A detonation and afterburner airflow separation exhaust device

Abstract

The present application belongs to the field of detonation turbine engine design, and is a device for separating detonation and afterburner airflow exhaust, comprising an inner nozzle, an outer nozzle, an inner regulating device, and an outer regulating device; when the detonation turbine engine is working, the high-temperature combustion gas in the afterburner combustion chamber enters the inner nozzle, the high-temperature combustion gas in the detonation combustion chamber enters the high-temperature combustion gas channel, and the outer cooling gas is divided into two streams and enters the first cooling channel and the second cooling channel respectively, cooling the wall surfaces of the outer nozzle and the inner nozzle. At the same time, the outer cooling gas in the first cooling channel and the second cooling channel enters the heat shield, so that the inner regulating device will not come into contact with the high-temperature combustion gas generated by the detonation combustion chamber, and at the same time, it is continuously cooled by the outer cooling gas, thereby minimizing the ambient temperature of the inner regulating device located in the outer high-temperature area, and effectively reducing the risk of ablation of the cylinder wall and the inner regulating device caused by the outer high-temperature area.

Description

Technical Field

[0001] The present application belongs to the field of detonation turbine engine design, and in particular relates to a detonation and afterburner airflow separation exhaust device. Background Art

[0002] With the development of science and technology, turbofan engine technology based on the Brayton cycle (i.e., isobaric cycle) has become very mature, and engine performance has reached a high level. Further improving engine performance within the framework of traditional engine cycles is very difficult. In recent years, researchers at home and abroad have been trying to find new cycles or combustion methods to achieve performance breakthroughs in traditional engines. Among them, the detonation cycle, with its high cycle efficiency and self-pressurization during the combustion process, has the advantages of higher cycle efficiency and better economy compared to traditional engines.

[0003] Detonation turbine engines generally utilize a detonation combustion and afterburner fusion technology. The afterburner is located in the inner duct, where incompletely burned oxygen from the core engine enters the afterburner and undergoes secondary isobaric combustion with the fuel. The detonation chamber is located in the outer duct of the turbofan engine. The outer duct air enters the detonation chamber and effectively mixes with the injected fuel, achieving efficient isochoric combustion through detonation, producing high-temperature, high-pressure gas. These two gases together generate thrust, achieving increased engine thrust. There are two design options for the exhaust of the two airflows: mixed exhaust and separate exhaust. Analysis and numerical calculations have shown that mixed exhaust can increase the pressure in the inner duct and deviate from the engine state. The separate exhaust option maximizes the capabilities of the two airflows, achieving maximum engine thrust.

[0004] The existing separate exhaust scheme is a double-layer nozzle structure, in which the outer nozzle is controlled by an actuator arranged on the outer wall of the outer nozzle, and the inner nozzle is controlled by an actuator arranged on the inner wall. This scheme is only suitable for the low-temperature outer channel of the traditional turbofan engine, but for the high-temperature outer channel of the outer detonation engine, it is easy to bring a greater ablation risk to the nozzle adjustment device arranged on the inner wall. Summary of the Invention

[0005] The purpose of the present application is to provide a detonation and afterburner airflow separate exhaust device to solve the problem in the prior art that separate exhaust easily leads to the risk of ablation of the nozzle adjustment device.

[0006] The technical solution of the present application is: a detonation and afterburner airflow separate exhaust device, comprising an inner nozzle, an outer nozzle, an inner regulating device, and an outer regulating device; the inner nozzle is connected to the afterburner combustion chamber, the outer nozzle is coaxially arranged on the outer side of the inner nozzle, the outer regulating device is arranged on the outer nozzle, and the inner regulating device is partially arranged on the inner nozzle; a heat insulation device is provided between the inner nozzle and the outer nozzle; the heat insulation device comprises an inner heat shield and an outer heat shield, a high-temperature gas channel is formed between the inner and outer heat shields, and high-temperature gas from the detonation combustion chamber can flow through the high-temperature gas channel; a first cooling channel is formed between the inner heat shield and the inner nozzle, and a second cooling channel is formed between the outer heat shield and the outer nozzle, and outer cooling gas can flow through the first and second cooling channels; a heat shield is provided in the high-temperature gas channel, the heat shield is sealed to both the inner and outer heat shields, the heat shield is connected to the first and second cooling channels, and the inner regulating device passes through the heat shield.

[0007] Preferably, the internal regulating device includes a power part, a transmission part and a driving part. The power part is arranged on the outer wall of the outer nozzle, the driving part is arranged on the outer wall of the inner nozzle, the transmission part is connected between the power part and the driving part and the transmission part passes through the heat insulation cover.

[0008] Preferably, the power component includes a first hydraulic actuator cylinder, and there are two groups of the first hydraulic actuator cylinders, which are symmetrically arranged on both sides of the outer culvert nozzle. The first hydraulic actuator cylinder is fixedly connected to the straight section of the outer culvert. The transmission component includes an outer rocker arm, a transmission shaft, an inner rocker arm and a motion valve. The transmission shaft is inserted into the heat insulation cover along the radial direction of the aircraft engine. The outer rocker arm is fixedly connected between the first hydraulic actuator cylinder and the transmission shaft, the inner rocker arm is fixedly connected between the motion valve and the transmission shaft, and the motion valve is coaxially slidably connected to the outside of the inner culvert nozzle.

[0009] Preferably, a guide block arranged along the axial direction of the aircraft engine is provided on the outer side wall of the inner nozzle, and a guide groove slidingly matched with the guide block is provided on the inner side wall of the motion valve.

[0010] Preferably, there are multiple groups of driving members and they are evenly distributed along the circumference of the inner nozzle. The driving members include a first connecting rod and a second connecting rod. One end of the first connecting rod is fixedly connected to the transmission member and the other end is hinged to the second connecting rod. The end of the second connecting rod away from the first connecting rod is hinged to the inner convergence section of the inner nozzle.

[0011] Preferably, there are multiple groups of the outer culvert adjustment devices and they are evenly spaced along the circumference of the outer culvert nozzle. The outer culvert adjustment device includes a second hydraulic actuator and a third connecting rod. The second hydraulic actuator is fixedly connected to the straight section of the outer culvert. One end of the third connecting rod is hinged to the piston rod of the second hydraulic actuator, and the other end is hinged to the convergent section of the outer culvert.

[0012] Preferably, the outer heat insulation screen is inclined inward at a position corresponding to the outer duct convergent section of the outer duct nozzle to form a convergent heat insulation screen, a convergent cooling channel is formed between the convergent heat insulation screen and the outer duct convergent section, the convergent cooling channel is connected with the second cooling channel, a convergent exhaust channel is formed between the convergent heat insulation screen and the inner heat insulation screen, the convergent exhaust channel is connected with the high-temperature fuel gas channel, an expansion exhaust channel is formed between the outer duct expansion section and the inner heat insulation screen, the high-temperature fuel gas in the convergent exhaust channel and the outer duct cooling gas in the convergent cooling channel are mixed in the expansion exhaust channel and then discharged at an accelerated rate.

[0013] The present application discloses a detonation and afterburner airflow separation exhaust device, comprising an inner nozzle, an outer nozzle, an inner regulating device, and an outer regulating device. When the detonation turbine engine is operating, the high-temperature combustion gas in the afterburner combustion chamber enters the inner nozzle, the high-temperature combustion gas in the detonation combustion chamber enters the high-temperature combustion gas channel, and the outer cooling gas is divided into two streams and enters the first cooling channel and the second cooling channel respectively, cooling the walls of the outer nozzle and the inner nozzle. At the same time, the outer cooling gas in the first cooling channel and the second cooling channel enters the heat shield, so that the inner regulating device will not come into contact with the high-temperature combustion gas generated by the detonation combustion chamber, and is continuously cooled by the outer cooling gas, thereby minimizing the ambient temperature of the inner regulating device located in the outer high-temperature area, and effectively reducing the risk of ablation of the cylinder wall and the inner regulating device caused by the outer high-temperature area. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0015] Figure 1 This is a schematic diagram of the overall cross-sectional structure of this application;

[0016] Figure 2 An axonometric view of the connotative nozzle highlighting the connotative adjustment device for this application;

[0017] Figure 3 An axonometric view of the culvert nozzle highlighting the culvert adjustment device for this application.

[0018] 1. Inner nozzle; 2. Outer nozzle; 3. Outer straight section; 4. Outer convergent section; 5. Inner convergent section; 6. Inner heat shield; 7. Outer heat shield; 8. First cooling channel; 9. Second cooling channel; 10. First hydraulic actuator; 11. Outer rocker arm; 12. Drive shaft; 13. Inner rocker arm; 14. Motion valve; 15. Heat shield; 16. First connecting rod; 17. Second connecting rod; 18. Second hydraulic actuator; 19. Third connecting rod; 20. Convergent cooling channel; 21. Convergent exhaust channel; 22. Divergent exhaust channel. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0020] A detonation, afterburner airflow separation exhaust device, such as Figure 1-3 As shown, the endotube nozzle 1 comprises an endotube nozzle 2, an endotube regulating device, and an endotube regulating device. The endotube nozzle 1 is connected to the afterburner and is used to discharge the high-temperature combustion gas in the afterburner. The endotube nozzle 2 is coaxially arranged outside the endotube nozzle 1 and is used to discharge the external cooling gas and the high-temperature combustion gas in the detonation combustion chamber. The endotube nozzle 1 comprises an endotube straight section, an endotube convergent section 5, and an endotube divergent section, respectively. The endotube nozzle 2 comprises an endotube straight section 3, an endotube convergent section 4, and an endotube divergent section, respectively. The structures of the endotube nozzle 1 and the endotube nozzle 2 are both conventional and will not be described in detail here.

[0021] The outer culvert regulating device is arranged on the outer culvert nozzle 2, and the inner culvert regulating device is partially arranged on the inner culvert nozzle 1; a heat insulation device is arranged between the inner culvert nozzle 1 and the outer culvert nozzle 2.

[0022] The heat insulation device includes an inner heat insulation screen 6 and an outer heat insulation screen 7. A high-temperature gas channel is formed between the inner heat insulation screen 6 and the outer heat insulation screen 7. High-temperature gas from the detonation combustion chamber can flow through the high-temperature gas channel. A first cooling channel 8 is formed between the inner heat insulation screen 6 and the inner nozzle 1. A second cooling channel 9 is formed between the outer heat insulation screen 7 and the outer nozzle 2. The outer cooling gas can flow through the first cooling channel 8 and the second cooling channel 9.

[0023] A heat shield 15 is provided in the high-temperature gas channel. The heat shield 15 is sealedly connected to the inner heat shield 6 and the outer heat shield 7. The heat shield 15 is connected to the first cooling channel 8 and the second cooling channel 9. The internal regulating device passes through the heat shield 15.

[0024] The thermal insulation device allows for the separate exhaust of high-temperature combustion gases and duct cooling gas. During detonation turbine engine operation, high-temperature combustion gases in the afterburner chamber enter the inner nozzle 1, while those in the detonation chamber enter the high-temperature gas channel. These gases avoid contact with the outer surface of the inner nozzle 1 and do not affect the inner wall of the inner nozzle 1. The duct cooling gas is split into two streams and enters the first cooling channel 8 and the second cooling channel 9, respectively, cooling the outer nozzle 2 and inner nozzle 1 walls. Simultaneously, the outer cooling gas in the first cooling channel 8 and the second cooling channel 9 enters the thermal insulation shield 15. This prevents the inner regulating device from contacting the high-temperature combustion gases generated by the detonation chamber while simultaneously being continuously cooled by the outer cooling gas. This minimizes the ambient temperature of the inner regulating device located in the outer high-temperature region, effectively reducing the risk of ablation of the cylinder wall and the inner regulating device caused by the outer high-temperature region. This approach offers low technical risk and meets engineering requirements.

[0025] Preferably, the shape of the heat shield 15 can be circular or racetrack-shaped.

[0026] Preferably, the endotube adjustment device includes a power component, a transmission component, and a drive component. The power component is located on the outer wall of the outer endotube nozzle 2, and the drive component is located on the outer wall of the endotube nozzle 1. The transmission component is connected between the power component and the drive component and passes through the heat shield 15. In this way, the endotube cooling air can effectively cool the transmission component and the drive component at various positions, effectively adjusting the endotube convergent section 5 of the endotube nozzle 1 while ensuring the working state of the endotube adjustment device.

[0027] Preferably, the power component includes a first hydraulic actuator 10, and there are two groups of the first hydraulic actuator 10 and they are symmetrically arranged on both sides of the outer culvert nozzle 2. The first hydraulic actuator 10 is fixedly connected to the outer culvert straight section 3. The transmission component includes an outer rocker arm 11, a transmission shaft 12, an inner rocker arm 13 and a motion valve 14. The transmission shaft 12 is inserted into the heat insulation cover 15 along the radial direction of the aircraft engine. The outer rocker arm 11 is fixedly connected between the first hydraulic actuator 10 and the transmission shaft 12. The inner rocker arm 13 is fixedly connected between the motion valve 14 and the transmission shaft 12. The motion valve 14 is coaxially slidably connected to the outside of the inner culvert nozzle 1.

[0028] By providing two sets of first hydraulic actuators, axial displacement is stably output to the drive shaft 12 via the outer rocker arm 11. The outer rocker arm 11 and drive shaft 12 are splined together. The drive shaft 12 controls the axial displacement of the motion valve 14 via the inner rocker arm 13. The axial displacement of the motion valve 14 can be controlled by controlling the length of the inner rocker arm 13. The motion valve 14 then controls the movement of the inner nozzle 1 via a driver. By designing the transmission components that pass through the heat shield 15 and the first hydraulic actuator 10 located on the outer nozzle 2, the number and complexity of the inner regulating devices within the outer channel can be minimized, facilitating cooling of the regulating devices.

[0029] Preferably, a guide block is provided on the outer sidewall of the inner nozzle 1, arranged along the axial direction of the aircraft engine, and a guide groove is provided on the inner sidewall of the motion valve 14, which slides with the guide block. The provision of the guide block and the guide groove can prevent the motion valve 14 from deflecting and rotating during axial movement.

[0030] Preferably, there are multiple groups of driving parts and they are evenly distributed along the circumference of the internal nozzle 1. The driving parts include a first connecting rod 16 and a second connecting rod 17. One end of the first connecting rod 16 is fixedly connected to the transmission part and the other end is hinged to the second connecting rod 17. The end of the second connecting rod 17 away from the first connecting rod 16 is hinged to the internal convergence section 5 of the internal nozzle 1, which is simple to drive and stable to control.

[0031] Preferably, there are multiple groups of outer culvert adjustment devices and they are evenly spaced along the circumference of the outer culvert nozzle 2. The outer culvert adjustment device includes a second hydraulic actuator 18 and a third connecting rod 19. The second hydraulic actuator 18 is fixedly connected to the outer culvert straight section 3. One end of the third connecting rod 19 is hinged to the piston rod of the second hydraulic actuator 18, and the other end is hinged to the outer culvert convergence section 4. The drive is simple and the control is stable.

[0032] Preferably, the outer heat insulation screen 7 is inclined inward at a position corresponding to the outer culvert convergent section 4 of the outer culvert nozzle 2 to form a convergent heat insulation screen, a convergent cooling channel 20 is formed between the convergent heat insulation screen and the outer culvert convergent section 4, the convergent cooling channel 20 is connected to the second cooling channel 9, a convergent exhaust channel 21 is formed between the convergent heat insulation screen and the inner heat insulation screen 6, the convergent exhaust channel 21 is connected to the high-temperature gas channel, an expansion exhaust channel 22 is formed between the outer culvert expansion section and the inner heat insulation screen 6, the high-temperature gas in the convergent exhaust channel 21 and the outer culvert cooling gas in the convergent cooling channel 20 are mixed in the expansion exhaust channel 22 and then discharged at an accelerated rate.

[0033] The high-temperature combustion gas and the outer cooling gas in the second channel are narrowed and pressurized at the convergent exhaust channel 21 and the convergent cooling channel 20 respectively, and then the channels are expanded at the divergent exhaust channel 22 so as to be discharged quickly, forming an exhaust structure similar to a nozzle with high exhaust efficiency.

[0034] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A detonation and afterburner airflow separation exhaust device, characterized by: The invention comprises an inner nozzle (1), an outer nozzle (2), an inner regulating device and an outer regulating device; the inner nozzle (1) is connected to the afterburner, the outer nozzle (2) is coaxially arranged on the outside of the inner nozzle (1), the outer regulating device is arranged on the outer nozzle (2), and the inner regulating device is partially arranged on the inner nozzle (1); a heat insulation device is provided between the inner nozzle (1) and the outer nozzle (2); The heat insulation device comprises an inner heat insulation screen (6) and an outer heat insulation screen (7), a high-temperature gas channel is formed between the inner heat insulation screen (6) and the outer heat insulation screen (7), and the high-temperature gas channel can flow through the high-temperature gas from the detonation combustion chamber, a first cooling channel (8) is formed between the inner heat insulation screen (6) and the inner nozzle (1), and a second cooling channel (9) is formed between the outer heat insulation screen (7) and the outer nozzle (2), and the outer cooling gas can flow through the first cooling channel (8) and the second cooling channel (9); A heat shield (15) is provided in the high-temperature gas channel. The heat shield (15) is sealedly connected to the inner heat shield (6) and the outer heat shield (7). The heat shield (15) is communicated with the first cooling channel (8) and the second cooling channel (9). The internal regulating device passes through the heat shield (15).

2. The detonation and afterburner airflow separation exhaust device according to claim 1, characterized in that: The inner regulating device comprises a power part, a transmission part and a driving part, wherein the power part is arranged on the outer side wall of the outer nozzle (2), the driving part is arranged on the outer side wall of the inner nozzle (1), the transmission part is connected between the power part and the driving part and the transmission part passes through the heat insulation cover (15).

3. The detonation and afterburner airflow separation exhaust device according to claim 2, characterized in that: The power component includes a first hydraulic actuator (10), and there are two groups of the first hydraulic actuator (10) symmetrically arranged on both sides of the outer culvert nozzle (2). The first hydraulic actuator (10) is fixedly connected to the outer culvert straight section (3). The transmission component includes an outer rocker arm (11), a transmission shaft (12), an inner rocker arm (13) and a motion valve (14). The transmission shaft (12) is inserted into the heat shield (15) along the radial direction of the aircraft engine. The outer rocker arm (11) is fixedly connected between the first hydraulic actuator (10) and the transmission shaft (12). The inner rocker arm (13) is fixedly connected between the motion valve (14) and the transmission shaft (12). The motion valve (14) is coaxially slidably connected to the outer side of the inner culvert nozzle (1).

4. The detonation and afterburner airflow separation exhaust device according to claim 3, characterized in that: A guide block arranged along the axial direction of the aircraft engine is provided on the outer side wall of the inner nozzle (1), and a guide groove slidingly matched with the guide block is provided on the inner side wall of the motion valve (14).

5. The detonation and afterburner airflow separation exhaust device according to claim 2, characterized in that: There are multiple groups of driving members and they are evenly arranged along the circumference of the inner nozzle (1). The driving members include a first connecting rod (16) and a second connecting rod (17). One end of the first connecting rod (16) is fixedly connected to the transmission member and the other end is hinged to the second connecting rod (17). The end of the second connecting rod (17) away from the first connecting rod (16) is hinged to the inner convergence section (5) of the inner nozzle (1).

6. The detonation and afterburner airflow separation exhaust device according to claim 1, characterized in that: There are a plurality of outer culvert adjustment devices which are evenly spaced along the circumference of the outer culvert nozzle (2). The outer culvert adjustment device comprises a second hydraulic actuator (18) and a third connecting rod (19). The second hydraulic actuator (18) is fixedly connected to the outer culvert straight section (3). One end of the third connecting rod (19) is hinged to the piston rod of the second hydraulic actuator (18), and the other end is hinged to the outer culvert convergent section (4).

7. The detonation and afterburner airflow separation exhaust device according to claim 1, characterized in that: The outer heat insulation screen (7) is inclined inwardly at a position corresponding to the outer converging section (4) of the outer converging nozzle (2) to form a convergent heat insulation screen. A convergent cooling channel (20) is formed between the convergent heat insulation screen and the outer converging section (4). The convergent cooling channel (20) is connected to the second cooling channel (9). A convergent exhaust channel (21) is formed between the convergent heat insulation screen and the inner heat insulation screen (6). The convergent exhaust channel (21) is connected to the high-temperature gas channel. An expansion exhaust channel (22) is formed between the outer converging section and the inner heat insulation screen (6). The high-temperature gas in the convergent exhaust channel (21) and the outer converging cooling gas in the convergent cooling channel (20) are mixed in the expansion exhaust channel (22) and then discharged at an accelerated rate.

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