Double-pipe combined auxiliary power combustion chamber, aircraft and using method

Abstract

The invention relates to the technical field of aero-engines, in particular to a double-pipe combined auxiliary power combustion chamber, an aircraft and a using method. A double-pipe combined auxiliary power combustion chamber comprises a combustion chamber casing, a combustion chamber and a combustion chamber, the flame tube set is arranged in the containing space, the flame tube set comprises a first flame tube and a second flame tube, the second flame tube is suitable for containing fuel gas, and a second gas outlet of the second flame tube communicates with the first flame tube; or the first flame tube is suitable for containing fuel gas, and the first gas outlet of the first flame tube communicates with the second flame tube. The invention provides a double-tube combined auxiliary power combustion chamber, an aircraft and a using method, and aims to solve the problems that an APU flame tube of the auxiliary combustion chamber and an EPU flame tube under an EPU working condition are separately designed, fuel gas enters the EPU flame tube and occupies a part of volume in the EPU flame tube, the EPU flame tube occupies a large volume due to mixed combustion expansion, and the combustion efficiency is low. The auxiliary combustion chamber is large in size.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular to a double-pipe combined auxiliary power combustion chamber, an aircraft and a use method. BACKGROUND

[0002] With the increasing complexity and functionality of modern military and civilian aircraft electronics and electrical equipment, and the widespread use of high-thrust / power aero-engines, the auxiliary power system has become an indispensable second power system on the aircraft. The second power system is mainly used to start the main engine and provide a compressed air source for the aircraft environmental control system, drive the aircraft hydraulic pump, generator to provide a hydraulic source, power source, etc. for the aircraft. The traditional second power system mechanically drives or air pressure drives the main engine, and uses two independent turbine power devices (APU+EPU), generators and hydraulic pumps as loads. Among them, the APU usually provides secondary energy for the aircraft below 12000m for a long time or provides starting energy for the engine below 6000m, with a high use frequency, and the ratio of running time / aircraft flight time has reached 0.8. The EPU provides emergency attitude control secondary energy for the aircraft within the full envelope range of the aircraft, for a short time, and quickly uses hydrazine fuel.

[0003] The initially integrated combined auxiliary power device (IPU) is obtained by physically combining the EPU and the APU on the same gear box, canceling the gear box, hydraulic pump, controller and generator of the EPU, thereby reducing the complexity of the entire system, but the two still need independent combustion chambers and turbines. The integrated IPU can realize the APU working mode and the EPU working mode through mode switching. The APU working mode (EPU inlet closed), the high-temperature and high-pressure air supplied from the compressor enters the combustion chamber and mixes with the fuel to burn, and then the high-temperature and high-pressure gas flows through the turbine to do work, thereby realizing the APU working mode function. The EPU working mode (APU inlet closed), the gas supplied from the EPU inlet pipe enters the combustion chamber to burn, and then the high-temperature and high-pressure gas flows through the turbine to do work, thereby realizing the EPU working mode function.

[0004] Further integration is that APU and EPU share the same combustion chamber and turbine, the original independent APU and EPU two combustion chambers are integrated into a double-mode combustion chamber, and the original APU turbine and EPU turbine are shared, so that the APU has the emergency function of the EPU and saves a set of EPU combustion chamber and turbine, further reducing the volume and weight, forming a super combined auxiliary power unit (SIPU). SIPU greatly optimizes the system structure and can start the main engine, provide emergency power and other functions in the full flight envelope. When the main engine stops working at high altitude beyond the APU working envelope, the EPU mode starts to work and provides emergency power to the aircraft, and when the flight height of the aircraft drops to the working envelope of the APU mode, the on-board high-pressure air bottle stops supplying air, and at the same time the compressor inlet guide vane and outlet damper are opened. Air enters to work in APU mode.

[0005] The existing auxiliary combustion chamber often designs the APU flame tube under APU working condition and the EPU flame tube under EPU working condition separately, and in the EPU working condition, the EPU flame tube will enter the gas, the gas will occupy a part of the volume in the EPU flame tube, and the gas mixed with high-pressure air burns and expands to make the EPU flame tube occupy a larger volume, so that the auxiliary combustion chamber has a larger volume. SUMMARY

[0006] The application provides a double-tube combined auxiliary power combustion chamber, an aircraft and a use method, to solve the problem that the auxiliary combustion chamber designs the APU flame tube under APU working condition and the EPU flame tube under EPU working condition separately, in the EPU working condition, the EPU flame tube will enter the gas, the gas will occupy a part of the volume in the EPU flame tube, and the gas mixed with high-pressure air burns and expands to make the EPU flame tube occupy a larger volume, so that the auxiliary combustion chamber has a larger volume.

[0007] In a first aspect, the application provides a double-tube combined auxiliary power combustion chamber, comprising: A combustion chamber case, the combustion chamber case has a containing space; A flame tube group is arranged in the containing space, the flame tube group comprises a first flame tube and a second flame tube, the first flame tube is suitable for containing gas, and a first gas outlet of the first flame tube is in communication with the second flame tube.

[0008] Combustion gas enters the second flame tube. After ignition, a chemical reaction occurs, releasing heat. Since combustion takes time, the gas in the second flame tube, while undergoing the chemical reaction, simultaneously enters the first flame tube through the second outlet to continue the remaining combustion and heat release process. Connecting the outlet of the second flame tube to the first flame tube effectively utilizes the space within the first flame tube, thereby reducing the volume of the second flame tube and the overall volume of the combustion chamber casing, which in turn helps to reduce the weight and cost of the combustion chamber.

[0009] In one optional embodiment, the combustion chamber casing includes a front casing flange, an outer casing housing, and an inner casing housing. The flame tube assembly is partially disposed within the space formed by the outer casing housing and the inner casing housing. A front casing flange is provided on one side of the outer casing housing, and the front casing flange is adapted to be connected to a compressor.

[0010] In one optional embodiment, the combustion chamber casing further includes a gas collecting ring assembly, which includes a gas collecting space, a compressed air intake port, and a gas collecting casing. The gas collecting casing is fitted around the outer periphery of the outer casing housing. A compressed air intake port is provided at the connection between the gas collecting space and the receiving space. A first gas collecting hole is provided inside the outer casing housing, and the first gas collecting hole communicates with the gas collecting space.

[0011] In one optional embodiment, the combustion chamber casing further includes a dual-tube casing assembly, the dual-tube casing assembly including a dual-tube casing housing, the dual-tube casing housing being connected to the compressor intake port and the outer casing housing respectively, and the portion of the flame tube assembly exposed in the outer casing housing being disposed within the space formed by the dual-tube casing housing and the outer casing housing.

[0012] In one optional embodiment, the combustion chamber casing further includes a swirl connecting section disposed within the space formed by the outer casing housing and the inner casing housing. One end of the swirl connecting section is connected to the first exhaust port, and the other end of the swirl connecting section is adapted to be connected to the turbine intake end.

[0013] In one optional embodiment, the device further includes a fuel nozzle, a gas nozzle, a first ignition nozzle, and a second ignition nozzle. The fuel nozzle and the first ignition nozzle pass through the dual-tube casing and are connected to the first flame tube, respectively. The gas nozzle and the second ignition nozzle pass through the dual-tube casing and are connected to the second flame tube, respectively.

[0014] In one optional embodiment, the first flame tube includes a first inner ring plate, a first outer ring plate, a first side plate, and a second side plate, wherein the first inner ring plate, the first outer ring plate, the first side plate, and the second side plate form a first combustion space.

[0015] In one optional embodiment, the compressor includes a compressor housing and an air intake pipe, the compressor housing being connected to the front flange of the casing, and the air intake pipe being in communication with the compressor housing.

[0016] Secondly, the present invention also provides an aircraft including the aforementioned dual-tube combined auxiliary power combustion chamber.

[0017] Thirdly, the present invention also provides a method for using a dual-tube combined auxiliary power combustion chamber. Under EPU operating conditions, gas enters the second flame tube. After the gas is ignited, the gas in the second flame tube enters the first flame tube through the second gas outlet. Attached Figure Description

[0018] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0019] Figure 1 This is a front view of the dual-tube combined auxiliary power combustion chamber according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the internal structure of the dual-tube combined auxiliary power combustion chamber according to an embodiment of the present invention; Figure 3 for Figure 1 Cross-sectional view of AA; Figure 4 This is a schematic diagram of the first flame tube according to an embodiment of the present invention; Figure 5 This is a three-dimensional schematic diagram of the first flame tube according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the swirl connection section according to an embodiment of the present invention; Figure 7 This is another schematic diagram of the swirl connection section according to an embodiment of the present invention; Figure 8 This is a schematic diagram of the dual-tube combined auxiliary power combustion chamber under APU no-load conditions according to an embodiment of the present invention; Figure 9 This is a schematic diagram of the dual-tube combined auxiliary power combustion chamber of the present invention under APU no-load conditions, according to another angle. Figure 10 This is a schematic diagram of the dual-tube combined auxiliary power combustion chamber under EPU operating conditions according to an embodiment of the present invention.

[0020] Explanation of reference numerals in the attached drawings: 1. Combustion chamber casing; 11. Gas collecting ring assembly; 111. Compressed air intake port; 112. Gas collecting space; 113. Gas collecting casing; 12. Dual-tube casing assembly; 121. Main engine intake port; 122. First electric nozzle mounting base; 123. First nozzle mounting base; 124. Second electric nozzle mounting base; 125. Second nozzle mounting base; 13. Outer casing housing; 131. Casing front flange; 132. First gas collecting port; 14. Inner casing housing; 15. Swirl connection section; 151. Swirl mounting hole; 152. Outer adapter ring; 153. Adapter part; 154. Inner adapter ring; 155. Outer support ring; 156. Film cooling hole; 16. Receiving space; 2. Flame tube assembly; 21. First flame tube assembly. 211. Flame tube; 212. First guide vane; 213. First vortex generator; 214. First side plate; 2131. Side plate main combustion port; 2132. Side plate mixing port; 2133. Side plate cooling port; 215. First outer ring plate; 216. Cap; 217. First exhaust port; 218. Small bend pipe; 219. First ignition nozzle port; 22. Second flame tube; 221. Second exhaust port; 3. Turbine; 4. First ignition nozzle; 5. Fuel nozzle; 6. Second ignition nozzle; 7. Gas nozzle; 8. Compressor; 81. Compressor rear flange; 82. Air intake pipe; 83. Axial diffuser. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] The following is combined with Figures 1 to 10 The following describes embodiments of the present invention.

[0023] According to an embodiment of the present invention, in one aspect, a dual-tube combined auxiliary power combustion chamber is provided, comprising: a combustion chamber housing 1, the combustion chamber housing 1 having a receiving space 16; and a flame tube assembly 2 disposed within the receiving space 16, the flame tube assembly 2 including a first flame tube 21 and a second flame tube 22, the second flame tube 22 being adapted to contain combustion gas, and a second outlet 221 of the second flame tube 22 communicating with the first flame tube 21.

[0024] Combustion gas enters the second flame tube 22. After ignition, a chemical reaction occurs, releasing heat. Since combustion takes time, the gas in the second flame tube 22, while undergoing the chemical reaction, enters the first flame tube 21 through the second outlet 221 to continue the remaining combustion and heat release process. Connecting the outlet of the second flame tube 22 to the first flame tube 21 effectively utilizes the space within the first flame tube 21, thereby reducing the volume of the second flame tube 22 and the overall volume of the combustion chamber casing 1, which in turn helps to reduce the weight and cost of the combustion chamber.

[0025] In one embodiment, such as Figure 1 , Figure 2 and Figure 3 As shown, the combustion chamber casing 1 includes a front casing flange 131, an outer casing housing 13, and an inner casing housing 14. The flame tube assembly 2 is partially disposed within the space formed by the outer casing housing 13 and the inner casing housing 14. The front casing flange 131 is provided on one side of the outer casing housing 13, and the front casing flange 131 is adapted to be connected to the compressor 8. In this embodiment, the front casing flange 131 is connected to the compressor rear flange 81 to realize the connection between the combustion chamber casing 1 and the compressor 8.

[0026] In one embodiment, such as Figure 1 , Figure 2 and Figure 3 As shown, the combustion chamber casing 1 also includes a gas collecting ring assembly 11, which is disposed within the receiving space 16. The gas collecting ring assembly 11 includes a gas collecting space 112, a compressed air intake port 111, and a gas collecting casing 113. The gas collecting casing 113 is fitted around the outer periphery of the outer casing shell 13. A compressed air intake port 111 is provided at the connection between the gas collecting space 112 and the receiving space 16. A first gas collecting hole 132 is provided inside the outer casing shell 13, and the first gas collecting hole 132 communicates with the gas collecting space 112. This allows the receiving space 16 and the gas collecting space 112 within the outer casing shell 13 to communicate. Gas enters the gas collecting space 112 through the first gas collecting hole 132, and then enters the receiving space 16 from the gas collecting space 112 through the compressed air intake port 111.

[0027] In one embodiment, such as Figure 1 , Figure 2 and Figure 3 As shown, the combustion chamber casing 1 also includes a dual-tube casing assembly 12. The dual-tube casing assembly 12 includes a dual-tube casing housing, which is connected to the compressed air intake port 111 and the outer casing housing 13. The portion of the flame tube assembly 2 exposed outside the outer casing housing 13 is located within the space formed by the dual-tube casing housing and the outer casing housing 13, so as to accommodate the flame tube assembly 2. To realize the control of the air volume and opening and closing of the compressed air intake port 111, a control valve is provided at the compressed air intake port 111 to realize the opening, closing and air volume control of the compressed air intake port 111.

[0028] In one embodiment, such as Figure 1 , Figure 2 and Figure 3 As shown, the combustion chamber casing 1 also includes a swirl connecting section 15, which is disposed within the space formed by the outer casing housing 13 and the inner casing housing 14. One end of the swirl connecting section 15 is connected to the first exhaust port 217, and the other end of the swirl connecting section 15 is adapted to connect to the intake end of the turbine 3. The swirl connecting section 15 is used to transfer the gas ejected from the flame tube through the intake end of the turbine 3 into the turbine 3.

[0029] In this embodiment, as Figure 6 , Figure 7 As shown, the swirl connection section 15 includes an outer adapter ring 152, an adapter portion 153, an inner adapter ring 154, an outer support ring 155, a swirl mounting hole 151, and a film cooling hole 156, wherein the film cooling hole 156 is formed by the gap between the outer adapter ring 152 and the adapter portion 153.

[0030] In one embodiment, such as Figure 1 , Figure 2 As shown, it also includes a fuel nozzle 5, a gas nozzle 7, a first ignition nozzle 4, and a second ignition nozzle 6. The fuel nozzle 5 and the first ignition nozzle 4 pass through the double-tube casing and are connected to the first flame tube 21. The gas nozzle 7 and the second ignition nozzle 6 pass through the double-tube casing and are connected to the second flame tube 22. Figure 2 As shown, the dual-tube casing is provided with a first nozzle mounting seat 123, a second nozzle mounting seat 125, a first electric nozzle mounting seat 122, and a second electric nozzle mounting seat 124. The first nozzle mounting seat 123 is fixedly connected to the fuel nozzle 5, the second nozzle mounting seat 125 is fixedly connected to the gas nozzle 7, the first electric nozzle mounting seat 122 is fixedly connected to the first ignition electric nozzle 4, and the second electric nozzle mounting seat 124 is fixedly connected to the second ignition electric nozzle 6.

[0031] In one embodiment, such as Figure 1 , Figure 2 , Figure 4 and Figure 5 As shown, the first flame tube 21 includes a first inner ring plate 215, a first outer ring plate 214, a first side plate 213 and a second side plate. The first inner ring plate 215, the first outer ring plate 214, the first side plate 213 and the second side plate form a first combustion space, which is used to accommodate fuel injected from the fuel nozzle 5.

[0032] In this embodiment, as Figure 2 , Figure 4 , Figure 5 , Figure 9 and Figure 10As shown, the first flame tube 21 also includes an inner ring guide plate, a vortex generator, a cap, a small bend 218, and a first electric nozzle hole 219. The first side plate 213 and the second side are correspondingly arranged, the first inner ring plate 215 and the first outer ring plate 214 are correspondingly arranged, the first electric nozzle hole 219 is located on the first outer ring plate 214, the vortex generator communicates with the first combustion space, and the fuel nozzle 5 communicates with the vortex generator. In this embodiment, as... Figure 4 , Figure 5 As shown, the first outer ring plate 214 is provided with a first outer ring main combustion hole 2141, a first outer ring mixing hole 2142, and a first outer ring cooling hole 2143; the first side plate 213 and the second side are respectively provided with a side plate main combustion hole 2131, a side plate cooling hole 2133, and a side plate mixing hole 2132; the first inner ring plate 215 is provided with a first inner ring main combustion hole, a first inner ring mixing hole, and a first inner ring cooling hole. In this embodiment, as... Figure 4 As shown, the end of the first flame tube 21 away from the cap is the first air outlet 217.

[0033] In this embodiment, as Figure 2 As shown, the second flame tube 22 includes a third side plate, a fourth side plate, a second outer ring plate, and a second inner ring plate. The third and fourth side plates are correspondingly arranged, as are the second outer and second inner ring plates. The third side plate, fourth side plate, second outer ring plate, and second inner ring plate form a second combustion space, which is connected to the gas nozzle 7. A second electric nozzle hole is provided on the second outer ring plate. In this embodiment, the second gas outlet 221 of the second flame tube 22 is connected to the first inner ring plate 215 of the first flame tube 21, and the second flame tube 22 is provided with cooling holes.

[0034] In one embodiment, such as Figure 3 , Figure 8 As shown, the compressor 8 includes a compressor housing and an air intake pipe 82. The compressor housing is connected to the front flange 131 of the casing, and the air intake pipe 82 is connected to the compressor housing.

[0035] According to an embodiment of the present invention, another aspect provides an aircraft including the aforementioned dual-tube combined auxiliary power combustion chamber.

[0036] A method for using a dual-tube combined auxiliary power combustion chamber, with four operating conditions: APU no-load, APU loaded, EPU loaded, and main generator loaded, includes the following steps: (1) Under APU no-load conditions, such as Figure 8 , Figure 9As shown, all the high-pressure air from the compressor 8 enters the combustion chamber casing 1 through the channel between the axial diffuser 83 and the outer casing 13. The high-pressure air enters the gas collecting ring assembly 11 through multiple axially arranged first gas collecting holes 132. After being rectified by the gas collecting ring and the front side plate and concentrated into the compressor intake port 111, the high-pressure air enters the dual-tube casing assembly 12. Then, the high-pressure air is divided into three streams and enters the flame tube: The first stream of high-pressure air enters the first flame tube 21 from the outer ring main combustion hole, outer ring mixing hole, outer ring cooling hole, side plate main combustion hole 2131, side plate mixing hole 2132, side plate cooling hole 2133, and small bend pipe 218 cooling hole. The second stream of high-pressure air enters the interior of the second flame tube 22 through the cooling hole; The third stream of high-pressure air enters the interior of the flame tube assembly 2 through the film cooling hole 156 of the swirl transition section; The second high-pressure air enters the second flame tube 22 and then enters the first flame tube 21 from the inner ring main combustion hole, the inner ring cooling hole and the second air outlet 221 to mix with the first high-pressure air. After mixing, it enters the swirl transition section and is cooled by the third high-pressure air. High-pressure air enters the second flame tube 22 through the cooling hole and does not participate in combustion. It enters the first flame tube 21 through the second outlet 221 and the outer ring main combustion hole of the second flame tube 22. The side plate main combustion hole 2131, the external main combustion hole and the inner ring main combustion hole divide the flow field in the first flame tube 21 into a recirculation area. The atomized aviation kerosene mixes with the high-pressure air swirled in by the fuel nozzle 5 and the vortex and enters the recirculation area. It is then ignited by the first ignition nozzle 4 to produce high-temperature gas. High-pressure air passes through the side plate mixing hole 2132, the outer ring mixing hole, and the second outlet 221 to further divide the flow field inside the first flame tube 21 into a mixing region, mixing the high-temperature gas in the recirculation region. The mixed gas enters the swirl connection section 15 along the first outlet 217, and then enters the turbine 3 to do work. The airflow from the side cooling holes, outer ring cooling holes, inner ring cooling holes, small bend pipe 218 cooling holes, and air film cooling holes 156 is used to cool their respective walls. (2) Under APU load conditions, part of the high-pressure air from the compressor 8 enters the accommodating space 16 of the combustion chamber casing 1 through the channel between the axial diffuser 83 and the outer casing 13. The flow pattern of this part of the high-pressure air is consistent with the flow pattern of the APU no-load mode. The other part of the high-pressure air flows out from the compressor volute and the bleed pipe 82 in sequence to provide bleed air to the engine, so as to realize the function of starting the engine or the environmental control. (3) Under EPU operating conditions, the premixed gas supplied by the gas tank is injected into the second flame tube 22 from the gas nozzle 7 and then ignited by the second ignition nozzle 6 to generate high-temperature gas. The high-temperature gas is blocked by the first inner ring plate 215 of the first flame tube 21, forming a super-large ring vortex in the first flame tube 21 for flame stabilization and gas combustion. The high-temperature gas generated by combustion enters the swirl transfer section from the first outlet 217 and enters the turbine 3 to do work. Under EPU load mode, a small amount of high-pressure air is allowed to be introduced from the main engine intake port 121 for wall cooling. Turbine 3 drives compressor 8 to rotate. In this state, compressor intake port 111 is closed (control valve is closed). High-pressure air from compressor 8 cannot enter the combustion chamber through the channel between axial diffuser 83 and outer casing 13. Instead, it flows out sequentially from compressor 8 volute and bleed air pipe 82 to provide bleed air to the engine, thus enabling the engine to start or control the air supply. (4) Under the main engine load condition, high-pressure air flows into the dual-tube casing assembly 12 from the main engine intake port 121. The flow field of high-pressure air in the flame tube is basically consistent with the APU load mode. The fuel nozzle 5 supplies fuel, the gas nozzle 7 does not work, and the turbine 3 drives the compressor 8 to rotate. In this state, the compressor 8 intake port is closed. The high-pressure air of the compressor 8 cannot enter the combustion chamber from the channel between the axial diffuser 83 and the outer casing 13. Instead, it flows out from the compressor 8 volute and the bleed pipe 82 in sequence to provide bleed air to the main engine and realize the function of starting the main engine or environmental control.

[0037] In this embodiment, the main engine load mode can be used for single-engine failures in twin-engine aircraft operating at altitudes above 13,000 meters, and for situations where the high-pressure air supply from the gas tank is insufficient. Compared to the APU load mode, the main engine load mode directly introduces high-pressure air from the main engine, and the high-pressure air from compressor 8 no longer flows into the combustion chamber. Therefore, the inlet flow rate of compressor 8 can be significantly reduced, and the fuel flow rate in the combustion chamber casing 1 can also be appropriately reduced. Compared to the EPU load mode, the main engine load mode provides more stable and sustained air pressure.

[0038] For assembly, the compressor 8 casing is first installed on the compressor 8. After the compressor 8 and turbine 3 are installed, the combustion chamber casing 1 is installed. The swirl transition section is placed inside the turbine 3 guide vane of the turbine 3. The casing front flange 131, outer casing shell 13, inner casing shell 14, baffle and gas collecting ring assembly 11 are unit units and are integrally welded together. The casing front flange 131 is connected to the compressor 8 rear flange. After the first flame tube 21 and the second flame tube 22 are integrally welded together, they are inserted into the outer casing shell 13 through the double-tube casing mounting hole, and then axially inserted into the swirl transition section through the transition section mounting hole. The double-tube casing assembly 12 is connected to the gas collecting ring assembly 11, enclosing the first flame tube 21 and the second flame tube 22 inside the combustion chamber casing 1. The fuel nozzle 5 passes through the first nozzle mounting seat 123, the cap 216, and the vortex generator in sequence and communicates with the first combustion space. The first ignition nozzle 4 passes through the first nozzle mounting seat 122 and the first nozzle hole 219 and communicates with the first combustion space. The second ignition nozzle 6 passes through the second nozzle mounting seat 124 and the second nozzle hole seat and communicates with the second combustion space. The gas nozzle 7 passes through the second nozzle mounting seat 125 and communicates with the second combustion space.

[0039] The dual-tube combined auxiliary power combustion chamber provided by the present invention has the following advantages: (1) Gas enters the second flame tube 22. After the gas is ignited, the gas in the second flame tube 22 enters the first flame tube 21 through the second outlet 221. When the gas is ignited, it expands and the expanded gas enters the first flame tube 21, thereby reducing the volume of the second flame tube 22 and reducing the volume of the entire combustion chamber casing 1; (2) The combustion chamber structure is optimized. The axial diffuser 83 at the outlet of the compressor 8 is retained. The air is further compressed by the axial diffuser 83 to increase the air pressure (the higher the pressure, the easier it is to ignite successfully and the better the performance). However, the air is no longer directly introduced from the axial diffuser 83 but flows out from the compressed air inlet 111 of the gas collecting ring assembly 11. The opening and closing are controlled by the control valve set at the compressed air inlet 111 to prevent gas backflow; (3) It can realize the switching between different working conditions. The inlet and outlet are combined under each working condition to realize functional and modal diversification.

[0040] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A dual-tube combined auxiliary power combustion chamber, characterized in that, include: Combustion chamber housing (1), the combustion chamber housing (1) having a receiving space (16); The flame tube assembly (2) is located in the accommodating space (16). The flame tube assembly (2) includes a first flame tube (21) and a second flame tube (22). The second flame tube (22) is adapted to contain gas, and the second outlet (221) of the second flame tube (22) is connected to the first flame tube (21).

2. The dual-tube combined auxiliary power combustion chamber according to claim 1, characterized in that, The combustion chamber casing (1) includes a casing front flange (131), an outer casing housing (13) and an inner casing housing (14). The flame tube assembly (2) is partially located in the space formed by the outer casing housing (13) and the inner casing housing (14). The outer casing housing (13) has a casing front flange (131) on one side, and the casing front flange (131) is adapted to be connected to the compressor (8).

3. The dual-tube combined auxiliary power combustion chamber according to claim 2, characterized in that, The combustion chamber casing (1) further includes a gas collecting ring assembly (11), which includes a gas collecting space (112), a compressed air intake port (111), and a gas collecting casing (113). The gas collecting casing (113) is fitted around the outer casing shell (13). A compressed air intake port (111) is provided at the connection between the gas collecting space (112) and the accommodating space (16). A first gas collecting hole (132) is provided inside the outer casing shell (13), and the first gas collecting hole (132) is connected to the gas collecting space (112).

4. The dual-tube combined auxiliary power combustion chamber according to claim 3, characterized in that, The combustion chamber casing (1) also includes a double-tube casing assembly (12), which includes a double-tube casing housing. The double-tube casing housing is connected to the compressed air intake port (111) and the outer casing housing (13), respectively. The portion of the flame tube assembly (2) exposed in the outer casing housing (13) is located in the space formed by the double-tube casing housing and the outer casing housing (13).

5. The dual-tube combined auxiliary power combustion chamber according to claim 4, characterized in that, The combustion chamber casing (1) further includes a swirl connection section (15), which is located in the space formed by the outer casing housing (13) and the inner casing housing (14). One end of the swirl connection section (15) is connected to the first air outlet (217), and the other end of the swirl connection section (15) is adapted to communicate with the air inlet of the turbine (3).

6. The dual-tube combined auxiliary power combustion chamber according to claim 5, characterized in that, It also includes a fuel nozzle (5), a gas nozzle (7), a first ignition nozzle (4), and a second ignition nozzle (6). The fuel nozzle (5) and the first ignition nozzle (4) pass through the double-tube casing and are connected to the first flame tube (21). The gas nozzle (7) and the second ignition nozzle (6) pass through the double-tube casing and are connected to the second flame tube (22).

7. The dual-tube combined auxiliary power combustion chamber according to claim 6, characterized in that, The first flame tube (21) includes a first inner ring plate (215), a first outer ring plate (214), a first side plate (213), and a second side plate. The first inner ring plate (215), the first outer ring plate (214), the first side plate (213), and the second side plate form a first combustion space.

8. The dual-tube combined auxiliary power combustion chamber according to claim 2, characterized in that, The compressor (8) includes a compressor housing and an air intake pipe (82). The compressor housing is connected to the front flange (131) of the casing, and the air intake pipe (82) is connected to the compressor housing.

9. An aircraft, characterized in that, Includes the dual-tube combined auxiliary power combustion chamber as described in any one of claims 1-8.

10. A method of using a dual-tube combined auxiliary power combustion chamber, for using the dual-tube combined auxiliary power combustion chamber of claim 1, characterized in that, Under EPU operating conditions, gas enters the second flame tube (22). After the gas is ignited, the gas in the second flame tube (22) enters the first flame tube (21) through the second outlet (221).

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