WO2017164773A1 - Dispositif à réaction avec combustion par détonation muni d'un registre à pendule - Google Patents

Dispositif à réaction avec combustion par détonation muni d'un registre à pendule Download PDF

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Publication number
WO2017164773A1
WO2017164773A1 PCT/RU2017/000073 RU2017000073W WO2017164773A1 WO 2017164773 A1 WO2017164773 A1 WO 2017164773A1 RU 2017000073 W RU2017000073 W RU 2017000073W WO 2017164773 A1 WO2017164773 A1 WO 2017164773A1
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Prior art keywords
detonation combustion
pendulum
air
detonation
combustion
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PCT/RU2017/000073
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English (en)
Russian (ru)
Inventor
Анатолий Михайлович КРИШТОП
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Анатолий Михайлович КРИШТОП
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Publication of WO2017164773A1 publication Critical patent/WO2017164773A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F02K7/06—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with combustion chambers having valves

Definitions

  • the group of inventions relates to the fields of energy, transport, mechanical engineering and engine building, and specifically to devices, installations, and assemblies in which the working fluid is used to create a supersonic reactive high-temperature plasma jet in the process of detonation combustion of a fuel-air mixture for universal and highly efficient use in various designs of devices and aggregates of detonation combustion using pendulum-sliding devices of reactive detonation combustion, n
  • valve pulsating detonation engines Disadvantages of valve pulsating detonation engines: the obligatory use of expensive materials of fireproof walls and valves, the low repetition rate of cycles associated with the difficulty of providing a given service life, at which the valves in such an engine must work with a high frequency (about 100 Hz) , the complexity of the design of synchronization of the valves, which are responsible for the supply of the fuel mixture, as well as directly by the detonation combustion cycles themselves.
  • pendulum-slide device of reactive detonation combustion (MSURDG)” and “method of functioning of the MSURDG” can also be conditionally attributed to the next principal version of the detonation combustion scheme - “pendulum-gate” scheme of detonation combustion, in which the detonation front combustion of the air-fuel mixture is initiated and moves in an uncooled ceramic combustion chamber with a high frequency of more than 100 Hz from one area to another under the action of a swinging pendulum ceramic gate with constant updating of the air-fuel mixture.
  • the prototype contains a PDG chamber, also containing a device for generating shock waves, made in the form of a jet accelerator and coaxially located solid streamlined body, mounted in a nozzle and having an axial and angular degree of freedom, the rear profiled part of which forms a nozzle with an external nozzle expansion, and the annular channel is connected to the node of gas generation products and is focused on the front profiled part of the solid streamlined body.
  • a device for generating shock waves made in the form of a jet accelerator and coaxially located solid streamlined body, mounted in a nozzle and having an axial and angular degree of freedom, the rear profiled part of which forms a nozzle with an external nozzle expansion, and the annular channel is connected to the node of gas generation products and is focused on the front profiled part of the solid streamlined body.
  • the disadvantages of the prototype device the difficulty of regulating or changing the mode of their operation while maintaining profitability in the conditions of ultrahigh operating temperature of a solid streamlined body fixed in the nozzle and having axial and angular degrees of freedom, the overall low efficiency due to the absence of a lockable (constant volume) at a time - the name of the beginning of the "detonation explosion" of the vapor of the working mixture and the lack of universality of application in various designs of reactive devices and detonation combustion units, for example p: rotary detonation aggregates, ramjet engines of different speed ranges, detonation air-jet engine hybrid units, as well as in the designs of detonation highly efficient fuel combustion units in power systems of various purposes and in different fields of application.
  • the objective of achieving the technical result to which the claimed group of inventions is directed is to create a detonation combustion device capable of very efficiently and fully burning a very poor air-fuel mixture with a significant and guaranteed coefficient of excess air in an uncooled ceramic combustion chamber, brought to "white heat" with with a wall temperature of 1300 - 1500 ° ⁇ , where under conditions of a lockable (constant volume) for the duration of the "detonation explosion" of the vapors of the air-fuel mixture, it is guaranteed very poor air-fuel mixture will burn completely and fully at an average degree of its preliminary (before the start of the work cycle) compression and at the same time capable of universally working in different variants of designs of detonation combustion devices and assemblies, for example: straight-line jet detonation combustion engines of different speed ranges, hybrid once-through jet detonation combustion engines of various speed ranges with variable or unchanged thrust vector, rotary detonation combustion engines, the shaft torque of which formed by reactive thrust located on the edges of the rotor of the pendulum-
  • a pendulum-slide device for reactive detonation combustion includes an air supply system using at least one source of pre-compressed air, a fuel supply system using at least one type of fuel and a detonation combustion system consisting of a dynamic gas generation chamber, a ceramic combustion chamber, with at least two separate detectors for starting the child’s process national combustion, working, at least, from the main fuel system, the outlet nozzle and the pendulum ceramic gate located inside the detonation combustion system, the axis of which has the ability to fix it in the middle position, to separate the detonation combustion system in a longitudinal section into two equal symmetrical unlocked areas in the idle mode, and the possibility of limited rotations to the extreme positions of the ceramic gate in the operating mode, to separate the detonation combustion system in cross-section into two alternately dynamically locked in antiphase regions of the detonation combustion system, one of which is open on the supply side of the
  • a pendulum-slide device for reactive detonation combustion includes an air supply system using at least one source of pre-compressed air, a fuel supply system using using at least one type of fuel and a detonation combustion system consisting of a dynamic gas generation chamber, a ceramic combustion chamber, with at least two separate process triggers detonation combustion, operating, as a minimum, from the main fuel system, an outlet nozzle containing water nozzles and a water supply system to water nozzles, and a pendulum ceramic gate located inside the detonation combustion system, the axis of which has the possibility of fixing it on average position, for dividing the detonation combustion system in the longitudinal section into two equal symmetrical unlocked regions in the idle mode, and the possibility of limited rotations to the extreme positions of the ceramic flange operating mode, for separating the detonation combustion system in longitudinal section into two alternately dynamically locked in antiphase regions
  • a pendulum-slide device for reactive detonation combustion includes an air supply system using at least one source of pre-compressed air, a fuel supply system using using at least one type of fuel and a detonation combustion system consisting of a dynamic gas generation chamber, a ceramic combustion chamber, with at least two separate process triggers detonation combustion, containing an additional fuel system, with a separate tank of additional flammable fuel, and having the ability to switch the operating mode from the additional and / or main fuel system, output nozzle and pendulum ceramic gate located inside the detonation combustion system, the axis of which has the possibility of fixing it in the middle position, for dividing the detonation combustion system in the longitudinal section into two equal symmetrical unlocked areas in the idle mode, and the possibility of limited rotations to the extreme positions of the ceramic gate in operating mode, for dividing the detonation combustion system in longitudinal section into two regions of the de
  • a pendulum-slide device for reactive detonation combustion includes an air supply system using at least one source of pre-compressed air, a fuel supply system using using at least one type of fuel and a detonation combustion system consisting of a dynamic gas generation chamber, a ceramic combustion chamber, with at least two separate process triggers detonation combustion, containing an additional fuel system, with a separate tank of additional flammable fuel, and having the ability to switch the operating mode from an additional and / or main fuel system, an output nozzle containing water nozzles and a water supply system to water nozzles, and a pendulum ceramic gate located inside the detonation combustion system, the axis of which has the ability to fix it in the middle position, to separate the detonation combustion system in the native section into two equal symmetrical unlocked areas in the idle mode, and the possibility of limited rotations to the extreme positions of the ceramic gate in the operating
  • Another design difference is that the movable pendulum ceramic gate operates with a minimum gap without friction between the end surfaces of the ceramic combustion chamber without seals.
  • a further difference in the design is that the longitudinal sectional shape of the detonation combustion system is profiled, and the pendulum ceramic gate is made asymmetric about its axis of rotation.
  • a further difference in the design is that the longitudinal sectional shape of the detonation combustion system is made non-profiled, and the pendulum ceramic gate is made symmetrical about its axis of rotation.
  • a further design difference is that the air supply system and the detonation combustion system contain a common decompressor consisting of a gate at the inlet of the air supply system and a gate at the outlet of the detonation combustion system.
  • the technical result is also achieved in the method of functioning of the pendulum-vane device for reactive detonation combustion (hereinafter referred to as MSURDG), which consists in the fact that at the time of starting the MSURDG, compressed air and fuel are supplied to the input of the MSNURDG detonation combustion system and initiate a detonation wave by one of the sides of the pendulum ceramic gate from the middle position, and in this case, the detonation combustion front of the air-fuel mixture is initiated and moves in an uncooled ceramic combustion chamber with at a high frequency (of the order of 100 Hz) alternately from one area of the ceramic combustion chamber to another under the action of a swinging pendulum ceramic gate with constant updating of the air-fuel mixture.
  • the invention is a new "pendulum-gate" scheme of detonation combustion.
  • the proposed unit of detonation combustion in the form of a hybrid straight-through variant a detonation combustion engine of a wide range from zero to transonic speeds with an unchanged thrust vector, characterized in that it includes at least one pendulum-vane reactive detonation combustion device that does not have the ability to change the thrust vector, combined an air supply system comprising subsonic air intake and air compressor devices driven by an electric and / or heat engine, as well as a system of gates and tight joints, Allowing to supply air from the air compressor and / or subsonic air intake directly to the inlet of the air supply system of the pendulum-vane device for reactive detonation combustion.
  • a detonation combustion unit in the form of a variant of a hybrid ramjet jet engine of detonation combustion of a wide range from zero to transonic speeds with a variable thrust vector, characterized in that it includes at least one pendulum-slide device for reactive detonation combustion, a combined air supply system containing subsonic air intake and air compressor devices a quarrel, driven by an electric and / or heat engine, as well as a system of gates and hermetic connections allowing to supply air from an air compressor and / or a subsonic air intake directly to the inlet of the air supply system of a pendulum-vane device for reactive detonation combustion, and also a device for changing the thrust vector of a pendulum-slide device for reactive detonation combustion.
  • a detonation combustion unit in the form of a variant of a hybrid ramjet engine of detonation combustion of a wide range from zero to supersonic speeds with an unchanged thrust vector, characterized in that it includes at least one pendulum-slide device for reactive detonation combustion, not capable of changing the thrust vector, combined air supply system, containing devices with a supersonic air intake, a subsonic air intake and an air compressor driven by an electric and / or heat engine, as well as a system of gates and tight connections that allow air to be supplied from the air compressor and / or subsonic air intake and / or from a supersonic air intake directly to the system inlet air supply of the pendulum-gate device of jet detonation combustion.
  • a detonation combustion unit in the form of a variant of a hybrid ramjet jet engine of detonation combustion of a wide range from zero to supersonic speeds with a variable thrust vector, characterized in that it includes at least , one pendulum-vane device for reactive detonation combustion, a combined air supply system containing devices of a supersonic air intake, subsonic air air intake and air compressor driven by an electric and / or heat engine, as well as a system of gates and airtight connections allowing air from the air compressor and / or subsonic air intake and / or from a supersonic air intake directly to the system inlet air supply of the pendulum-vane device for reactive detonation combustion, as well as a device for changing the thrust vector of the pendulum-vane device for reactive detonation combustion.
  • a detonation combustion unit in the form of a variant of a rotary detonation combustion engine, a torque on the shaft of which is formed by jet thrust located at the edges of the rotor of the pendulum-vane reactive detonation combustion devices , characterized in that it includes at least one rotor wheel, at the edges of which are located at least two pendulum-slide devices for reactive detonation combustion, with a common fuel system located outside and / or inside the rotor wheel of the rotary engine of the detonation combustion engine, and at the same time also includes at least one starter device, allowing to be able to achieve the initial operating speeds of the rotor wheel of the rotary engine of the detonation combustion engine .
  • a detonation combustion unit in the form of a variant of a hybrid air-reactive detonation combustion unit, characterized in that it includes a primary energy source in which at least one reversible is used an electric machine and one electric battery, a detonation combustion rotary engine, including at least one rotor wheel, at least two pendulum-vane wheels are located at its edges a device for reactive detonation combustion, which also contains blades of a propeller, in the zone of the air flow of which at least one is located that does not have the ability to change the thrust vector of a pendulum-slide device for reactive detonation combustion, the topic of air supply which is also associated with an additional air intake, with the ability to control the size and direction of the incoming air flow.
  • a detonation combustion unit in the form of a variant of a hybrid air-reactive detonation combustion unit, characterized in that it includes a primary energy source in which at least one reversible is used an electric machine and one electric battery, a detonation combustion rotary engine, including at least one rotor wheel, at least two pendulum-vane wheels are located at its edges a device for reactive detonation combustion, which also contains blades of a propeller, in the zone of the air flow of which at least one is located, equipped with a device for changing the thrust vector, a pendulum-vane device for reactive detonation combustion, the air supply system of which is also associated with additional air intake, with the ability to control the size and direction of the incoming air flow.
  • a detonation combustion unit in the form of a hybrid transport power unit of detonation combustion, characterized in that it includes a primary energy source in which at least one reversible electric machine and one an electric battery, a rotary engine of detonation combustion, including at least one rotor wheel, at the edges of which are located at least two swingarm of a detonation combustion system, which also contains propeller blades, in the airflow zone of which there is at least one that does not have the ability to change the thrust vector of a pendulum-vane reactive detonation combustion device, the air supply system of which It is also connected with an additional air intake, which has the ability to control the size and direction of the incoming air flow, and also includes an electromechanical transmission of the hybrid drive of a detonation combustion power unit on a solid and / or liquid and / or snow-ice surface.
  • the proposed unit of detonation combustion in the form of a hybrid transport detonation combustion power unit, characterized in that it includes a primary energy source, in which at least one reversible electric machine and one electric battery are used, a detonation combustion rotary engine including at least one rotor wheel, at the edges of which at least two pendulum-vane devices for reactive detonation combustion are located, which also contains propeller blades, in the air flow zone of which at least one is located a pendulum-vane device for reactive detonation combustion, which is connected with an additional air intake, which has the ability to control the size and direction of the incoming air flow, and also includes an electromechanical drive transmission the movement of the hybrid transport power unit of detonation combustion on a solid and / or liquid and / or snow-ice surface.
  • a detonation combustion unit in the form of a variant of a detonation combustion unit for burning fuel in energy systems, characterized in that it includes a compressed air supply system, a fuel combustion system containing at least one pendulum-slide device for reactive detonation combustion.
  • a detonation combustion unit in the form of a variant of a detonation combustion unit for highly efficient fuel combustion in energy systems, characterized in that it includes a compressed air supply system, a fuel combustion system containing at least one pendulum-slide device for reactive detonation combustion, the output nozzle of which contains an MHD generator.
  • a detonation combustion unit in the form of a variant of a detonation combustion unit for highly efficient fuel combustion in energy systems of high ecology, characterized in that it includes a compressed air supply system, an environmentally friendly system burning fuel, containing at least one pendulum-slide device for reactive detonation combustion, the output nozzle of which contains a device for cracking org matic and additional fuel ustroy- GUSTs feed gas phase recycled cracking organic fuel, in the main a new fuel supply system for the pendulum-slide device for reactive detonation combustion.
  • FIG. 1 The essence of the group of inventions is illustrated by the drawings of FIG. 1, FIG. 2, FIG. 3, FIG. 4, FIG. 5, FIG. 6, FIG. 7, FIG. 8 and FIG. 9.
  • Fig. 1 (a), (b), (c) shows a functional diagram of a variant of a pendulum-vane reactive detonation combustion device (hereinafter referred to as MBURDG), in which a movable pendulum ceramic gate operates, for example, with a minimum a gap without friction between the end surfaces of the ceramic combustion chamber without seals, the longitudinal sectional shape of the detonation combustion system is for example profiled, and the pendulum ceramic gate is made, for example, asymmetrical about its axis of rotation.
  • MBURDG pendulum-vane reactive detonation combustion device
  • FIG. 1 (a) shows the MSURDG scheme, in the initial state prior to the start of the working process, which contains a subsonic air intake of the air supply system 2, a fuel system with an output nozzle 1, a dynamic gas generation chamber 4, separated by a narrowing profile 3 into sectors (A 1, A 2, B 1, B 2), a ceramic combustion chamber 7 with sectors (C 1, C 2, D 1, D 2) and with two separate devices for starting the detonation combustion process 9 and 10 , the output nozzle 11 and the pendulum ceramic gate 12, rigidly mounted on its axis 5, connected to a starter device, for example, in the form of a direct current electric motor with rotor rotation limiters and a middle neutral lock (not shown in the drawing).
  • a starter device for example, in the form of a direct current electric motor with rotor rotation limiters and a middle neutral lock (not shown in the drawing).
  • FIG. 1 (b) shows a schematic of an MBMSDG, in the state of the beginning of the working process, when the starter device rotates the axis 5, on which the pendulum ceramic gate 12 is rigidly fixed to its extreme position towards a separate device for starting the detonation combustion process 10 for initiation detonation wave of detonation combustion of air-gas mixture.
  • FIG. 1 (c) shows a schematic of an MBMSDG, in a state of continuation of the working process, when the pendulum ceramic gate 12, under the action of the first detonation wave of detonation combustion of the air-fuel mixture, rotates to its opposite extreme position towards a separate device for starting the process of detonation national combustion 9 to initiate the next detonation wave of detonation combustion of the air-fuel mixture.
  • the air supply system Before the direct start of operation of the MSURDG, the air supply system generates pre-compressed air at the outlet of the air intake 2, and the supply system fuel with a fuel nozzle 1 forms a fuel-air mixture with a certain degree of its preliminary compression (before the start of the working cycle) at the entrance of a dynamic gas generation chamber 4 sectors (A 1, B 1), where gas generation products are formed in the narrowing region of profile 3 with increasing pressure sectors ( ⁇ 2, ⁇ 2), with a fixed middle position of the movable pendulum ceramic gate 12, which symmetrically detonates the detonation combustion system in the longitudinal section into two equal unlocked regions 6 with sectors ( ⁇ 2, ⁇ 1, ⁇ 2 ) and 8 sectors (B 2, D 1, D 2) in Scheme 1 (a) - idle mode.
  • a 1, B 1 gas generation products are formed in the narrowing region of profile 3 with increasing pressure sectors ( ⁇ 2, ⁇ 2), with a fixed middle position of the movable pendulum ceramic gate 12, which symmetrically detonates the detonation combustion system
  • the direct start of the operation of the MBSURDG begins when the starter device is turned, which, turning to one side, the movable pendulum ceramic gate 12 forms dynamically lockable antiphase regions of the detonation combustion system, and using the example of FIG. 1 (b) as the operating mode, the first during the movement of the air-fuel mixture, the dynamically locked region (A 1, B 1, A 2, C 1) of the detonation combustion system, which at the beginning of the movement of the air-fuel mixture forms its preliminary compression in the narrowing zone (A 1, B 1 ) dinam egg gas generation chamber 5 and additional compression of gas generation products when the flow is inhibited in the narrowing zone (A 2, C 1) with a maximum increase in temperature and pressure of gas generation products at the corresponding device for starting the process of detonation combustion 10 of the ceramic combustion chamber 7, which initiates a detonation wave, for example, in a detonation tube with an electric discharge of the required power for this, followed by a general “detonation explosion” of vapors of a working seam
  • a 1, B 1, B 2, D 1 the detonation combustion system with its own device for starting the detonation combustion process 9 and the “detonation explosion” process is repeated similarly to the above process in locked region (A 1, B 1, A 2, C 1) of the detonation combustion system in the diagram of Fig.
  • the detonation combustion process goes into self-oscillating mode with the subsequent disconnection of the starter device and devices for starting the detonation process combustion 9 and 10 upon reaching the “white-hot” mode of the ceramic combustion chamber 7, brought to a wall temperature of 1300 - 1500 ° C with the effect of ignition for the vapors of the working gas-air mixture, which makes it possible to very efficiently and fully burn a very poor working tailboat stuffy mixture with a significant and guaranteed coefficient of excess air.
  • the described embodiment of the MSURDG according to the scheme of FIG. 1 can be used in the designs of ramjet detonation jet engines for aircraft, as well as for the designs of rotary detonation engines whose rotors receive torque due to the reactive thrust of the pendulum-vane reactive detonation combustion devices located along the edges of the rotor of such an engine and the efficiency of such engines will be quite high during explosive (detonation) combustion - a speed of about 2000 m / s, in comparison normal combustion in which the combustion front has only a velocity of 20-40 m / sec.
  • the following MSURDG variant can be used, which differs from the variant according to FIG. 1 in that the detonation combustion process triggering devices contain an additional fuel system, with a separate tank of additional flammable fuel, and have the ability to switch the operating mode from the additional and / or main fuel system.
  • the operation algorithm of such a variant of the pendulum-vane device for reactive detonation combustion is similar to the above described embodiment according to the scheme of Fig.
  • the detonation combustion process start devices operate on flammable fuel, and when Lenia pressures to nominal, the device trigger detonation combustion perevodyat- camping on the base fuel.
  • the following MBMSDG variant can be used, which differs from the variant according to the scheme of FIG. 1 in that the output nozzle contains water nozzles and a system for supplying water to water nozzles.
  • the operation algorithm of such an MBRDG variant is similar to the above-described variant according to the scheme of Fig.
  • FIG. 2 shows a functional diagram of a detonation combustion unit, in the form of variants of a hybrid ramjet jet engine of detonation combustion of a wide range from zero to transonic speeds with an unchanged thrust vector of FIG. 2-a and with a variable thrust vector of FIG. 2 -B-.
  • Functional diagram of figure 2-a contains a combined air supply system containing a subsonic air intake device 14 and an air compressor 13, driven by an electric and / or heat engine (not shown), as well as a system of valves and tight connections 15, allowing to supply air from the air compressor and / or subsonic air intake directly to the inlet of the air supply system MSHURDG 16 with an unchanged thrust vector 17.
  • FIG. 2 -b- contains a combined system for air containing devices of a subsonic air intake 14 and an air compressor 13 driven by an electric and / or heat engine (not shown in the drawing), as well as a system of gates and airtight connections 15 that allow air to be supplied from the air compressor and / or a subsonic air intake directly to the inlet of the MSHURDG air supply system 16 with a variable thrust vector 17, the direction of which is regulated by means of the position change device 18 of the MSHURDG 16.
  • GPRDG hybrid direct-flow jet detonation combustion engine
  • a wide range from zero to transonic speeds with an unchanged thrust vector according to the scheme of FIG. 2-a is as follows.
  • the gate system and tight connections 15 are switched to the pre-compressed air supply mode at the air supply system MSHURDG 16 input only from the air compressor 13, after which pre-compressed air is supplied directly to the input of the air supply system MSHURDG 16, the operation algorithm of which is described according to the scheme of Fig. 1, and at the same time the thrust of the GPRDG will be regulated by about the compressor 13 and the operation mode of the MSHURDG 16.
  • the gate system and the tight joints 15 are switched to the mode of supplying the pre-compressed air to the input of the MSURDG air supply system 16 from the air compressor 13 and the subsonic air intake 14 and further to the mode only from the subsonic air intake 14 with an increase in the speed of the incoming air flow of the GPRDG with an unchanged thrust vector.
  • the GPRDGG includes an air compressor 13, a system of gates and pressurized joints 15 deactivates the subsonic air intake 14, and the regulation of the jet thrust of the MSHURDG 16 will be determined by the operation of its fuel system and the performance of the air compressor 13.
  • the air compressor 13 will again be turned on, and the system of gates and tight joints 15 it can be switched to the mode of supplying pre-compressed air to the inlet of the air supply system ⁇ 16 only from the air compressor 13, which will be taken out of operation as the speed of the incoming air flow at the inlet of the subsonic air intake 14 increases when it returns to small or zero angles of change traction vector by regulating the device for changing the position 18 of the MSURDG 16.
  • the above four MSWDG variants can be applied using at least one embodiment in the form of a hybrid combined-cycle internal combustion engine.
  • FIG. 3 shows a functional diagram of the detonation combustion unit, in the form of variants of a hybrid ramjet jet engine of detonation combustion of a wide range from zero to supersonic speeds with an unchanged thrust vector of FIG. 3-a and with a variable thrust vector of FIG. -B-.
  • 3-a contains a combined air supply system containing devices of a supersonic air intake 19, a subsonic air intake 14 and an air compressor 13, driven by an electric and / or heat engine (not shown), and a system of gates and hermetic connections 15, allowing to supply air from the air compressor 13 and / or subsonic air intake 14 and / or supersonic air intake 19 directly to the inlet of the air supply system MSHURDG 16 with unchanged traction 17.
  • H-B- comprises a combined air supply system comprising devices of a supersonic air intake 19, a subsonic air intake 14 and an air compressor 13, driven by an electric and / or heat engine (not shown), and a system of gates and tight joints 15, allowing to supply air from the air compressor and / or subsonic air intake and / or supersonic air intake 19 directly to the inlet of the air supply system MSHURDG 16 with changes emym thrust vector 17, the direction of which is regulated by means of po- repositioning device 18 MSHURDG 16.
  • the operation algorithm of the GPRDG variant a wide range from zero to supersonic speeds according to the scheme of Fig. 3, is similar to the GPRDG according to the scheme of Fig. 2 and differs only in that when the GPRDG is at subsonic speeds when only subsonic air inlet 14 is operating and, if necessary, transition to transonic speeds with the transition to supersonic speeds, an additional air compressor 13 is put into operation, and the system of gates and hermetic connections 15 puts the supersonic air intake 19 into operation and takes the subsonic zduhozabornik 14 and at least a necessary air compressor 13. The transition from supersonic velocity to dozvuko- stems speed in reverse.
  • FIG. 4 shows a functional diagram of a detonation combustion unit, in the form of variants of rotary detonation combustion engines (hereinafter referred to as RDDG), torque, on the shaft of which is formed by a jet propulsion rod, located at the edges of at least one RDDG rotor wheel with a common a fuel system located outside and / or inside the rotor wheel of the RDG.
  • RDDG rotary detonation combustion engines
  • FIG. 4 4-a, a functional diagram of an embodiment of a RDG with a common fuel system 21 with a fuel pipe 23 located outside the rotor wheel of the RDG is shown, and contains at least one rotor wheel with a flange 22 located on its axis a starter device 20, and also located at the edges of the rotor wheel, at least two MSHURDG 16.
  • FIG. 4 -b- shows a functional diagram of a variant of the RDG with a common fuel system 21 located inside the rotor wheel of the RDG and contains a rotor wheel with antsem 22 located on its axis star- Terni device 20, and located at the edges of the rotor wheel, at a minimum, two MSHURDG 16.
  • the starter device 20 untwists the rotor wheel with a flange 22, to which the load of the RDDG can be connected, and when the pressure of the pre-compressed air at the inlet of the air supply systems of all MSHURDG 16 reaches a sufficient value to start the working process, until the initial working speeds of rotation are reached, all MBURDG 16 are included in the operation and the operation algorithm of the MBURDG 16 is described above in accordance with the scheme of Fig. 1.
  • the torque on the RDDG shaft is formed by jet thrust located along the edges of the MSHURDG 16 rotor and can be controlled by changing the thrust and the number of working MSHURDG 16, as well as by changing the total number of RDDG rotor wheels included in the work.
  • the four MSWURDG variants described above can be used, and for the MSHURG version with water nozzles for the hybrid steam-gas rotary engine of detonation combustion, the versions can be used.
  • FIG. 5 presents a functional diagram of a detonation combustion unit, in the form of a variant of a hybrid air-reactive unit of detonation combustion rhenium (hereinafter referred to as GVRADG) with an unchanged vector that contains a primary energy source in which at least one reversible electric machine 25 and one electric accumulator 24 are used, a rotary detonation combustion engine including at least one rotor wheel 26 , at the edges of which there are at least two pendulum-vane devices for reactive detonation combustion 16, which also contains blades of a propeller 26, in the area of the air flow of which at least one pendulum-vane is located a jet detonation combustion system 16 that does not have the ability to change the thrust vector, the air supply system of which is also connected to an additional air intake 27, with the ability to control the size and direction of the incoming air flow, and in the drawing of FIG.
  • GVRADG hybrid air-reactive unit of detonation combustion rhenium
  • FIG. 5 is an additional air intake 27 , in the position of the maximum value from the direction of the incoming air stream of the propeller 26, and in the drawing of Fig. 5 -b- the additional air intake 27, in the position of the maximum value from the sum of the directions of the inlet yaschego airflow propeller 26 and counter to the direction of movement of the air flow.
  • the angle of attack of the blades of the propeller 26 is reduced to the minimum value and a reversible electric machine 25 in the motor mode powered by an electric battery 24 untwists the propeller 26, which is also the rotor wheel 26 of the rotary detonation combustion engine, at the edges of which at least two MSHURG 16, which are included in the work when the nominal pressure of the preliminary compressed air in the air chambers of the MSHURDG 16 is reached, the operation algorithm of which is described according to the scheme of Fig. 1.
  • the GVRADG increases the angle of attack of the propeller blades 26 and the thrust of the ⁇ 16 of the rotary engine of detonation combustion, which creates an air flow of vertical thrust of the ⁇ , in the area of which at least one more ⁇ 16 is installed as part of a separate ramjet engine with an additional air inlet 27, with the ability to control the size and direction of the incoming air flow, which is set to the position according to the scheme of figure 5 -a to start the MSH URG 16 as part of a separate ramjet engine of detonation combustion and the creation of horizontal thrust GVRADG, and with increasing horizontal speed GVRADG additional air intake 27 is moved to the position according to the scheme of figure 5-b-.
  • the GVRADG is turned off You MSHURG 16 as part of a separate ramjet engine of detonation combustion with an additional air intake 27 and adjust the angle of attack of the propeller blades 26 and the thrust of MSHURG 16 of the rotary engine of detonation combustion in order to reduce the vertical thrust of the HVRADG.
  • FIG. 6 shows a functional diagram of a detonation combustion unit, in the form of a variant of a hybrid air-reactive detonation combustion unit (hereinafter referred to as HVRADG) with a variable thrust vector, and this scheme differs from the described scheme of FIG. 5 only by the presence of a position change device 18 MSURDG 16 as part of a separate ramjet engine of detonation combustion, and the operation of this device is described by the operation of the GPRDG variant, a wide range from zero to transonic speeds, with a variable thrust vector according to the scheme of FIG. 2 - -.
  • HVRADG hybrid air-reactive detonation combustion unit
  • Both versions of the GVRADG with an unchanged thrust vector of Fig. 5 and with a variable thrust vector of Fig. 6 can be used for highly reliable helicopter designs, which even with the failure of all heat engines in the GVRADG are capable of making a soft, safe landing of the helicopter due to the hybrid drive of the carrier propellers from a reversible electric machine, and this distinguishes them from modern helicopters, making in such cases a hard, fatal landing.
  • the variant of the HVRADG with a variable thrust vector of FIG. 6 allows the creation of an ultra-fast and ultra-maneuverable design of a highly reliable helicopter.
  • Fig. 7 shows a functional diagram of a detonation combustion unit, in the form of a variant of a hybrid transport power unit of detonation combustion (hereinafter GTSADG) and this scheme differs from the described scheme of Fig. 5 only by the presence of an electromechanical transmission drive drive 28 GTSADG on solid and / or liquid and / or snow-ice surface and the GTSADH operation algorithm in the take-off and landing mode is similar to that described in the diagram of FIG. 5.
  • GTSADG hybrid transport power unit of detonation combustion
  • the GTSADG has an additional mode of movement on a solid and / or liquid and / or snow-ice surface, and for this it is enough to have only MBM 16 in operation with a minimum angle of attack of the blades of the screw 26 of the rotary engine of detonation combustion, the load of which will be a reversible electric machine 25 in generator mode to power electric motors of an electromechanical transmission of a 28 GTSADG motion drive on a solid and / or liquid and / or snow-ice surface.
  • the angle of attack of the blades of the propeller 26 may even have negative values, if necessary, have better adhesion to the surface.
  • FIG. 8 shows a functional diagram of a detonation combustion unit, in the form of a variant of a GTSADG with a variable thrust vector, and this diagram differs from the described scheme of Fig. 7 only by the presence of a position change device 18 MSHURDG 16 as part of a separate direct-flow detonation combustion engine and the operation of this device is described the operation of the GPRDG variant, a wide range from zero to near-sonic speeds, with a variable thrust vector according to the scheme of FIG. 2-b-.
  • Both versions of the GTSADG with an unchanged thrust vector of Fig. 7 and with a variable thrust vector of Fig. 8 can be used to create highly reliable structures of hybrid flying vehicles with the possibility of movement on a solid and / or liquid and / or snow-ice surface.
  • the design of a simple and inexpensive ultra-reliable flying car will help to radically solve the problem of traffic jams in megacities.
  • Fig.9 shows a functional diagram of a detonation combustion unit, in the form of a variant of a detonation combustion unit for burning fuel in energy systems according to the scheme of Fig.9-a, which contains a compressed air supply system 13, a fuel combustion system containing at least one MSURDG 16, as well as in the form of a detonation combustion unit for highly efficient fuel combustion in energy systems according to the scheme of FIG. 9 -b-, which contains a compressed air supply system 13, a fuel combustion system, containing at least one MSHURDG 16, the output nozzle of which contains an MHD generator 29 to increase the overall efficiency of the detonation combustion unit, and also according to the diagram of Fig.
  • the operation algorithm of the MSHURDG 16 in the detonation combustion units according to the schemes of Fig. 9 is similar to that described in the variant according to the scheme of Fig. 1 and the overall efficiency of the detonation combustion unit for burning fuel in energy systems can be increased by using the MHD generator, and environmental improvement can be achieved when using a device for cracking fossil fuels and an additional device for supplying a gas phase processed by cracking organic fuel in the main fuel supply system MSHURDG, for example, for pulverized coal-fired power plants without emissions of coal dust combustion products into the atmosphere.
  • the described group of inventions allows to obtain a high economic and environmental effect when used in transport and in the energy sector and covers several dozens of possible versions of detonation combustion units using pendulum-vane reactive detonation combustion devices.
  • a technical result is achieved, which consists in creating a detonation combustion device capable of very efficiently and fully burning a very poor air-fuel mixture with a significant and guaranteed coefficient of excess air in an uncooled ceramic combustion chamber brought to “white heat” with a wall temperature at 1300 - 1500 ° ⁇ , where under conditions of a lockable (constant volume) for the duration of the "detonation explosion" of air-fuel mixture vapors, it is guaranteed a very poor air-fuel mixture will be fully burned with an average degree of its preliminary (before the start of the working cycle) compression and at the same time capable of universally working in different designs of detonation combustion devices and units using pendulum-vane reactive detonation combustion devices, for example: hybrid ramjet detonation combustion engines of various speed ranges with variable or unchanged thrust vector, rotary detonation engines rhenia, the torque on the shaft of which is formed by jet thrust located on the edges of the rotor of the pendulum-vane devices
  • A.A. Vasiliev Features of the use of detonation in propulsion systems, p. 129, 141-145.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)

Abstract

Le groupe d'inventions concerne des dispositifs à réaction avec combustion par détonation. Le dispositif à réaction avec combustion par détonation est muni d'un registre à pendule disposé à l'intérieur du système de combustion par détonation et séparant le système en deux régions verrouillables tour à tour en phase opposée. Une des régions est ouverte du côté de l'alimentation en mélange air-carburant et est fermée en direction de la tuyère de sortie, et l'autre région en phase opposée est fermée du côté de l'alimentation en mélange air-carburant et est ouverte en direction de la tuyère de sortie. Le dispositif à réaction avec combustion par détonation comprend également un dispositif de démarrage qui permet de réorienter de façon limitée l'axe du registre à pendule céramique et de fixer ledit axe dans sa position médiane. L'invention vise à créer un dispositif à combustion par détonation capable de brûler un mélange très appauvri dans une chambre de combustion céramique non refroidie.
PCT/RU2017/000073 2016-03-22 2017-02-14 Dispositif à réaction avec combustion par détonation muni d'un registre à pendule WO2017164773A1 (fr)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113513429A (zh) * 2021-04-16 2021-10-19 中国人民解放军战略支援部队航天工程大学 能实现切向不稳定燃烧与连续旋转爆震的发动机及方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2124137C1 (ru) * 1997-03-20 1998-12-27 Тюриков Владимир Петрович Пульсирующий воздушно-реактивный двигатель с диссипационной камерой сгорания
GB2383612A (en) * 2001-12-03 2003-07-02 Nicholas Paul Robinson Jet engine
RU2561757C1 (ru) * 2014-01-14 2015-09-10 Николай Борисович Болотин Трехкомпонентный воздушно-реактивный двигатель

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2124137C1 (ru) * 1997-03-20 1998-12-27 Тюриков Владимир Петрович Пульсирующий воздушно-реактивный двигатель с диссипационной камерой сгорания
GB2383612A (en) * 2001-12-03 2003-07-02 Nicholas Paul Robinson Jet engine
RU2561757C1 (ru) * 2014-01-14 2015-09-10 Николай Борисович Болотин Трехкомпонентный воздушно-реактивный двигатель

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113513429A (zh) * 2021-04-16 2021-10-19 中国人民解放军战略支援部队航天工程大学 能实现切向不稳定燃烧与连续旋转爆震的发动机及方法
CN113513429B (zh) * 2021-04-16 2022-03-11 中国人民解放军战略支援部队航天工程大学 能实现切向不稳定燃烧与连续旋转爆震的发动机及方法

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