CN117145632A - Kerosene/liquid methane external parallel turbine-based rotary detonation engine - Google Patents

Abstract

The invention provides a kerosene/liquid methane external parallel turbine-based rotary detonation engine, which comprises an outer shell (611), a mixed pressure type air inlet channel (1), an adjustable external air inlet channel (2), a cooling system (3), an air entraining valve (4), a turbine engine (5) and a rotary detonation engine (6). Also provides a working method thereof. The invention can fully utilize the advantages of the detonation engine and the turbine engine, can meet the wide-speed-range flight of 0-6Ma, and has great significance for realizing the high-speed remote flight of the near space aircraft, solving the problems of thrust trap and the like existing in the prior combined power.

Description

Kerosene/liquid methane external parallel turbine-based rotary detonation engine

Technical Field

The invention belongs to the technical field of aeroengines, and particularly relates to a kerosene/liquid methane external parallel turbine-based rotary detonation engine.

Background

Hypersonic aircraft are praised as the third revolution in the world's aviation history following propellers and jet planes, and their research will have a tremendous impact on the military field. The power device is a main key technology for realizing hypersonic flight, and the currently commonly adopted turbine-based combined cycle engine (TBCC) has the problems of thrust trap and the like during mode conversion.

The detonation combustion chamber adopted at present directly replaces the scheme of main combustion, and pressure return can occur due to higher peak pressure of detonation waves, so that the stable working margin of the gas compressor is narrowed. In addition, the unsteady, uneven flow of the detonation combustor outlet reduces turbine power extraction efficiency and operational life. Furthermore, the control mechanism of the rotary detonation wave is not clear, and a serious challenge is presented to the overall control of the engine.

When the Mach number is high, the air inlet temperature is increased sharply, so that the strength of the engine material is poor, the reliability is reduced, the performance of the engine is poor, and the thrust requirement of the near-space vehicle is difficult to meet. At the moment, the temperature of the high-temperature air flow is reduced below the limit of the temperature of the engine by adopting an effective technical means, and the method has important significance for ensuring the reliable and efficient operation of the engine. At present, a jet cooling mode is generally adopted, namely, a spraying device of a coolant is arranged in front of a gas compressor, the heat absorption characteristic of liquid drop evaporation is utilized to reduce the incoming flow temperature, but liquid can be mixed with high-temperature air to form complex gas-liquid two-phase flow, pressure pulsation is caused, the distortion degree of gas flow at the inlet of the gas compressor is increased, and the working performance of the gas compressor is reduced.

Disclosure of Invention

In view of the problems existing in the background art, the invention provides a kerosene/liquid methane external parallel turbine-based rotary detonation engine, which comprises an outer shell 611, a mixed pressure type air inlet channel 1, an adjustable air inlet channel 2, a cooling system 3, an air bleed valve 4, a turbine engine 5 and a rotary detonation engine 6;

the mixed pressure type air inlet channel 1 is provided with: a central rectifying cone 11, an inner housing 12; the central rectifying cone 11 is characterized in that the front part of the main mixing pressure type air inlet channel 1 is conical, the middle part is cylindrical, the rear part is conical, and the whole body is approximately spindle-shaped with two pointed ends; a heat-resistant coating is coated on the surface of the central rectifying cone 11; the whole inner shell 12 is in a general cylindrical shell shape, is arranged on the periphery of the central rectifying cone 11, the front end face is positioned in the middle of the front cone of the central rectifying cone 11, and continuously extends backwards from the rear end of the central rectifying cone 11 to the compressor casing, the front edge of the inner shell 12 is in an arc shape, and the thickness of the inner shell gradually transits to the thickness consistent with the thickness of the compressor casing on the premise of meeting the strength requirement; an external pressure type air inlet channel is formed between the central rectifying cone 11 and the outer shell 611 at the position where the front part of the central rectifying cone 11 is not surrounded by the inner shell 12; an internal pressure type air inlet channel is formed between the central rectifying cone 11 and the inner shell 12;

the annular area surrounded by the outer shell 611 and the inner shell 12 of the mixed pressure type air inlet channel 1 forms a flow passage of the rotary detonation engine 6;

the adjustable air inlet channel 2 is arranged at the periphery of the outer shell 611, and the adjustable air inlet channel 2 comprises an adjusting piece 21, a transmission rod 22 and an actuating mechanism 23; the adjusting piece 21 is arranged outside the head of the outer shell, the rear end of the adjusting piece 21 is hinged with the front end of the outer shell 611 through a hinge, and the adjusting piece can move radially through a shaft formed around the hinge; the transmission rod 22 is arranged on the outer side of the head of the adjustable air inlet channel 2, the transmission rod 22 is connected with the adjusting piece 21 through a hinge, the connecting point is positioned in the middle of the adjusting piece, the transmission rod is used for transmitting force from the actuating mechanism 23 and driving the adjusting piece 21, and the rear end of the transmission rod 22 is fixedly connected with a piston of the actuating mechanism 23; the actuating mechanism 23 is arranged outside the outer shell 611, and the actuating mechanism 23 and the outer shell are fixedly connected, and the actuating mechanism 23 provides power for adjusting the adjustable air inlet channel 2; the adjustable air inlet channel 2 adjusts the inlet area of the air inlet channel according to the flight Mach number, and when the air inlet channel is 0-3Ma, the adjusting piece rotates inwards until the adjustable air inlet channel 2 is closed, so that the flight resistance is reduced; when the Mach number is greater than 3, the regulating piece rotates outwards until reaching the set air inlet area, and the adjustable air inlet channel 2 is opened;

the cooling system 3 is provided with a heat exchange line 31, a booster pump 32, a return pump 33, a mixer 34, and a fuel pump 35; the heat exchange pipeline 31 is provided with a connecting piece 311 and a pipeline 312, the heat exchange pipeline 31 is arranged between the central rectifying cone 11 and the air compressor 51, and the rear end of the heat exchange pipeline 31 is connected with an inlet guide vane of the air compressor 51; the heat exchange pipeline 31 is in coaxial relation with the mixed pressure type air inlet channel 1 and the adjustable air inlet channel 2, and the shaft is the axis of the engine; the connecting piece 311 is a whole cylindrical frame structure and comprises a circular ring 3111 at the front end and the rear end, and a plurality of support trusses 3112 which are arranged in parallel and connect the front circular ring 3111 and the rear circular ring 3111 together, wherein the plurality of support trusses 3112 are identical, are uniformly arranged on the circumference of the circular ring perpendicularly to the plane of the circular ring 3111 and are fixedly connected with the two circular rings; the connecting piece 311 is respectively connected with the central rectifying cone 11 and the air compressor 51 through the front circular ring 3111 and the rear circular ring 3111; the pipeline 312 is composed of a plurality of layers of 'solenoid' pipelines, the plurality of layers of 'solenoid' pipelines are coaxial, each layer of pipeline forms a cylindrical frame structure, each layer of pipeline is independent from each other, and the pipelines are sequentially arranged from inside to outside from small to large according to the radius;

a booster pump 32, a return pump 33, a mixer 34, and a fuel pump 35 are disposed on the outer case 611, the booster pump 32 for increasing the pressure of the cooling medium, the return pump 33 for recovering the high-temperature medium output from the heat exchange line 31 after heat exchange and injecting it into the mixer 34, and the fuel pump 35 for providing an initial pressure to the cooling medium injected into the heat exchange line 31; the mixer 34 is used for regulating the temperature of the reflux cooling medium; the mixer 34 has two inlets, one is high-temperature reflux from the reflux pump 33 and the other is initial normal-temperature fuel of the fuel pump 35, and the two are mixed to obtain fuel with proper temperature and injected into the main combustion chamber and the detonation combustion chamber;

a bleed valve 4 arranged on the compressor casing of the turbine engine for connecting the compressor intermediate stage with the gas collection chamber 61 of the rotary detonation engine; at Mach numbers 0-3, the bleed valve 4 is opened; at Mach 3-6, the bleed valve 4 is closed;

the turbine engine 5 is provided with a compressor 51, a main combustion chamber 52, a turbine 53, an afterburner 54 and a laval 55;

the compressor 51, which is an axial compressor, comprises a compressor stator and a rotor, which are located after the heat exchange line 31;

a main combustion chamber 52, which is an annular combustion chamber, disposed immediately after the compressor 51;

a turbine 53, which is an axial-flow turbine, disposed immediately behind the main combustion chamber 52;

afterburner 54 disposed immediately after turbine 53;

a rotary detonation engine 6 arranged at the periphery of the turbine engine and comprising an air collection chamber 61, a tesla valve 62, a fuel chamber 63, an annular combustion chamber 64 and a laval nozzle 65; the rotary detonation engine 6 is arranged in a flow passage downstream of the adjustable air inlet passage 2; the air collecting cavity 61 is arranged at the downstream of the adjustable air inlet channel 2 and is an annular channel surrounded by the outer shell 611 and the inner shell 12; the tesla valve 62 is arranged immediately behind the gas collection chamber; the tesla valve 62 comprises a wedge-shaped part 621 and a flow guiding cone 622, wherein the wedge-shaped part 621 is fixedly connected with the outer wall of the inner shell 12, is arranged along the circumference of the outer wall of the inner shell 12, the wedge-shaped part 621 completely surrounds the inner shell 12, the axial section of the wedge-shaped part is wedge-shaped, the front part of the section is oblique line with a certain angle with the outer wall of the inner shell 12, the angle is an acute angle, the rear part is arc-shaped, two end points of the arc are respectively positioned at the tail end of the oblique line and one point on the outer wall of the inner shell 12, and the arc is recessed towards the oblique line direction; the cross section of the diversion cone 622 is streamline, the front part is circular arc, and is concentric with the rear circular arc of the wedge-shaped component 621, and gradually transits to a sharp angle backwards, which is at a certain distance from the inner shell 12, the backflow channel flows from the annular combustion chamber 64 to the gas collecting chamber 61, and the forward flow channel flows from the gas collecting chamber 61 to the combustion chamber 64; the diversion cone 622 is fixedly connected with the outer wall of the inner shell 12 through fixing mechanisms which are uniformly arranged along the circumferential direction; the fuel chamber 63 is divided into an outer fuel chamber and an inner fuel chamber, the outer fuel chamber being located on the inner wall of the outer shell 611 to protrude inward; the inner fuel cavity is positioned on the outer wall of the inner shell 12, protrudes outwards and is opposite to the outer fuel cavity; the axial section of the outer fuel cavity is a closed plane graph formed by a straight line and an arc, wherein the straight line is positioned on the outer surface of the outer shell 611 parallel to the axis of the engine, a rectangular hole is formed in the middle part of the closed graph, one side of the rectangular hole is positioned in the center of the straight line, thus the rectangular hole is distributed in a ring shape, the circle center of the ring-shaped rectangular hole coincides with the axis of the engine, and fuel is injected into the combustion chamber through a plurality of injection small holes arranged in the outer fuel cavity, and the fuel comes from the mixer 34; the fuel supply lines are disposed at the outer case 611 and the inner case 12, respectively; at the outer shell 611, the fuel supply pipeline enters the outer shell 611 from outside to inside through the through hole on the outer shell 611 and is directly connected with the outer fuel cavity; at the position of the inner shell 12, a fuel supply pipeline enters the inner shell 12 through another through hole on the outer shell 611, and then the fuel supply pipeline is divided into three paths, one path is connected with a main combustion chamber 52 of the turbine engine through a first half through hole on the inner shell 12, the other path is sprayed into an afterburner 54 through a second half through hole on the inner shell 12, and the other path is connected with an inner fuel cavity through a third half through hole on the inner shell 12; an inner fuel cavity is arranged at the same axial position, and the shape and the fuel injection mode of the inner fuel cavity are completely the same as those of the outer fuel cavity; the annular combustion chamber 64 is positioned behind the fuel cavity 63 and is an annular cavity; a laval nozzle 65 is located downstream of the annular combustion chamber 64; the high enthalpy product generated by the rotating detonation wave is discharged through the laval nozzle 65.

In one embodiment of the invention, the actuating mechanism 23 is a hydraulic actuating mechanism.

In another embodiment of the present invention, the line 312 uses two layers of "solenoids" and the cooling medium used in the line 312 is kerosene or liquid methane.

In one embodiment of the invention, the orifice is 0.2mm in diameter and the orifice is perforated vertically from the rectangular orifice to the combustion chamber.

The working method of the kerosene/liquid methane external parallel turbine-based rotary detonation engine comprises the following steps:

when 0-3Ma flies, in order to reduce the flying resistance, the actuating mechanism 23 drives the adjusting piece 21 to rotate inwards through the transmission rod 22 until the adjustable air inlet channel 2 is closed, external atmosphere only enters the turbine engine through the mixed pressure air inlet channel 1, after being compressed by a plurality of stages through a gas compressor, part of compressed gas enters the gas collecting cavity 61 through the gas bleed valve 4, and is fully mixed with fuel sprayed from the fuel cavity 63, the formed fresh mixture enters the annular combustion chamber 64, then the detonation system works, continuously rotating detonation waves are formed in the annular combustion chamber 64, the inflowing fresh mixture is continuously consumed, the combustion products expand downwards, and are discharged through the Laval nozzle 65 to generate thrust; another portion of the compressed gas continues to be compressed by the latter stages of the compressor 51, with the subsequent process being the same as a conventional turbine engine;

3-6Ma, in order to maintain the turbine engine performance, the bleed valve 4 is closed, and the actuating mechanism 23 drives the adjusting piece 21 to rotate outwards through the transmission rod 22 until the adjustable air inlet channel 2 is completely opened; on the one hand, the external atmosphere enters the gas collection cavity 61 through the adjustable gas inlet channel 2 and is fully mixed with fuel sprayed from the fuel cavity 63, the formed fresh mixture enters the annular combustion chamber 64, then the detonation system works, continuously rotating detonation waves are formed in the annular combustion chamber 64, the inflowing fresh mixture is continuously consumed, combustion products expand downstream, and the combustion products are discharged through the Laval nozzle 65 to generate thrust; the other part of external atmosphere enters the turbine engine through the mixed pressure type air inlet channel 1, and the inlet temperature before the air compressor 51 is higher due to higher Mach number of incoming flow, at the moment, the cooling system 3 starts to work, and part of fuel starts to flow into the heat exchange pipeline, on one hand, the temperature of the high-temperature air flow can be reduced after passing through the heat exchange pipeline, so that the reliable and stable work of the air compressor is facilitated; on the other hand, kerosene or methane in the pipeline is heated and evaporated or cracked, the reaction activity is improved, the kerosene or methane is divided into three paths after being mixed and cooled, one path enters the main combustion chamber 52 to participate in traditional isobaric combustion, the other path is injected into the annular combustion chamber 64 to participate in detonation combustion, and the other path is connected with the afterburner 54 to provide fuel when the afterburner is started.

The invention has the following advantages:

because the rotary detonation engine is arranged on the periphery of the turbine engine, the detonation combustion chamber adopts approximate isovolumetric combustion to replace the traditional isobaric combustion, and the combustion efficiency can be greatly improved.

By adopting the external parallel scheme, the influence of the detonation combustion chamber on engine parts such as a compressor, a turbine and the like can be effectively avoided, and the control difficulty is reduced.

When 0-3Ma flies, the adjustable air inlet channel is closed, and air required by detonation combustion flows in from the middle stage of the air compressor through the air bleed valve, so that the flying resistance is reduced; 3-6Ma, the bleed valve is closed, the adjustable air inlet is gradually opened, and high-temperature air required by detonation combustion is provided. At the moment, the heat exchange pipeline starts to work, so that on one hand, the air flow at the inlet of the air compressor can be cooled, and the performance of the turbine engine is kept; on the other hand, kerosene or liquid methane in the heat exchange pipeline can be heated, and the kerosene/liquid methane after heat exchange is introduced into the detonation combustion chamber. Heating will increase its evaporation rate and activity, facilitating subsequent detonation combustion. Through the two state switching, the wide-speed-range flight of 0-6Ma is realized.

Drawings

FIG. 1 is a schematic diagram of the operation of a kerosene/liquid methane external parallel turbine-based rotary detonation engine, wherein the open arrows indicate the direction of gas flow and the solid arrows indicate the direction of flow of the cooling medium kerosene/liquid methane;

FIG. 2 is a schematic illustration of the heat exchange circuit 31 of FIG. 1;

FIG. 3 shows a schematic diagram of a Tesla valve 62;

fig. 4 shows the shape of the outer fuel cavity.

Reference numerals illustrate:

1 mixed pressure type internal air inlet channel 4 air entraining valve

11 center cone 5 turbine engine

12 inner shell 51 compressor

2-adjustable main combustion chamber of outer air inlet 52

21 regulating plate 53 turbine

22 drive rod 54 afterburner

23 hydraulic actuator 55 Laval nozzle

3 Cooling System 6 continuous rotation detonation Engine

31 heat exchange pipeline 61 gas collecting cavity

32 booster pump 62 tesla valve

33 reflux pump 63 fuel chamber

34 mixer 64 annular combustor

35 fuel pump 65 Laval nozzle

611 outer shell 621 wedge-shaped element

622 flow guide cone 623 screw

Detailed Description

The kerosene/liquid methane external parallel turbine-based rotary detonation engine comprises an outer shell 611, a mixed pressure type air inlet channel 1, an adjustable air inlet channel 2, a cooling system 3, an air-entraining valve 4, a turbine engine 5 and a rotary detonation engine 6.

The mixed pressure type air inlet channel 1 is provided with: a central cone 11, an inner housing 12. The central rectifying cone 11 is mainly composed of three parts, the front part is conical, the middle part is cylindrical, the rear part is conical, the whole body is approximately spindle-shaped with two pointed ends, the central rectifying cone 11 is a device well known to those skilled in the art, and description is not repeated. To increase the reliability of the central cone 11 at high mach numbers, a heat resistant coating is applied to its surface. The whole inner shell 12 is in a generally cylindrical shell shape and is arranged on the periphery of the central rectifying cone 11, the front end face is positioned in the middle of the front cone of the central rectifying cone 11, the front end of the inner shell 12 extends backwards from the rear end of the central rectifying cone 11 to the compressor casing, the front edge of the inner shell 12 is in an arc shape, and in order to reduce the weight of the engine, the thickness of the inner shell gradually transits to the thickness consistent with the compressor casing on the premise of meeting the strength requirement. An external pressure type air inlet channel is formed between the central rectifying cone 11 and the outer shell 611 at the position where the front part of the central rectifying cone 11 is not surrounded by the inner shell 12, and the external pressure type air inlet channel carries out speed reduction and pressurization on incoming flow by means of a shock wave system formed by the central rectifying cone 11. The air flow then enters the internal pressure inlet channel formed between the central cone 11 and the inner housing 12 for further compression.

The annular region surrounded by the outer housing 611 and the inner housing 12 of the mixed pressure intake duct 1 constitutes a flow passage of the rotary knock engine 6.

The adjustable intake duct 2 is disposed at the periphery of the outer housing 611, and the adjustable intake duct 2 includes a regulating plate 21, a transmission rod 22, and an actuating mechanism 23 (the structure of the adjustable intake duct 2 can be seen in patent application "a turbine-based knock boost engine based on a pneumatic center body, application No. 202211224422.8"). The adjusting piece 21 is arranged outside the head of the outer shell, the rear end of the adjusting piece 21 is hinged with the front end of the outer shell 611 through a hinge, the inlet area of the air inlet channel is changed through axial radial movement formed around the hinge, the arrangement mode and structure of the adjusting piece 21 are similar to those of an adjustable convergent tail nozzle, and are well known to the person skilled in the art, the adjusting piece 21 is not tired (the adjusting piece 21 needs to be uniformly arranged into a circle on the circumference of the front end of the outer shell 611, and the left side and the right side of the adjacent adjusting piece are respectively overlapped and pressed (lapped) with the adjacent adjusting piece on the left side and the right side to form a gapless connecting surface. The transmission rod 22 is arranged on the outer side of the head of the adjustable air inlet channel 2, the transmission rod 22 is connected with the adjusting piece 21 through a hinge, the connecting point is positioned at the middle position of the adjusting piece, the transmission rod is used for transmitting force from the actuating mechanism 23 and driving the adjusting piece 21, and the rear end of the transmission rod 22 is fixedly connected with the piston of the actuating mechanism 23. The actuating mechanism 23 is arranged outside the outer shell 611, and the actuating mechanism 23 and the outer shell are fixedly connected, and the actuating mechanism 23 provides power for adjusting the adjustable air inlet channel 2. The adjustable air inlet channel 2 adjusts the inlet area of the air inlet channel according to the flight Mach number, and when the air inlet channel is 0-3Ma, the adjusting piece rotates inwards until the adjustable air inlet channel 2 is closed, so that the flight resistance is reduced; when Mach number is larger than 3, the adjusting piece rotates outwards until reaching the set air inlet area, and the adjustable air inlet channel 2 is opened.

The cooling system 3 is provided with a heat exchange line 31, a booster pump 32, a return pump 33, a mixer 34, and a fuel pump 35. The heat exchange pipeline 31 is provided with a connecting piece 311 and a pipeline 312, the heat exchange pipeline 31 is arranged between the central rectifying cone 11 and the air compressor 51, and the rear end of the heat exchange pipeline 31 is connected with an inlet guide vane of the air compressor 51, and the specific position is well known to the person skilled in the art. The heat exchange pipeline 31 is in coaxial relation with the mixed pressure type air inlet channel 1 and the adjustable air inlet channel 2 (the shaft is the axis of the engine). As shown in fig. 1 and 2, the connecting member 311 is a monolithic cylindrical frame structure, and includes a circular ring 3111 at each of front and rear ends, and several support trusses 3112 (3 support trusses are shown in the figure and are determined according to the actual number) which are parallel to each other and connect the front and rear circular rings 3111 together, where the several support trusses 3112 are identical, are uniformly arranged on the circumference of the circular ring perpendicularly to the plane of the circular ring 3111, and are fixedly connected to the two circular rings. The connection piece 311 is connected to the center cone 11 and the compressor 51 through the front and rear rings 3111, respectively. The pipe 312 is composed of a plurality of layers of pipes similar to "solenoids", the plurality of layers of the "solenoids" are coaxial, each layer of the pipe forms a cylindrical frame structure, each layer of the pipe is independent from each other, and the pipes are sequentially arranged from the inside to the outside according to the radius from the small to the large, and the aim of controlling the cooling effect can be achieved by controlling the working layers of the heat exchange pipe 31. In one embodiment of the present invention, a two layer "solenoid" is used, as shown in FIG. 2. The way to secure the piping 312 to the support truss 3112 is a conventional securing method and will not be described in detail. The cooling medium used in line 312 is kerosene or liquid methane. By reasonably arranging the heat exchange pipeline 31 in the engine, higher heat exchange efficiency can be realized, on one hand, the incoming flow temperature can be reduced, the cooling margin can be improved, and the circulating work can be increased; on the other hand, the temperature of kerosene or liquid methane can be increased, and the evaporation rate is accelerated, so that the characteristics of fuel entering a combustion chamber or an external detonation chamber are improved, the blending effect is improved, and the structure combustion is facilitated.

The booster pump 32, the return pump 33, the mixer 34 and the fuel pump 35 are disposed on the outer case 611, the operation principle of which is well known to those skilled in the art, wherein the booster pump 32 is used to raise the pressure of the cooling medium so that it can enter the heat exchange line 31 at a designed pressure, the return pump 33 is used to recover the high temperature medium outputted from the heat exchange line 31 after heat exchange and inject it into the mixer 34, and the fuel pump 35 is used to provide an initial pressure to the cooling medium injected into the heat exchange line 31. The mixer 34 is used to regulate the temperature of the return cooling medium so that it can flow into the main combustion chamber 52 and the fuel cavity 63 at a suitable temperature for organized combustion. The mixer 34 has two inlets, one is high temperature return from the return pump 33 and the other is the original normal temperature fuel from the fuel pump 35, and the two are mixed to obtain fuel with proper temperature and injected into the main combustion chamber and the detonation combustion chamber.

Bleed valve 4, which is arranged on the compressor casing of the turbine engine, in a specific position on the compressor casing which is well known to the person skilled in the art, for connecting the compressor intermediate stage with the gas collection chamber 61 of the rotary detonation engine. At Mach numbers 0-3, the bleed valve 4 is opened; at Mach 3-6, the bleed valve 4 is closed.

The turbine engine 5 is provided with a compressor 51, a main combustion chamber 52, a turbine 53, an afterburner 54 and a laval 55.

The compressor 51, which is an axial flow compressor, includes a compressor stator and rotor, the specific locations of which in the engine are well known to those skilled in the art, is shown in fig. 1, after the heat exchange line 31.

The main combustion chamber 52, which is an annular combustion chamber, is disposed immediately behind the compressor 51 and includes a diffuser, a flame tube, a housing, a fuel nozzle, and an ignition device, and the construction of the main combustion chamber 52 and its specific location in the engine are well known to those skilled in the art.

The turbine 53, which is an axial turbine, is disposed immediately behind the main combustion chamber 52, including a pilot and turbine, the construction of the turbine 53 and its specific location in the engine being well known to those skilled in the art.

Afterburner 54, which is comprised of oil rings, igniters, diffusers, cans, etc., is disposed immediately behind turbine 53, and the construction of afterburner 54 and its specific location in the engine is well known to those skilled in the art.

The structural composition of the laval 55 and its specific location in the engine are well known to those skilled in the art.

The rotary detonation engine 6, which is disposed at the periphery of the turbine engine, includes an air collection chamber 61, a tesla valve 62, a fuel chamber 63, an annular combustion chamber 64, and a laval nozzle 65, and the remaining specific structures of the rotary detonation engine 6 other than the tesla valve 62 are well known to those skilled in the art (refer to Liu Shijie. Continuous rotary detonation wave structure, propagation mode and self-sustaining mechanism research [ D ]. National defense science and technology university, 2012). As shown, a rotary knock engine 6 is arranged in the flow path downstream of the adjustable intake 2. The air collecting chamber 61 is disposed downstream of the adjustable intake duct 2, and is an annular passage surrounded by the outer housing 611 and the inner housing 12. The Tesla valve 62 is arranged immediately behind the gas collecting cavity and is used for inhibiting the return pressure of the rotary detonation wave, so that the adjustable gas inlet channel 2 can work normally; the tesla valve 62 is schematically shown in fig. 3, and the specific structure includes a wedge part 621 and a diversion cone 622, where the wedge part 621 is fixedly connected with the outer wall of the inner housing 12, and is arranged along the circumference of the outer wall of the inner housing 12, the wedge part 621 completely surrounds the inner housing 12, the axial section of the wedge part is wedge-shaped (the shaft is an engine axis), the front part of the section is a diagonal line (the angle is an acute angle) with the outer wall of the inner housing 12, the rear part is arc-shaped, two end points of the arc are respectively located at the tail end of the diagonal line and one point on the outer wall of the inner housing 12, and the arc is recessed toward the diagonal line. The cross section of the guide cone 622 is streamlined, like a water drop, the front part is circular arc, concentric with the rear circular arc of the wedge-shaped member 621, and gradually transitions back to a sharp corner, which is spaced apart from the inner housing 12, and the dashed arrow in fig. 3 represents a return flow path, the solid line represents a forward flow path, which is flowing from the annular combustion chamber 64 to the gas collecting chamber 61, and the forward flow path is flowing from the gas collecting chamber 61 to the combustion chamber 64. The guide cone 622 is fixedly connected to the outer wall of the inner housing 12 by means of, for example, 8 screws 623 which are arranged uniformly in the circumferential direction. The fuel chamber 63 is divided into an outer fuel chamber and an inner fuel chamber, the outer fuel chamber being located on the inner wall of the outer shell 611 to protrude inward; the inner fuel cavity is positioned on the outer wall of the inner shell 12, protrudes outwards and is opposite to the outer fuel cavity; the shape of the outer fuel chamber is shown in fig. 4, the axial section of the outer fuel chamber is a closed plane pattern formed by a straight line and an arc, wherein the straight line is positioned on the outer surface of the outer shell 611 parallel to the axis of the engine, a rectangular hole is formed in the middle part of the closed plane pattern, one side of the rectangular hole is positioned in the center of the straight line, thus the rectangular hole is distributed in a ring shape, the center of the ring-shaped rectangular hole coincides with the axis of the engine, the fuel is injected into the combustion chamber through 36 injection small holes with the aperture of 0.2mm, which are arranged in the outer fuel chamber, the injection small holes are punched from the rectangular hole to the combustion chamber in a vertical (shortest distance) manner, and the fuel comes from the mixer 34. The fuel supply lines are disposed at the outer housing 611 and the inner housing 12, respectively. At the outer shell 611, the fuel supply line passes through a through hole provided in advance in the outer shell 611, enters the outer shell 611 from outside to inside, and is directly connected to the outer fuel chamber. At the position of the inner shell 12, the fuel supply pipeline enters the inner shell 12 through another through hole which is arranged in advance on the outer shell 611, then the fuel supply pipeline is divided into three paths, one path is connected with the main combustion chamber 52 of the turbine engine through a first half through hole which is arranged in advance on the inner shell 12, the other path is sprayed into the afterburner 54 through a second half through hole which is arranged in advance on the inner shell 12, and the other path is connected with the inner combustion chamber through a third half through hole which is arranged in advance on the inner shell 12. To ensure a good mixing effect, as described above, an inner fuel chamber is provided at the same axial position, the shape and the fuel injection manner of which are exactly the same as those of the outer fuel chamber. An annular combustion chamber 64 is located behind the fuel cavity 63 and is an annular cavity. A laval nozzle 65 is located downstream of the annular combustion chamber 64. The rotating detonation wave propagates circumferentially within the annular combustor 64, continuously consuming reactants, and the resulting high enthalpy products are discharged via the Laval nozzle 65, creating a high velocity gas stream, thereby forming thrust. The laval nozzle 65 accelerates the expansion of the combustion products and is the primary component of thrust. Because of the simple construction of the rotary detonation engine, the absence of rotating parts, and the high rate of heat release, the overall length is less than that of a turbine engine, particularly if the outlet of the Laval nozzle 65 is located in the afterburner 54 of the turbine engine.

The construction of the bleed valve 4 and its specific position in the engine is well known to the person skilled in the art and will not be described in any greater detail.

In the kerosene/liquid methane external parallel turbine-based rotary detonation engine, when 0-3Ma flies, in order to reduce the flying resistance, an actuating mechanism 23 drives a regulating piece 21 to rotate inwards through a transmission rod 22 until an adjustable air inlet channel 2 is closed, external atmosphere only enters the turbine engine through a mixed pressure air inlet channel 1, after being compressed by a compressor in multiple stages, part of compressed gas enters an air collection cavity 61 through an air entraining valve 4 and is fully mixed with fuel sprayed from a fuel cavity 63, the formed fresh mixture enters an annular combustion chamber 64, a detonation system works, continuously rotating detonation waves are formed in the annular combustion chamber 64, the inflowing fresh mixture is continuously consumed, combustion products expand downwards and are discharged through a Laval nozzle 65 to generate thrust; the other part of the compressed gas is compressed by the latter stages of the compressor 51, and the subsequent process is the same as that of a conventional turbine engine, and will not be described again.

In the kerosene/liquid methane external parallel turbine-based rotary detonation engine, when 3-6Ma flies, in order to keep the turbine engine performance, the bleed valve 4 is closed, and the actuating mechanism 23 drives the regulating piece 21 to rotate outwards through the transmission rod 22 until the adjustable air inlet channel 2 is completely opened. On the one hand, the external atmosphere enters the gas collection cavity 61 through the adjustable gas inlet channel 2 and is fully mixed with fuel sprayed from the fuel cavity 63, the formed fresh mixture enters the annular combustion chamber 64, then the detonation system works, continuously rotating detonation waves are formed in the annular combustion chamber 64, the inflowing fresh mixture is continuously consumed, combustion products expand downstream, and the combustion products are discharged through the Laval nozzle 65 to generate thrust; the other part of external atmosphere enters the turbine engine through the mixed pressure type air inlet channel 1, and the inlet temperature before the air compressor 51 is higher due to higher Mach number of incoming flow, at the moment, the cooling system 3 starts to work, and part of fuel starts to flow into the heat exchange pipeline, on one hand, the temperature of the high-temperature air flow can be reduced after passing through the heat exchange pipeline, so that the reliable and stable work of the air compressor is facilitated; on the other hand, kerosene or methane in the pipeline is heated and evaporated or cracked, the reaction activity is improved, and the kerosene or methane is divided into two paths after being mixed and cooled, wherein one path enters the main combustion chamber 52 to participate in the traditional isobaric combustion, and the other path is injected into the annular combustion chamber 64 to participate in the detonation combustion.

Because the turbine-based rotary detonation engine is used, the invention can effectively utilize the advantages of high cycle efficiency, high-frequency continuous operation, only one ignition and the like of the rotary detonation engine, and has great significance for realizing high-speed remote flight of a near space aircraft and solving the problem of thrust trap existing in the existing combined power.

The kerosene/liquid methane external parallel turbine-based rotary detonation engine adopts the external parallel turbine-based rotary detonation engine, and according to the flight Mach number, the rotary detonation and the turbine engine are relatively independent by adjusting the internal flow passage of the engine, so that a series of problems caused by the replacement of a main combustion by a detonation combustion chamber can be effectively avoided, the flight envelope range of the engine is effectively widened, and the wide-speed-range flight of 0-6Ma is realized.

According to the kerosene/liquid methane external parallel turbine-based rotary detonation engine, high-temperature incoming flows can be cooled by using the kerosene/liquid methane according to the incoming flow Mach number, so that on one hand, the incoming flow temperature can be reduced, the cooling margin of the engine can be improved, and the circulating work can be increased; on the other hand, the temperature of kerosene or liquid methane can be increased, and the evaporation rate is accelerated, so that the characteristics of fuel entering a combustion chamber or an external detonation chamber are improved, the blending effect is improved, and the structure combustion is facilitated.

Claims (5)

1. The kerosene/liquid methane external parallel turbine-based rotary detonation engine is characterized by comprising an outer shell (611), a mixed pressure type air inlet channel (1), an adjustable external air inlet channel (2), a cooling system (3), an air entraining valve (4), a turbine engine (5) and a rotary detonation engine (6);

the mixed pressure type air inlet channel (1) is provided with: a central cone (11), an inner housing (12); the front part of the main mixed pressure type air inlet channel (1) is conical, the middle part is cylindrical, the rear part is conical, and the whole body is approximately fusiform with two pointed ends; a heat-resistant coating is coated on the surface of the central rectifying cone (11); the whole inner shell (12) is in a general cylindrical shell shape and is arranged on the periphery of the central rectifying cone (11), the front end face is positioned in the middle of the front cone of the central rectifying cone (11), the front end of the central rectifying cone (11) continuously extends backwards to the compressor casing from the rear end of the central rectifying cone (11), the front edge of the inner shell (12) is in an arc shape, and the thickness of the inner shell gradually transits to the thickness consistent with the compressor casing on the premise of meeting the strength requirement; an external pressure type air inlet channel is formed between the central rectifying cone (11) and the outer shell (611) at the position where the front part of the central rectifying cone (11) is not surrounded by the inner shell (12); an internal pressure type air inlet channel is formed between the central rectifying cone (11) and the inner shell (12);

the annular area surrounded by the outer shell (611) and the inner shell (12) of the mixed pressure type air inlet channel (1) forms a flow passage of the rotary detonation engine (6);

the adjustable air inlet channel (2) is arranged at the periphery of the outer shell (611), and the adjustable air inlet channel (2) comprises an adjusting piece (21), a transmission rod (22) and an actuating mechanism (23); the adjusting piece (21) is arranged on the outer side of the head of the outer shell, the rear end of the adjusting piece (21) is hinged with the front end of the outer shell (611) through a hinge, and the adjusting piece can move radially through a shaft formed around the hinge; the transmission rod (22) is arranged on the outer side of the head of the adjustable air inlet channel (2), the transmission rod (22) is connected with the adjusting piece (21) through a hinge, the connecting point is positioned in the middle of the adjusting piece, and the transmission rod is used for transmitting the force from the actuating mechanism (23) and driving the adjusting piece (21), and the rear end of the transmission rod (22) is fixedly connected with the piston of the actuating mechanism (23); the actuating mechanism (23) is arranged outside the outer shell (611) and is fixedly connected with the outer shell, and the actuating mechanism (23) provides power for adjusting the adjustable air inlet channel (2); the adjustable air inlet channel (2) adjusts the inlet area of the air inlet channel according to the flight Mach number, and when the air inlet channel is 0-3Ma, the adjusting piece rotates inwards until the adjustable air inlet channel (2) is closed, so that the flight resistance is reduced; when the Mach number is greater than 3, the regulating piece rotates outwards until reaching the set air inlet area, and the adjustable air inlet channel (2) is opened;

the cooling system (3) is provided with a heat exchange pipeline (31), a booster pump (32), a reflux pump (33), a mixer (34) and a fuel pump (35); the heat exchange pipeline (31) is provided with a connecting piece (311) and a pipeline (312), the heat exchange pipeline (31) is arranged between the central rectifying cone (11) and the air compressor (51), and the rear end of the heat exchange pipeline is connected with an inlet guide vane of the air compressor (51); the heat exchange pipeline (31) is in coaxial relation with the mixed pressure type air inlet channel (1) and the adjustable air inlet channel (2), and the shaft is the axis of the engine; the connecting piece (311) is of an integral cylindrical frame structure and comprises a circular ring (3111) at the front end and the rear end, and a plurality of support trusses (3112) which are arranged in parallel and are used for connecting the front circular ring (3111) and the rear circular ring (3111), wherein the support trusses (3112) are identical, are uniformly arranged on the circumference of the circular ring in a manner of being perpendicular to the plane of the circular ring (3111) and are fixedly connected with the two circular rings; the connecting piece (311) is respectively connected with the central rectifying cone (11) and the air compressor (51) through the front circular ring (3111) and the rear circular ring; the pipeline (312) is composed of a plurality of layers of solenoid pipelines, the solenoid pipelines are coaxial, each layer of pipeline forms a cylindrical frame structure, each layer of pipeline is independent from each other, and the pipelines are sequentially arranged from the small radius to the large radius from the inside to the outside;

the booster pump (32), the reflux pump (33), the mixer (34) and the fuel pump (35) are arranged on the outer shell (611), the booster pump (32) is used for increasing the pressure of the cooling medium, the reflux pump (33) is used for recovering the high-temperature medium output by the heat exchange pipeline (31) after heat exchange and injecting the high-temperature medium into the mixer (34), and the fuel pump (35) is used for providing initial pressure for the cooling medium injected into the heat exchange pipeline (31); a mixer (34) for regulating the temperature of the return cooling medium; the mixer (34) is provided with two inlets, one is high-temperature backflow from the backflow pump (33), the other is initial normal-temperature fuel of the fuel pump (35), and the two are mixed to obtain fuel with proper temperature, and the fuel is injected into the main combustion chamber and the detonation combustion chamber;

a bleed valve (4) arranged on a compressor casing of the turbine engine for connecting a compressor intermediate stage and a gas collection chamber (61) of the rotary detonation engine; at Mach number 0-3, the bleed valve (4) is opened; at Mach 3-6, the bleed valve (4) is closed;

the turbine engine (5) is provided with a compressor (51), a main combustion chamber (52), a turbine (53), an afterburner (54) and a Laval (55);

the compressor (51) is an axial-flow compressor and comprises a compressor stator and a rotor, and the compressor stator and the rotor are positioned behind the heat exchange pipeline (31);

a main combustion chamber (52), which is an annular combustion chamber, arranged immediately after the compressor (51);

a turbine (53), which is an axial turbine, arranged immediately after the main combustion chamber (52);

an afterburner (54) arranged immediately after the turbine (53);

a rotary detonation engine (6) arranged at the periphery of the turbine engine and comprising an air collection chamber (61), a tesla valve (62), a fuel chamber (63), an annular combustion chamber (64) and a laval nozzle (65); the rotary knocking engine (6) is arranged in a flow passage at the downstream of the adjustable air inlet passage (2); the air collection cavity (61) is arranged at the downstream of the adjustable outer air inlet channel (2) and is an annular channel surrounded by the outer shell (611) and the inner shell (12); a tesla valve (62) is arranged immediately behind the gas collection chamber; the Tesla valve (62) comprises a wedge-shaped part (621) and a flow guiding cone (622), wherein the wedge-shaped part (621) is fixedly connected with the outer wall of the inner shell (12), the wedge-shaped part (621) is arranged along the circumference of the outer wall of the inner shell (12), the inner shell (12) is completely surrounded by the wedge-shaped part, the axial section of the Tesla valve is wedge-shaped, the front part of the section is oblique line with a certain angle with the outer wall of the inner shell (12), the angle is acute angle, the rear part is arc-shaped, two end points of the arc are respectively positioned at one point on the tail end of the oblique line and the outer wall of the inner shell (12), and the arc is recessed towards the oblique line direction; the cross section of the diversion cone (622) is streamline, the front part is circular arc, the diversion cone is concentric with the rear circular arc of the wedge-shaped component (621), the diversion cone gradually transits to a sharp angle backwards, and has a certain distance with the inner shell (12), the backflow channel flows from the annular combustion chamber (64) to the gas collection chamber (61), and the forward flow channel flows from the gas collection chamber (61) to the combustion chamber (64); the diversion cone (622) is fixedly connected with the outer wall of the inner shell (12) through fixing mechanisms which are uniformly arranged in the circumferential direction; the fuel cavity (63) is divided into an outer fuel cavity and an inner fuel cavity, and the outer fuel cavity is positioned on the inner wall of the outer shell (611) and protrudes inwards; the inner fuel cavity is positioned on the outer wall of the inner shell (12), protrudes outwards and is opposite to the outer fuel cavity; the axial section of the outer fuel cavity is a closed plane graph formed by a straight line and an arc, wherein the straight line is positioned on the outer surface of the outer shell (611) parallel to the axis of the engine, a rectangular hole is formed in the middle part of the closed graph, one side of the rectangular hole is positioned in the center of the straight line, the rectangular holes are distributed in a ring shape, the circle center of the ring-shaped rectangular hole coincides with the axis of the engine, and fuel is injected into the combustion chamber through a plurality of injection small holes arranged in the outer fuel cavity and comes from the mixer (34); the fuel supply pipes are arranged at the outer shell (611) and the inner shell (12), respectively; at the outer shell (611), a fuel supply pipeline enters the outer shell (611) from outside to inside through a through hole on the outer shell (611) and is directly connected with an outer fuel cavity; at the position of the inner shell (12), a fuel supply pipeline enters the inner shell (12) through another through hole on the outer shell (611), then the fuel supply pipeline is divided into three paths, one path is connected with a main combustion chamber (52) of the turbine engine through a first half through hole on the inner shell (12), the other path is sprayed into an afterburner (54) through a second half through hole on the inner shell (12), and the other path is connected with an inner combustion chamber through a third half through hole on the inner shell (12); an inner fuel cavity is arranged at the same axial position, and the shape and the fuel injection mode of the inner fuel cavity are completely the same as those of the outer fuel cavity; the annular combustion chamber (64) is positioned behind the fuel cavity (63) and is an annular cavity; a Laval nozzle (65) is located downstream of the annular combustion chamber (64); the high enthalpy product produced by the rotating detonation wave is discharged through a Laval nozzle (65).

2. The kerosene/liquid methane external parallel turbine-based rotary detonation engine of claim 1, wherein the actuation mechanism (23) is a hydraulic actuation mechanism.

3. The kerosene/liquid methane external parallel turbine-based rotary detonation engine of claim 1, wherein the conduit (312) uses two layers of "solenoids" and the cooling medium used in the conduit (312) is kerosene or liquid methane.

4. The kerosene/liquid methane external parallel turbine-based rotary detonation engine of claim 1, wherein the injection orifice has a bore diameter of 0.2mm, the injection orifice being perforated vertically from the rectangular bore to the combustion chamber.

5. The kerosene/liquid methane external parallel turbine-based rotary detonation engine of any of claims 1 to 4, characterized by the working method of:

when 0-3Ma flies, in order to reduce the flying resistance, the actuating mechanism (23) drives the regulating piece (21) to rotate inwards through the transmission rod (22) until the adjustable air inlet channel (2) is closed, external atmosphere only enters the turbine engine through the mixed pressure air inlet channel (1), after being compressed by a compressor in a multistage way, part of compressed gas enters the air collecting cavity (61) through the air entraining valve (4), and is fully mixed with fuel sprayed from the fuel cavity (63), the formed fresh mixture enters the annular combustion chamber (64), then the detonation system works, continuously rotating detonation waves are formed in the annular combustion chamber (64), the inflowing fresh mixture is continuously consumed, and combustion products expand downwards and are discharged through the Laval nozzle (65) to generate thrust; another portion of the compressed gas is continuously compressed by the latter stages of the compressor (51), and the subsequent process is the same as that of a conventional turbine engine;

3-6Ma, in order to keep the turbine engine performance, the bleed valve (4) is closed, the actuating mechanism (23) drives the adjusting piece (21) to rotate outwards through the transmission rod (22) until the adjustable air inlet channel (2) is completely opened; on the one hand, the external atmosphere enters the gas collection cavity (61) through the adjustable outer gas inlet channel (2) and is fully mixed with fuel sprayed from the fuel cavity (63), the formed fresh mixture enters the annular combustion chamber (64), then the detonation system works, continuously rotating detonation waves are formed in the annular combustion chamber (64), the inflowing fresh mixture is continuously consumed, combustion products expand downstream, and are discharged through the Laval nozzle (65) to generate thrust; the other part of external atmosphere enters the turbine engine through the mixed pressure type air inlet channel (1), and the inlet temperature before the air compressor (51) is higher due to higher incoming flow Mach number, at the moment, the cooling system (3) starts to work, and part of fuel starts to flow into the heat exchange pipeline, so that the temperature of the high-temperature air flow can be reduced after passing through the heat exchange pipeline, and the reliable and stable work of the air compressor is facilitated; on the other hand, kerosene or methane in the pipeline is heated and evaporated or cracked, the reaction activity is improved, the pipeline is divided into three paths after being mixed and cooled, one path enters a main combustion chamber (52) to participate in traditional isobaric combustion, the other path is injected into an annular combustion chamber (64) to participate in detonation combustion, and the other path is connected with an afterburner (54) to provide fuel when the afterburner is started.