the entrance to the device for connecting additional masses, form a cyclically repeating circular motion of the exhaust gases in a closed thermodynamic circuit in which they are mechanically cleaned with a filter and / or neutralized catalytic converter to reduce the emission of toxic substances, while by repeating cycles of passage through them of exhaust gases improve the quality of cleaning and / or increase the efficiency exhaust gas neutralization efficiency.  21. The method according to any one of paragraphs. 1-20, characterized in that when using devices for connecting additional masses, blade stages of the rotor of the jet adaptive engine and / or blade turbines that perform useful work due to the kinetic energy of the reactive mass flowing from the jet devices, as well as using a closed thermodynamic circuit gradually reduce the speed of supersonic pulses of jet jets of combustion products to a design level that provides a reduction in the noise effect when exhaust gases are released into the atmosphere to regulatory requirements without additional external systems jamming.  22. The method according to any one of paragraphs. 1-21, characterized in that the power on the output shaft of the power plant is obtained through the combined use of a jet-adaptive engine and at least one engine of a different operating principle, for example an electric motor, and they are included in the work together or independently.  23. The method according to any one of paragraphs. 1-22, characterized in that the power on the output shaft of the power plant is obtained using compressed air, which is sent from the pneumatic accumulator through mechanical or pneumatic, along with the products of combustion, to receive an active jet flowing out during the sequential connection from the jet devices of the nozzle apparatus a device providing its supply to the critical section of the jet nozzles in a pulsed mode.  24. The method according to any one of paragraphs. 1-23, characterized in that the power of the jet-adaptive engine of the power plant is regulated by changing the frequency of the pulses of the jet, performing the function of the active in the process of sequential addition of additional masses by changing the frequency of the combustion cycles in the periodic combustion chambers and / or by changing the frequency of the pulse compressed air supply.  25. A method of converting energy in a power plant, in which a torque is generated on the power shaft of the machine engine by using the kinetic energy of the reactive mass flowing out of the jet device, and part of the available energy remaining after creating the moment on the power shaft is utilized, characterized in that for disposal, the outflow of the reactive mass is directed to the blades of at least one stage of the rotor of the blade turbine, which is kinematically not connected with the power shaft, and is continuously converted into a kin The rotational energy of the devices kinematically connected with this turbine and having an inertial mass, with the help of which it accumulates and, if necessary, is converted into electric energy and / or potential energy of the compressed gas using the energy received during the conversion and / or its accumulation with subsequent using, while using sensors control the permissible design limit of the speed of rotation of the inertial mass, above which increase the consumption of stored energy.  26. The method according to p. 25, characterized in that the accumulated inertial mass, recovered energy is used to increase power on the power shaft in excess of the power obtained from the energy of the reactive mass containing combustion products.  27. The method according to any one of paragraphs. 25 and 26, characterized in that the accumulated inertial mass, utilized energy is used to obtain power on the power shaft and / or to provide energy to external consumers to partially or completely replace the energy received from burning fuel, in which, by controlling a discrete process of burning fuel , at the same time reduce or completely stop its combustion and emission of combustion products into the atmosphere.  28. The method according to any one of paragraphs. 25-27, characterized in that when starting the power plant, the initial accumulation of kinetic energy by devices with inertial mass is carried out by rotating them using an electric motor due to external sources of electricity.  29. The method according to any one of paragraphs. 25-27, characterized in that when starting the power plant, the initial accumulation of kinetic energy by devices with inertial mass is carried out by rotating them due to the kinetic energy of the reactive mass from the nozzle apparatus, which is sent to the blades of the turbine rotor kinematically not connected with the power shaft, and convert into kinetic energy of rotation of the inertial mass of devices kinematically connected with the rotor.  30. The method according to any one of paragraphs. 25-29, characterized in that they use the compressor rotor, the mass of which is selected from the condition of simultaneously performing the functions of a device having an inertial mass that accumulates kinetic energy, and its discrete controlled conversion into potential energy of gases compressed in the same compressor, while compressed gases through a non-return valve, they are pumped into the pneumatic accumulator to the upper design pressure level, above which one pneumatic valve blocks the access of gases to the compressor, and through another the remains of compressed gas in the volume between the inlet of the pneumatic accumulator and the outlet of the compressor, the rotor of which then rotates idle without consuming the energy of the inertial mass for compression, until the pressure drops to the design level at which the supply of gases to the inlet is resumed compressor.  31. The method according to any one of paragraphs. 25-30, characterized in that they increase the speed of rotation of the compressor rotor relative to the speed of the rotary blade turbine due to the kinematic connection between them through a planetary gear, reducing the peripheral speed of the turbine blades relative to the speed of the reactive mass flowing from the previous rotor stage of the jet adaptive engine , after the formation of a moment on its shaft, and increase the force of its impact on these blades, and the compressor shaft and the shaft of the blade turbine are located one inside the other and rotate through anetarnuyu transmission in one direction, wherein a difference of rotation speeds of outer and inner rings of the bearing shaft of the compressor is reduced by the amount of blade turbine shaft rotation speed at which the fixed bearings.  32. The method according to any one of paragraphs. 25-31, characterized in that they use an electric generator, the mass of which is selected from the condition that it performs the functions of a device having an inertial mass for the accumulation of kinetic energy, which in the same generator when connected to it loads are converted into electric.  33. The method according to any one of paragraphs. 25-32, characterized in that at the beginning of the vehicle’s movement, the moment required to bring the power shaft of the rotor of the jet adaptive engine of the power plant from a stationary state into rotation is created using the discreteness of the processes of fuel combustion and the supply of the working fluid to the jet device, connecting to them at any given time the estimated number of periodic combustion chambers and other autonomous energy sources, including those generated due to the energy accumulated by the inertial mass, and supplying the required amount of working fluid with calculated thermodynamic characteristics for the formation of the total reactive mass, providing a given value of the moment on the power shaft, while due to the low inertia and the inverse dependence of the moment on the shaft on the rotational speed of the rotor of the jet adaptive engine, reduce the time required to accelerate vehicle after the start of movement.  34. The method according to any one of paragraphs. 25-33, characterized in that for a given reduction in speed or movement under the influence of external forces, the kinetic energy accumulated by the mass of the vehicle is converted through its mover into the kinetic energy of rotation of the rotor of the traction motor included in the generator mode and / or of the compressor rotor, which compresses the gases and is directed through the nozzle apparatus onto the turbine blades for conversion into kinetic energy of the inertial mass and its accumulation, and / or is compressed in the radial channels of the rotor by jet-adaptive th engine, and when it expires from its rotating nozzle apparatus, they act on the blades of a blade turbine to convert and store energy.  35. The method according to any one of paragraphs. 25-34, characterized in that the operation of the power plant in an environment with a pressure exceeding atmospheric, is provided due to the energy accumulated by the inertial mass, which is used to drive a compressor that creates a vacuum in the exhaust gas outlet region, while simultaneously compressing the exhaust gas in the exhaust channel , which is connected to the entrance to the device for connecting additional masses of the jet adaptive engine and form a closed thermodynamic circuit in which the exhaust gases used in previous cycles are used as additional masses, performing a cyclically repeated process of sequential connection at elevated pressure at the inlet of the connection device, to the reactive mass of the products of combustion of this cycle flowing out of the jet devices, and the outflow of the combined reaction mass into the region with reduced pressure, and for the emission of excess exhaust gases the exhaust channel is connected to the external environment through a non-return valve and bleeds part of the compressed gases through it if the pressure in the channel exceeds the pressure externally environment.  36. The method according to any one of paragraphs. 25-35, characterized in that when working underwater, the exhaust gases compressed in the exhaust channel of a closed thermodynamic circuit, due to part of the kinetic energy accumulated by the inertial mass, are at least partially vented through the non-return valve into the pneumatic accumulator and accumulate in it until the calculated pressure, and with a decrease in pressure overboard, it is used as a working fluid to perform useful work during their expansion with subsequent release into the external environment.  37. The method according to any one of paragraphs. 25-36, characterized in that when working underwater, part of the energy of the inertial mass is converted into electricity to create a moment on the power shaft using an electric motor, accumulate it in storage devices and / or carry out hydrolysis to partially replace organic fuel and compressed air with hydrogen and oxygen and the use of part of oxygen in life support systems.  38. The method according to any one of paragraphs. 25-37, characterized in that in a closed thermodynamic circuit due to part of the kinetic energy accumulated by the inertial mass, cyclically repeating circular motion of the exhaust gases is formed and, at an increased pressure in the exhaust channel, they are mechanically cleaned with a filter and / or neutralized by a catalytic converter for reduce emissions of toxic substances, while by repeating cycles of passage through them of exhaust gases improve the quality of their cleaning and / or increase the contact time reagents with a catalyst, which, along with increased pressure, increase the efficiency of neutralization.  39. The method according to any one of paragraphs. 25-38, characterized in that the atmospheric air is compressed in the compressor due to the energy accumulated by the inertial mass, then it is accumulated in the pneumatic accumulator, from which at the right time, directly or through the heat exchange device, it is sent to the jet nozzles of the jet adaptive engine, and expanding into nozzles, lower its temperature and direct it to cool the elements of the power plant and / or external objects, and then at least partially return it to the compressor for re-compression and re-direct the compressed air in the accumulator to form a closed refrigeration circuit, which, along with the development of "cold", is used to provide power to the power shaft without emission of exhaust gases into the outer environment.  40. The method according to any one of paragraphs. 25-39, characterized in that the compressed and low temperature air from the closed refrigeration circuit is used, for example, to form a fuel-air mixture or provide external consumers, and the consumed mass of air is replenished from the atmosphere, creating due to the kinetic energy of the jet formed by the expansion of compressed air from a pneumatic accumulator in jet nozzles, vacuum at the inlet of devices for connecting additional masses for the influx of atmospheric air, which is used as an additional but the mass to be joined in the process of joining, while creating a united reactive mass that increases the moment on the power shaft, utilize part of its kinetic energy remaining after creating the moment, and then direct consumers to use part of the “cold”, and / or to the input of additional devices masses of the next rotor stage of the jet adaptive engine, and / or to the compressor input.  41. The method according to any one of paragraphs. 25-40, characterized in that the air supplied to the input of the devices for connecting additional masses from the atmosphere, when periodically replenishing the amount of air consumed by external consumers from the refrigeration circuit, is cooled to the temperature at which the moisture contained in it during the expiration of the jets crystallize, and the crystals are captured and concentrated in the volume located before entering the compressor, and after the cessation of low-temperature air flow, ice crystals under the influence of heat and transmitted via the conductive elements of the thermodynamic circuit designs and / or under the action of elements specifically heated to melt, and the water formed collected in a container.  42. An energy conversion method in which the kinetic energy of a reactive mass flowing out of a jet device is used to generate torque on the rotor shaft of a jet engine, characterized in that at least two are used to produce reactive mass in a jet adaptive engine working fluids, different in their thermodynamic characteristics, and due to the main working fluid, which has a greater potential energy, form at least one jet device a jet, which is sent to an additional mass attachment device and used as an active jet in the process of adding additional masses, and another working fluid, with a lower potential energy than the main one, is directed to the input of the same device for attachment as additional masses and due to partial transfer of the kinetic energy of the active jet in the process of joining accelerates it, combining both working bodies in one stream to create a united reactive mass, and the magnitude and soon The combined reactive mass is controlled by changing the number and parameters of the inkjet devices and attachment devices involved in the process of its creation, by connecting the sources of the working fluid through separate channels and changing the thermodynamic characteristics of the working fluids supplied to each involved device or to groups of devices with design for this operating mode by parameters, as well as changing the parameters of the processes of joining additional masses, tuning the jet-adaptive engine to achieve optimal efficiency when developing the total torque in various operating modes, thereby adapting it to the conditions of multi-mode application.  43. The method according to p. 42, characterized in that the combined reactive mass obtained in the process of attaching additional masses flowing out of at least one additional mass attaching device of the fixed nozzle apparatus is directed to the blades of at least one rotor blade stage jet adaptive engine.  44. The method according to any one of paragraphs. 42 and 43, characterized in that the expiration obtained in the process of joining additional masses of the combined reactive mass is carried out from devices for connecting additional masses of the nozzle apparatus located at least at one level of the outer part of the impeller of at least one step of the jet rotor adaptive engine to create jet thrust and torque on the shaft, and the main working fluid is fed into the jet device of a rotating nozzle apparatus to create a jet stream, yayuschey function active during connection of additional masses at this stage radial channels.  45. The method according to any one of paragraphs. 42-44, characterized in that the moment on the shaft of the jet adaptive engine is obtained due to the simultaneous action of the combined reactive mass from the nozzle apparatus on the blades of at least one blade stage and the expiration of the combined reactive mass from the rotating nozzle apparatus one step of the same rotor of the jet adaptive engine.  46. The method according to any one of paragraphs. 42-45, characterized in that the additional moment on the shaft of the jet-adaptive engine with a multi-stage rotor is formed by directing a jet flowing from the blades or rotating nozzle apparatus of the previous stage, through the guide apparatus to the blades of the next blade stage of the rotor or to the input of devices for connecting additional masses steps with a rotating nozzle apparatus as additional masses.  47. The method according to any one of paragraphs. 42-46, characterized in that in order to increase the moment on the shaft the jet stream flowing from the previous stage is directed through the guide apparatus to the blades of the next rotor stage, and after the expiration from the blades is directed to the input of the additional mass attachment devices of the rotating nozzle fixed to this the same rotor stage following the blades in the direction of the jet, as additional masses.  48. The method according to any one of paragraphs. 42-47, characterized in that for the formation of jet jets used in the processes of attaching additional masses as active masses, jet devices of various operating principles are used, for example, electroreactive, jet nozzles, detonation combustion chambers, and the jet stream from these devices is sent directly to input device for attaching additional masses or through a radial channel.  49. The method according to any one of paragraphs. 42-48, characterized in that the jet jets used as active in the joining processes are formed in detonation combustion chambers in which the combustion products are directed to form jet jets flowing towards each other at the focal point of the spherical part of the detonation combustion chamber, and compressed air-fuel mixture is supplied to parallel channels, the jet of which is directed to the same point for the collision of the jets, causing a local increase in temperature and pressure and initiating self-oscillations an efficient process of detonation combustion with the formation of high-frequency detonation waves propagating in the opposite direction from the spherical part of the detonation combustion chamber, and with high kinetic energy dispersing the combustion products, the process lasts until the supply of combustion products or air-fuel mixture stops, and starts again when the supply is resumed.  50. The method according to any one of paragraphs. 42-49, characterized in that the main working fluid, which generates a stationary expiring jet stream through the jet device, is sent to an additional mass attachment device, the input of which is connected to the atmosphere or to another source of additional masses, which are ejected by this jet stream in the process of parallel connection, transferring part of the energy to them due to turbulization and mixing of flows in the device for adding additional masses.  51. The method according to any one of paragraphs. 42-50, characterized in that the potential energy of the main working fluid in the jet device is converted into the kinetic energy of the pulses of the jet stream, the expiration of which is sent to the device for attaching additional masses and create a vacuum in it, which is stored for a period of time necessary for successive flowing in each pulse of the jet stream of the estimated number of additional masses that accelerate and form a combined reactive mass in the process of sequential connection .  52. The method according to any one of paragraphs. 42-51, characterized in that the potential energy of the main working fluid in the jet device is converted into the kinetic energy of the pulses of the jet stream, which is sent to the device for attaching additional masses, and atmospheric air or other working fluid is supplied through a channel connected directly to the input of the same device body as additional masses and, increasing in the process of sequential addition of their kinetic energy due to the energy of the main working fluid, form a combined reactive mass at.  53. The method according to any one of paragraphs. 42-52, characterized in that to obtain the pulses of the jet stream, which acts as an active jet in the process of sequential addition of additional masses, at least two different working fluids with different thermodynamic characteristics are used, and pulses formed by the working fluid with less potential energy , used to pre-accelerate additional masses in order to reduce losses by reducing the difference in meeting speeds during their subsequent interaction with the mass of the main work which body having a greater kinetic energy, and its relative cost reduction energy and increasing the combined speed of the reaction mass.  54. The method according to any one of paragraphs. 42-53, characterized in that the potential energy of the main working fluid in the jet device is converted into the kinetic energy of the pulses of the jet, which acts as an active jet in the process of sequential addition of additional masses, and another working fluid with constant pressure and lower potential energy is sent to the same a device through an annular jet nozzle for the formation of a stationary expiring jet stream, the energy of which is used in the process of attaching additional masses, at the entrance of the same device between the pulses of the active jet, to create a constant vacuum at the entrance to the attachment device and preliminary acceleration of additional masses in order to reduce energy losses during their subsequent interaction with the mass of the main working fluid by reducing the speed difference.  55. The method according to any one of paragraphs. 42-54, characterized in that the process of attaching additional masses is carried out sequentially, using two connection devices at the same time, located one after the other, while the jet stream flowing out after the process of connecting additional masses from the first device performs the function of an ejection jet in the process of attaching additional masses in the second device, and at the same time as the momentum increases due to an increase in the combined reactive mass, the velocity of its outflow and the angular velocity c Ruino adaptive engine to the calculated level.  56. The method according to any one of paragraphs. 42-55, characterized in that in multi-mode applications, when changing the rotor speed, automatically, due to a change in centrifugal force, the critical section area of the jet nozzles of the rotating nozzle apparatus is changed, adjusting the jet adaptive engine to the flow rate of the main working fluid in accordance with the required value moment in a given mode, for example, when accelerating a vehicle during the start of movement, the greatest power on the shaft is required, therefore the nozzle cross-sectional area is maximum, and reduce it by moving the nozzle control element under the action of centrifugal force, which increases as the rotor speed rises, to the minimum cross-sectional area at steady state.  57. The method according to any one of paragraphs. 42-56, characterized in that after creating a moment on the shaft, the remaining part of the available kinetic energy of the reactive mass is used, controlling the direction of its expiration, to form traction applied to the attachment point of the jet adaptive engine.  58. The method according to any one of paragraphs. 42-57, characterized in that as the rotor of the jet adaptive engine using a vehicle propulsion device, for example, propeller blades or fans, or fan, or part of their blades, and the estimated speed of rotation of the blades is provided by changing the parameters of the connection process and design the amount of the total combined reactive mass and the rate of its expiration, while the kinetic energy remaining after creating the moment on the shaft is used to control the direction of expiration of this reactive mass to create additional reactive thrust to the thrust created by the propulsion device of the vehicle. 59. The method according to any one of paragraphs. 42-58, characterized in that the compressed working fluid with a temperature close to the ambient temperature is expanded in the jet nozzles and cooled, depending on the degree of compression to negative temperatures below -130 ^o C, while using a jet adaptive engine to create power on the shaft and performing the functions of the expander, and then in the process of attaching additional masses in the connection device, it is used to perform the functions of an air chiller with refrigerant - the main working fluid, cooling flax-attaching masses, moreover, lowering their temperature to the calculated one with the possibility of its regulation within the limits depending on changes in the quantity, range of thermodynamic characteristics of the main working fluid and coefficient of addition of additional masses m.  60. The method according to any one of paragraphs. 42-59, characterized in that when creating a moment on the shaft, the jet adaptive engine is simultaneously set to operate in pump mode to pump external gas masses due to the kinetic energy of the reactive mass flowing out from the jet devices and creating a vacuum at the inputs of the additional mass connecting devices, and during forced rotation of the power shaft - in the mode of a centrifugal compressor and jet generator to compress external gases in the radial channels of the rotor and convert their potential energy into reagent s nozzles into kinetic energy of the jet.  61. A method of converting energy in a gas generator to generate a working fluid, in which the pressure and available work of expanding the combustion products are increased in each thermodynamic cycle during the combustion of fuel in a closed volume of the periodic combustion chamber, characterized in that due to a part of the obtained increase in potential energy of the combustion products , with their partial expansion in the closed volume of the periodic combustion chamber, work is performed to move the spool valve from its original position, in which the spring acting on it is almost completely unclenched and the exhaust channel is closed along its axis by the calculated distance, during which it compresses the spring, accumulating energy to ensure the spool valve returns to its original position - reverse, and open passage sections for the release of combustion products, after which, under the action of a compressed spring, the valve is stopped and the return stroke begins, during which fuel is injected under pressure and compressed air is supplied, providing mixing of the components air-fuel mixture for the next thermodynamic cycle, which begins after the spool valve returns to its original position and ignites the air-fuel mixture, and the necessary thermodynamic characteristics and the amount of combustion products produced per unit time are obtained depending on the purpose and modes of use of the gas generator due to the set ignition frequency of the air-fuel mixture mixtures, changes in the pressure of compressed air for its formation, changes in the volume of the chamber periodically combustion during controlled filling of part of its internal volume with an incombustible mass, and regardless of which (s) of the above methods are used to change the parameters of the combustion products, a constant amount of fuel is provided in all thermodynamic cycles, as well as the estimated duration and amplitude of the pulses release, the values of which in this method of energy conversion do not depend on changes in the frequency of thermodynamic cycles.  62. The method according to p. 61, characterized in that due to the energy of the combustion products, when they are partially expanded, the slide valve is moved and a vacuum is created in the volume associated with its direct passage through the closed check valve with a passage section for fuel injection, and also with an open channel for supplying fuel from the fuel tank, from which the estimated amount of fuel flows into this volume under the action of the resulting vacuum, which is insulated at the beginning of the movement of the spool valve during its return stroke, blocking the channel for its supply, and then, due to the energy of the accumulated spring, create pressure in this volume, open the check valve under the action of pressure and displace the calculated amount of fuel through the passage section for its injection.  63. The method according to any one of paragraphs. 61 and 62, characterized in that during the release of the combustion products from the periodic combustion chamber with a decrease in their pressure to the level of air pressure intended for purging, they begin to supply it to the chamber and continue it during movement and stop of the spool valve after the end of the forward stroke, before the start of the return, and end during the return stroke, at the beginning of the movement of the spool valve after closing the exhaust channel.  64. The method according to any one of paragraphs. 61-63, characterized in that the periodic combustion chamber is purged with air, which is compressed by the compressor piston, driven by the energy of the combustion products during movement of the spool valve during the forward stroke, and the compression and supply of air into this chamber to form the following air-fuel mixture The thermodynamic cycle is produced during the reverse stroke by the same piston due to the energy accumulated by the spring.  65. The method according to any one of paragraphs. 61-64, characterized in that at the end of the direct stroke of the slide valve, the combustion products discharged from the periodic combustion chamber are sent to a jet device for generating pulses of a jet stream, while the gas generator simultaneously functions as a heat engine - a pulsating jet gas generator and a jet propulsion device.  66. The method according to any one of paragraphs. 61-65, characterized in that the products of combustion of the re-enriched air-fuel mixture at the end of the direct stroke of the slide valve through the exhaust channel are sent to the detonation combustion chamber to form supersonic jet jets, which are angled towards each other at the focal point of the spherical part of the detonation combustion chamber, and air compressed by the compressor piston when moving the slide valve due to the energy of the combustion products, or compressed air from external sources is supplied to the same point for collisions jets, causing a local increase in temperature and pressure and initiating a self-oscillating process of detonation combustion with the formation of high-frequency detonation waves propagating in the opposite direction from the spherical part of the chamber and with high kinetic energy dispersing the combustion products, and the process continues until the supply of combustion products or air to end of the forward stroke of each thermodynamic cycle and resumes with a given frequency of ignition of the fuel air mixture in the periodic combustion chamber, while the gas generator simultaneously performs the functions of a heat engine - a pulsating jet gas generator and a jet propulsion device.  67. The method according to any one of paragraphs. 61-66, characterized in that the pulses of the jet of combustion products from the jet device of the chamber of the periodic combustion of the gas generator are sent to the device for attaching additional masses of the gas generator, in which during the sequential connection due to their kinetic energy they accelerate the mass of atmospheric air, combining it in the flow between pulses in the calculated proportion with the combustion products, and before the flow deceleration in the diffuser of the device connecting additional masses due to the calculated pairs the connection process meters provide a decrease in the velocity of the mass being combined below the speed of sound and the composition of the gas mixture, which allows it to be used as a component of the air-fuel mixture, which reduces the amount of nitrogen oxides in the combustion products, and a compressed working fluid is obtained at the outlet of the diffuser and sent to the check valve air accumulator for accumulation up to the design level, above which the ignition of the air-fuel mixture in the periodic combustion chamber is stopped a, and when the pressure drops below the calculated level, it is again ignited and the process continues.  68. The method according to any one of paragraphs. 61-67, characterized in that the working fluid from the pneumatic accumulator through the channels through the pneumatic valves is sent for use in the second thermodynamic circuit of the power plant and / or as a component of the air-fuel mixture of the periodic combustion chamber of the first thermodynamic circuit of the power plant and / or the periodic combustion chamber of the gas generator, and / or for external consumption.

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