RU2641178C1 - Method of forming reactive forces of motion from air-dynamic part of jet and device for realization of this method - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: method is carried out by means of transverse extrusion of the required air mass for a combustion chamber from accelerating air column by jet from the channel formed by a blade rotor in a cylindrical body with subsequent replacement of accelerated air mass onto newly formed air mass with subsequent replacement of already cut part of reactive jet on column of air, which is carried out in the blind position of the channel by the lateral filling of the released space with air from the surrounding space through a screw window of a body in the period of its movement for getting into the jet from the other side. Lateral extrusion of the air mass from its volume is possible at the formation of a considerable internal pressure from the head of the jet to the counter-acting force of the resistance to acceleration of the free air mass in the channel, which requires the absence of the initial movement in the associated direction and its excess in the volume, which are allocated for the traction force increase.

EFFECT: increased efficiency of the air-jet engine by the steady supply of air mass under any operating conditions with a concomitant increase in traction force.

2 cl, 6 dwg

Description

Combustible fuel in the flowing air stream generates an equivalent opposite thermal pressure between the profiled engine passage channel, or the combustion chamber, and the resistance to the expiration of the expanded part of the air stream with combustion products during the passage of the smallest section, dividing it into the inlet and outlet, separated from the engine in the form of a jet stream with the opposite movement of the engine under the action of reactive forces of motion created by the separating heat pressure, or traction force balanced by otivleniem additional acceleration inlet air flow to the jet velocity while maintaining mass balance of the total flow stream, disregarding the fuel mass.

The influence of the inlet air flow on the generated thrust force limits the flight characteristics of the aircraft, which can be solved by various methods of forming the inlet air mass independent of the flight conditions with the creation of jet propulsion forces acceptable for different flight conditions, including start and finish sections with intermediate maneuvering.

Missile shells launched from a carrier aircraft or accelerator use the simplest way to generate reactive forces of a ramjet engine consisting of a combustion chamber between profiled sections of the through channel, which creates heat pressure with a constant fuel consumption in the air flow coming in with increasing flight speed under the influence of reactive thrust created by an increase in speed to the speed of a jet stream, limited by a nonlinear drop in drag forces acceleration with increasing speeds of the converted flows from thermal pressure in geometric progression with the same nonlinear increase in drag.

Disadvantages include the impossibility of using it on other types of aircraft in the presence of zero flight speed, the limitation of maneuverability by the possibility of reducing or interrupting the air intake when the flight vector changes, the uneconomic complexity of regulating the air mass for constant-flow fuel, or vice versa, with the variable air velocity, the heat load of the camera combustion and the output part of the jet engine with the cooling ability of the inlet air stream.

In a pulsating air-jet engine, consisting of a combustion chamber between the blocked intake valves and the elongated outlet part of the flow housing, the inlet air flow at ground-start conditions at zero speed enters through the open valves due to the pressure differential between atmospheric pressure and the rarefaction zone formed after leaving of a thermal flash of pressure of a jet stream through an elongated nozzle with fresh air blowing through the engine cavity for a new flash of thermal pressure, ar the impulsive movement of reactive forces that close the valves on the one hand with the development of traction, and on the other, the reactive outcome of the heated air mass with combustion products through an elongated nozzle with subsequent inertia.

With the development of speed, the counter-pressure of the air space is added to the atmospheric pressure with the displacement of the opening differential pressure in the direction of its increase without using an elongated nozzle while maintaining the pulse interaction of the interchangeable bodies.

The disadvantages include the frequency of occurrence of the thrust force, alternating with its preparation, the fragility of the valve grill, the limitation of maneuverability associated with a change in the linear interaction of the oncoming air pressure with the inlet and outlet sections of the engine.

A known scapular method of forming in the engine air flow cut-off from the air space the inlet air part with kinetic energy of the outlet reactive part by means of a turbocompressor mechanism delimited by combustion chambers.

The process of kinetic energy extraction from a jet stream is accompanied by an increased resistance of its formation from thermal separation pressure by the resistance of the turbine wheel blades associated with the engine with twisting the interscapular channels of the output stream with a decrease in traction force.

The process of formation of the inlet air flow consists in its separation from the interscapular air flow moving around the circumference under the action of centrifugal forces or inclined interaction with the blades with the influence of the oncoming air flow on its formation.

The disadvantages include:

- energy loss during its transformation by the blade elements of the turbocompressor mechanism between the converted sections of the flow stream;

- reducing the efficiency of the turbojet engine by the restrictive conditions for the flow of blades around the interacting stream;

- the concentration of thermal loads on the turbine blades under the action of centrifugal forces with the need to form an inlet air stream of increased volume for cooling.

There is a method of forming the inlet air mass of a Comprex type supercharged piston engine by alternately compressing the air mass in channels fed by the rotor mechanism, converted by end-cap windows into through, one-sided or two-sided closed, previously filled with air from the surrounding space by ejector replacement of exhaust gases in the through position of the channel , under the residual pressure of the exhaust gases with a blocked bottom channel with subsequent expansion due to the occurrence of elastic forces, inter acting without mixing gases through the approaching windows into the atmosphere and bypassing the rotation gaps and cross-sections adapted to each other, through pipelines to the engine cylinders.

The use of a rotary pressurization of a piston engine as a supercharger of the jet engine air inlet is not feasible due to the fundamental differences in their operation, where in the case of a piston engine it is possible to compress the air mass in the channels between the overlap and thermal pressure after it has been worked by the piston stroke, and in the case of a jet engine, compression exhausted by acceleration of air mass gases, focusing on the overlapping of the output section associated with the engine, deprives the possibility of the formation of reactive forces of heat pressure in confined space.

The known principle of a shot and intermittent change of charge from a magazine, including a drum type, with an AK-47 pulse weapon or other similar weapon, including a cyclical change of the barrel with the residual pressure of the powder gases during the acceleration of the bullet in the barrel channel with the achievement of the powder gases of the lateral drive outlet piston engine charge change with overcoming the opposing force of the return spring.

The use of a jet engine is counteracted by its own supply of charge and a separating body like a rocket engine, the reciprocating movement of the mechanical parts of the shutter and the supply of cartridges from the magazine with a break for the pulsed development of the reactive forces of movement in the form of recoil and departure of the bullet, the fragility of the mechanical interaction of parts and moving solid bodies in the form of a bullet in the barrel, a piston in the sleeve of a recharge machine, cartridges in a store.

The objective of the invention is the efficiency, efficiency and all-round air jet engine.

The problem is solved by the formation of reactive motion forces by thermal expansion of the inlet air flow with balancing the generating pressure by the resistance of the engine with the formation of traction force and resistance to acceleration of the ejected expanded inlet air flow, the oxygen of which is converted by the fuel into combustion products with the formation of a uniformly-flowing jet by lateral extrusion of opposing forces of the inlet air mass from its array inserted into the jet stream instead of the current part in the period of inertial resistance to acceleration forces with an associated increase in traction balancing force to resist the separation of the output stream from the heat pressure of the input stream, replaced and renewed as the resistance forces are accelerated by replacing the array with the newly created array during the round-trip of the jet stream as part of their endless chain by transverse and successive replacement of the space released under the ceiling with a growing array of space by the current part of the displaced jet of air mass from the surrounding space with an endless resumption of the process of transverse extrusion of the inlet air mass from the air-dynamic part of the jet stream with the formation of heat pressure in it when the combustion chamber intersects with the formation of a thrust force increased by the dynamic resistance of its air part formed by the inserted air mass with an associated increase traction forces with looped repetition.

The device for implementing the method according to claim 1, comprises a rotor ring of interscapular channels in a one-sided closed rotation housing with the possibility of alternatingly extending the output channel of the combustion chamber, or generator, a source of thermal formation of air-reactive driving forces, ringed by the input channel and side outlet, through the end window in the case located between the window of the remaining channels, encircling the housing between the inlet and outlet sections of the extension part of the channels.

The blades or partitions of the rotor dividing the through annular cavity between the housing into the channels are the blades of a screw propeller folded and fixed with long edges to the rotor and do not create traction or lifting force in contrast to them, but counteract the pressure of the jet at the moment of its intersection and lateral bending from the longitudinal dynamic processes between the variable pressure of the interacting masses acting between them, which is achieved by changing the adjacent sides of the blade with the corresponding extension of the screw hub and a reduced diameter, focusing their direction of free expansion in the allotted corridor of action within the channel to create traction or lifting force with the associated formation of the air intake for the combustion chamber of a jet engine, or vice versa.

Practically constructively, the problem is solved by using Comprex type pressurization as a source of formation of the jet engine air inlet mass by changing the redistribution of windows from the end parts of the body over its entire surface with the complete closure of one end face of the body, except for one connected to the output channel of the jet engine, and with full opening of all windows on the opposite end side of the case with the addition of two windows on the side of the case, one of which is located between the end CNAM connected to the inlet of the jet engine, and the second obliquely encircles the housing on the opposite side between the end windows.

Almost dynamically, the problem is solved by replacing the exhaust channel’s hard overlap with an inertial resistance force to the pressure of the exhaust gas by an air mass preformed under closed end windows, coming through the inclined side window from the surrounding space after the exhaust exhaust gas is exhausted into the circumferential recovery period of the persistent air mass, or its mass, with subsequent entry under the direct action of thermal pressure formed from the air mass squeezed out through the lateral CCW between the end windows through channel opposing longitudinal dynamic air jet forces.

Fundamentally, the solution of the problem is like the operation of an automatic weapon with the replacement of a bullet by an air mass, the discharge from which, and not from subsequent charge gases, is carried out during the action of a jet pulse, forms a new charge without using an intermediate piston mechanism using on-board fuel followed by a “shot” replaced air mass after practicing the resistance forces to acceleration of the previous one by drum change of a part of the barrel without changing the lateral exhaust of an external or own drive.

The addition of side windows, in contrast to the continuous cylindrical surface of the Kompreks housing, activates centrifugal forces, which from the side of the helical window with the air mass entering the interchannel space form opposing centrifugal forces, which tend to decrease the air mass density, which are compensated by the quenching of kinetic energy transversely the incoming air flow and the timely departure of the channel from the window under a cylindrical ceiling, and from the side of the selection window, centrifugal forces add input air flow.

In contrast to the reciprocating movement of the exhaust gases in the channel from its interaction through the air mass with a rigid overlap, a dictating channel of equal cross section, a unidirectional pulsating stream requires an equal section in order to concentrate the longitudinal-dynamic processes in the output stream with increasing pressure and associated formation torque like a turbine, which eliminates the dependence on an external drive.

The lengthening of the boost channels of the Comprex type of the piston engine causes the same exhaust gas energy released from the cylinder to compress a larger volume of air with a lower degree of pressure, because of which, when the intake air enters the cylinders, its mass decreases with the formation of excess volume, then compression with a jet stream of a column or an array of air of greater elongation leads to an increase in resistance to acceleration with an increase in the degree of pressure with an adjustable bypass section by selection of the input stream, and is unnecessary I air mass in the compression process serves to increase traction with reduced rotor speed at a frequency inversely related to the duration of the reactive pulse of each elongated channel capacity increased.

If in a ramjet engine, the jet forces are generated by the engine in the current stream, the speed of which grows together with the engine speed in airspace, then in the combustion chamber of the proposed engine variant, the reactive forces are formed from the input stable air stream formed by extrusion from the current with constant acceleration jet stream, which increases the efficiency and stability of the generated reactive thrust with optimal engine sizes.

The transverse-circumferential intake of air mass from the surrounding space through the channels of the rotor mechanism through the inclined window of the cylindrical body under the influence of the kinetic energy of the displaced parts of the jet stream does not change significantly at different positions to the direction of flight or the oncoming air flow, which will allow a wide variation of the thrust vector changes in the ramjet vector with a decrease or cessation of the oncoming air flow into the inlet section of the engine with the possibility of tipping over the flow during a turn, while in the proposed embodiment, when the opposite heat pressure forces are equal, the balancing force of the current flow does not change its position due to the ring selection of the incoming air mass from the jet created by it, and not from the oncoming air flow.

Due to the need to maintain tightness between the channels in the cavity of their rotation, it is unrealistic to use an internal protrusion from the side window to redirect part of the current air-dynamic part of the jet stream to the combustion chamber, and to prevent backward suction of the air mass from the bypass channel after the transfer of pressure forces in the stream in kinetic energy, the option of using bypass valves similar to PuVRD is prevented by the timely withdrawal of the channel from the outlet, which also agrees with the previous Incoming tvrascheniem therein accelerating jet to the combustion products.

Cutting off a jet stream with air mass by the location of the inlet section of the outlet channel at the outlet of the extension channel with a partial overlap of its passage channel transfers the critical section from the combustion chamber with the extension of its boundaries to the entire length of the outlet channel with large leaks through rotation gaps, which is closed by the counteraction of heat pressure forces through the channel , leading to the inoperability of the device, whereas when taking the air mass under pressure of any value, but without blocking the output section, it is reactive th jet, the flow in the bypass channel overcomes the resistance to thermal pressure by pouring into it due to the reduced resistance to the flow of the jet in the output channel of an equal cross-sectional area by selection of the opposing pressure, as well as the inertia of the initially generated bypass stream from the air part of the jet.

In a turbojet engine, the inlet air stream is generated by the jet stream by extracting part of the kinetic energy from the turbine with the transmission of torque to the compressor compressor wheels to form combustion chambers from it, blocking the duct part of the ring section engine, reactive driving forces with ring energy transfer through the turbocompressor mechanism with decreasing traction forces with restrictions, while in the proposed case, the jet stream squeezes the air mass from its mass siva in the outlet channel with an associated increase in traction and without restrictions on maneuverability by closed reverse flow into the combustion chamber with the possibility of associated external cooling, and not by excessive exhaustion of the air mass by a turbocharger to cool the combustion chamber.

If the increase in the combustion chambers is dictated by the overlap of the annular flow part formed by the zone of the most efficient interaction of the blades of the turbocompressor mechanism with the driven flow with an associated increase in power, then in the proposed case, an increase in the combustion chambers with the reactive forces that form them is associated with an increase in power with a concomitant peripheral increase in the channels with sectional their separation of the work done by the rotor mechanism case by repeating the side windows through the end windows with cam combustion ramie, wherein at separability turbojet combustor using only part of the total air flow formed bladed compressor wheel, whereas the combustion chamber in the present case uses the entire input bleed air from the pressure across the jet.

After the turbine selects the kinetic energy of the jet for the inlet air stream, it acquires the helical component of the stream with a slowing down of the vertical component, which determines the traction force with increased thermal pressure by closed resistance, while the interaction of the jet with the air mass is straightforward until it acquires a uniform speed, renewed by parallel replacement by scapular the channels of the rotor mechanism with the formation of a hollow cylindrical flow composed of withdrawn parts of a jet stream in a helical filling order.

The thermal load of the rotor rotor blades is optimized by alternately interacting with the exhaust gases of the combustion chamber and the inlet air mass from the surrounding space in comparison with the constant operation of the turbine in the outlet stream of the increased temperature combustion chamber when the compressor wheels are in air, relatively cold air mass, the temperature equalization of which to a general average affects the durability of the proposed engine.

It is possible to increase the pressure of the inlet air flow by premature withdrawal of the accelerating air mass or column of air in the channel of the rotor mechanism from the pressure of the jet of heat pressure until the resistance to acceleration is fully developed when they decrease geometrically depending on the increase in speed with the same increase in traction force in the same dependence at a lower speed of the output jet stream by increasing the rotational speed of the rotor mechanism or a large number of channels with a constant frequency o borot, as well as an increase in the length with a large run of the transverse interscapular air flow, the formation of which with a decrease in the speed of the cut-off parts of the jet stream is compensated by an increase in the helical window, while an increase in the pressure of the inlet air flow by the turbocompressor apparatus is achieved by increasing the compressor wheels and turbines with a decrease in the efficiency of the formation of traction .

The rotation of the thrust vector in flight creates a region of reduced pressure in front of the compressor with backward flow of the surrounding air space of the exhaust stream after the turbine, which leads to a decrease in the air intake into the combustion chamber with the removal of less torque by the turbine and a decrease in pressure drop between the blades, whereas in the absence of a turbocompressor mechanism with direct selection of the input mass from the jet stream, a change in the oncoming air flow does not affect the created e traction transverse wall of its air space and additional free jet expiration resistance increases thrust force is applicable, for example, quenching the landing speed of the aircraft with a smaller band path than during takeoff without using brake systems or in VTOL.

The method of generating reactive motion forces from the air-dynamic part of the jet stream is also applicable to other similar structures, for example, with the external location of the rotor around a cylindrical body with a bypass channel or a conical body and a rotor with channels of variable cross section while maintaining an equal passage area without transverse expansion, acting in the corridor of the expiration of interacting bodies with corresponding changes in design to highlight certain advantages in flight with an aircraft including, in particular maneuverability, to the detriment of others.

Manipulations and combinations in the form of increasing or decreasing the number of partitions of the rotor channels with the intersection of the jet at the same time more or less with the same or the opposite number of intersection of the outlet window, adjusting the slope, position, throughput sections increase the engine efficiency, which, in principle, is known from existing technology, for example, adjustable ignition, clearance in the valves of reciprocating engines, variable nozzle, screw pitch, etc., which are applicable in the proposed embodiment.

Accompanying drawings

FIG. 1 - scan with the principle of formation of reactive forces of motion from the air-dynamic part of the jet created by them; FIG. 2, 3, 4, 5 - engine in four projections; FIG. 6 is a perspective view in general with screw channels with associated external cooling parallel to the axis of rotation of the combustion chamber.

The parallel channels 1 are formed by the blades 2 of the rotor mechanism 3 in a one-sided closed cylindrical housing 4, part of which through the gas pipe 5, the end window 6 of the closed side and the combustion chamber 7 form a through annular cavity closing in the middle part of the through channels 1 through the side window 8 located on the cylindrical part of the housing 4, and the rest of the channels 1 under the closed side of the housing 4 form a flow cavity between the open side of the housing 4 and the side screw window 9 encircling the cylindrical surface s body 4 between the inlet and outlet sections looped channels 1 arranged to the combustion chamber 7 to form a torque rotary mechanism 3.

The inlet air stream 10 with fuel forms reactive forces in the combustion chamber 7 with heat pressure to form a thrust balancing jet stream 11, consisting of an expanded inlet air mass 10 with combustion products, causing non-mixing pressure on the column or mass of air mass 12 in the interscapular channel 1 with the formation of the air part of the jet 13 and the pressure on the forming channels 1 of the blade 2 of the rotor 3, causing a torque with the formation of a transversely replacing interscapular air flow .

The pressure of the compressed air array 12 in the air of the jet 13 extends along it, causing an increase in resistance to the formation of the jet 11 from heat pressure with increasing traction, and across it with the release of air mass through the side window 8 with the formation of the inlet air flow 10 s reverse flow through the gas pipeline 5 into the combustion chamber 7.

The centrifugal force of the circular motion of the air mass with channel 1 adds an ejection force to the force created by the inertial resistance of the array 12 to acceleration without affecting this acceleration from the pressure of the jet 11 extinguished by the cylindrical body 4, forming a common fixed wall of the channels 1.

After the conversion of the internal pressure energy into kinetic flow, the lateral air mass withdrawal ends with the passage of the channel 1, which extends the engine output channel, to the end overlap of the housing 4 with the beginning of the formation of the closed part of the channel while leaving it from the side window 8 and the jet 11 with subsequent contact with the side screw window 9, starting from the end overlap of channel 1.

The clipped part 13 of the jet stream 11 with accelerated array 12, which is inertial from the acceleration obtained earlier, leaves a rarefied cavity under the end overlap of channel 1, where air 14 flows from the surrounding space through the lateral screw window 9 under the influence of pressure difference to obtain kinetic energy of movement around the circle from rotor 3, and the action of the vacuum also extends along the channel, suppressed on one side by overlapping, on the other hand, by slowing the outgoing cut-off part 13 of the composite jet 11 .

Next, the rotor 2 with blades 2 shifts the axial channel 1 around the circumference of the cylindrical body 4 with closing and closing part of the screw window 9 at the level of the previously closed vacuum part of the channel and opening the next part of the screw window 9 at the level of the newly formed vacuum cavity between the layer of previously introduced air and the end face of the outgoing cut-off part 13 of the jet stream 11, which is transversely filled by air 14 from the surrounding space with continued braking of the outgoing part 13 of the stream, like the previous mu process, and at the same time, the rotor 3 introduces the next channel 1 into the place of the displaced channel 1 with the jet air 11 and the side window 8 of the intake air mass withdrawn from under the action of the jet and so on, which maintains the constancy of the incoming 14 preparatory air flow to create an array 12 transverse interscapular air flow and extruding inlet air flow 10 from the replaceable air masses 12 for the combustion engine of a jet engine.

Further advancement of the channel 1 along the inner cylindrical surface of the housing 4 opens new sections of the screw window 9 with the previous ones closed at the level of the newly formed vacuum cavity with its retracting effect on the atmospheric air 14 and on the cut-off part of the jet stream leaving the channel 1, which causes a slowdown of the transversely entering and outgoing waste streams with a decrease in the pitch of the helical window 9, which have a negative impact on the further efficiency of metabolic processes with a resulting smaller increase in additional silt traction.

After the cut-off part 13 of the jet stream 11 has expired from the channel with its complete filling with a stationary air mass or array 12, the channel is removed from the end face 4 and introduced under the jet stream 11 from the same chamber 7, from which it came out or into another with a sector configuration sequential passage through them, depending on their number, around the circumference of one rotary mechanism of a jet engine with the possibility of both separate formation of the inlet air stream, and branching one air stream n and all the cameras.

Used sources

1. The Internet.

2. Novikov V.N. Fundamentals of the design and construction of aircraft. 1991, p. 158 and others.

3. Julius Mackerle (J. Matskerle). Modern economical car. 1987, p. 175.

Claims (2)

1. The method of generating reactive motion forces from the air-dynamic part of the jet stream, including thermal expansion of the inlet air stream with balancing the generating pressure by the engine resistance with the formation of traction and resistance to acceleration at the output of the expanded inlet stream, the air component of which is converted by the fuel into combustion components to form uniformly-flowing jet stream by lateral extrusion of the inlet air mass from its array inserted into the jet stream instead of the current part, during the period of inertial resistance to acceleration forces with an associated increase in traction balancing resistance to separation of the output stream from the heat pressure of the input stream, replaced and renewed as the resistance forces are accelerated by replacing the array with the newly created array during the bypass of the jet stream as part of their endless chains by transverse and displaceable substitution after being freed under the overlap with a growing array of space, inertia expiring frequently displaced jet stream of the air mass from the surrounding space with an endless renewal of the process of transverse extrusion of the inlet air mass from the air-dynamic part of the jet stream with the formation of heat pressure in it when the combustion chamber intersects with the formation of a thrust force increased by the resistance of its air part formed by the inserted air mass with an associated increase in traction with a looped repetition. 2. The device for implementing the method according to claim 1, includes a rotary ring of interscapular channels in a one-sided closed rotation housing with the possibility of alternating extension through the window in the housing of the output channel of the generator for generating air-reactive motion forces, ringed by the input channel and the lateral outlet located between the window of the remaining channels, the enclosing body between the inlet and outlet sections of the extension part of the channels.

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