Single-head-to-full-ring combined auxiliary combustion chamber, aero-engine and control method

Abstract

The invention relates to the technical field of aero-engines, in particular to a single-head-to-full-ring combined auxiliary combustion chamber, an aero-engine and a control method. A single-head-to-full-ring combined auxiliary combustion chamber comprises an air inlet pipe set which comprises a first air inlet pipeline, a second air inlet pipeline and a third air inlet pipeline, the first air inlet pipeline is suitable for being connected with an air compressor, the second air inlet pipeline is suitable for being connected with an air tank, and the third air inlet pipeline communicates with the first air inlet pipeline and the second air inlet pipeline; the third air inlet pipeline is provided with a single-head air inlet connector. The single-head combustion chamber assembly comprises a single-head flame tube and an air inlet channel, and one end of the air inlet channel is communicated with the single-head air inlet connector. The invention provides a single-head-to-full-ring combined auxiliary combustion chamber, an aero-engine and a control method, and aims to solve the problems that in the EPU-to-APU mode process, the pressures on the two sides of an axial diffuser are different, EPU inlet air entering a combustion chamber and a turbine flows backwards to an air compressor, and the EPU mode is out of order.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular to a single-head full-ring combined auxiliary combustion chamber, an aero-engine and a control method. BACKGROUND

[0002] Auxiliary power units (APU) and emergency power units (EPU) need two completely independent combustion chambers to complete the system functions. The two sets of combustion chambers have complex structures, similar functions, large installation spaces, and heavy overall weights.

[0003] With the increasing complexity and functionality of modern aircraft electronics and electrical equipment, and the widespread use of large-thrust / power aero-engines, the second power system has become an indispensable auxiliary power system on the aircraft, and its technical development can be roughly divided into three generations.

[0004] The first generation of second power systems is composed of a small gas turbine engine, also known as an auxiliary power unit (APU), which is mainly used to start the main engine on the ground and in the air, to ignite at high altitudes, and has a limited operating height, and does not have the function of providing auxiliary power / power in the full flight envelope. Its combustion chamber is a traditional single-can or annular combustion chamber.

[0005] The second generation of second power systems uses integrated technology to add an EPU (Emergency Power Unit, EPU) to the APU, combines the functions of the two, and realizes function integration. The APU+EPU system can not only start the main engine on the ground and at a limited altitude in the air, but also has the ability to provide emergency power in the full flight envelope. The system is composed of an APU+EPU combination, and the combustion chamber, turbine, generator and hydraulic pump load in the system are two sets. Among them, the APU uses aircraft fuel as fuel, and the EPU uses hydrazine fuel. The disadvantage is that the structure is complex, the weight is large, and the hydrazine fuel is toxic, and the system has poor maintenance convenience.

[0006] The third generation of second power systems is an integrated combined auxiliary power system (Integrate Power Unit, IPU), which further simplifies the structure on the basis of maintaining the functions of the second generation of second power systems, and integrates the APU and EPU to share a set of combustion chamber, turbine, gearbox, generator and hydraulic pump load structure, thereby greatly optimizing the system structure, reducing the complexity of the system, and being able to start the main engine, provide emergency power and other functions in the full flight envelope.

[0007] In the IPU, the combustion chamber has two working modes: one is the normal suction working mode, that is, the APU working mode, in which the high-pressure airflow from the compressor is mixed with fuel to produce power; the other is the EPU working mode, in which the high-pressure airflow from the gas tank is mixed with fuel to produce power. Both the APU and the EPU mode use aircraft fuel as fuel, and the combustion of the two modes is completed in the same combustion chamber, so it is called a dual-mode combustion chamber.

[0008] Although the third-generation IPU integrates the APU and EPU combustion chambers into one combustion chamber and uses aircraft fuel as fuel, the inlets of the APU and the EPU are different, and the mode switching process is complex. The traditional APU inlet is the outlet of the compressor axial diffuser, and the EPU inlet is a circular hole on the combustion chamber casing. The gas source of the EPU comes from the gas tank, and the EPU inlet is often aligned with the turbine inlet. The gas source of the turbine inlet comes from the gas after combustion in the combustion chamber. During the EPU to APU mode conversion, the compressor is opened (the compressor axial diffuser is opened), the gas tank is slowly closed, the gas source of the compressor comes from the atmosphere, the gas in the combustion chamber under the APU state enters the turbine inlet, and the EPU inlet also enters the gas in the early stage of conversion. Due to the difference in gas pressure between the compressor and the gas tank, the high-pressure gas appears to flow, the pressure on both sides of the axial diffuser is not the same, and the compressor axial diffuser is prone to abnormal closing, which causes the EPU inlet gas that should enter the combustion chamber and the turbine to flow back to the compressor, resulting in reverse rotation of the compressor and forward rotation of the turbine, and failure of the EPU mode. SUMMARY

[0009] Therefore, the present application provides a single-head-to-full-ring combined auxiliary combustion chamber, an aero-engine and a control method to solve the problem that during the EPU to APU mode conversion, the compressor is opened (the compressor axial diffuser is opened), the gas tank is slowly closed, the gas source of the compressor comes from the atmosphere, the gas in the combustion chamber under the APU state enters the turbine inlet, and the EPU inlet also enters the gas in the early stage of conversion. Due to the difference in gas pressure between the compressor and the gas tank, the high-pressure gas appears to flow, the pressure on both sides of the axial diffuser is not the same, and the compressor axial diffuser is prone to abnormal closing, which causes the EPU inlet gas that should enter the combustion chamber and the turbine to flow back to the compressor, resulting in reverse rotation of the compressor and forward rotation of the turbine, and failure of the EPU mode.

[0010] In a first aspect, the present application provides a single-head-to-full-ring combined auxiliary combustion chamber, comprising: An air inlet pipe group, the air inlet pipe group comprising a first air inlet pipe, a second air inlet pipe and a third air inlet pipe, the first air inlet pipe being adapted to be connected to a compressor, the second air inlet pipe being adapted to be connected to a gas tank, the third air inlet pipe being in communication with the first air inlet pipe and the second air inlet pipe respectively, and the third air inlet pipe being provided with a single-head air inlet interface; The single-head combustion chamber assembly comprises a single-head casing shell, a single-head flame tube and an air inlet channel, the single-head casing shell is provided with a containing space, the single-head flame tube is arranged in the containing space, one end of the air inlet channel is communicated with a single-head air inlet interface, and the other end of the air inlet channel is communicated with the containing space.

[0011] By arranging the first air inlet channel connected with the compressor and the second air inlet channel connected with the gas tank, the high-pressure gas in the first air inlet channel or the second air inlet channel enters the third air inlet channel, instead of being arranged in the round hole on the combustion chamber casing to enter the single-head flame tube in the single-head combustion chamber assembly through the single-head air inlet interface of the third air inlet channel, thereby avoiding the high-pressure gas backflowing into the compressor during the switching of different air inlet channels, realizing the normal conversion of EPU to APU and ensuring normal operation.

[0012] In an optional embodiment, the single-head combustion chamber assembly comprises a flow guide plate, and the flow guide plate and the single-head casing shell form an air inlet channel therebetween.

[0013] In an optional embodiment, the single-head flame tube comprises an outer ring plate, an inner ring plate and two connecting side plates, the outer ring plate and the inner ring plate are connected with the connecting side plates to form a combustion space, the outer ring plate is provided with an outer ring main combustion hole, an outer ring mixing hole and an outer ring film cooling hole, the inner ring plate is provided with an inner ring main combustion hole, an inner ring mixing hole and an inner ring film cooling hole, and the connecting side plates are provided with side plate cooling holes.

[0014] In an optional embodiment, the single-head combustion chamber assembly further comprises a fuel nozzle assembly, the fuel nozzle assembly is arranged on the single-head casing shell, the fuel nozzle assembly comprises a nozzle pipe and a nozzle connecting port, the nozzle connecting port is arranged on the outer side of the single-head casing shell, the nozzle pipe is arranged in the containing space, one end of the nozzle pipe is connected with the nozzle connecting port, the other end of the nozzle pipe is communicated with a vortex finder of the single-head flame tube, and the vortex finder is arranged at the head of the single-head flame tube.

[0015] In an optional embodiment, the single-head combustion chamber assembly further comprises an ignition electrode, the ignition electrode penetrates through the single-head casing shell and is connected with the single-head flame tube.

[0016] In an optional embodiment, the single-head combustion chamber assembly further comprises a full-ring combustion chamber assembly, and the full-ring combustion chamber assembly further comprises a full-ring casing shell, the full-ring casing shell is fixedly connected with the single-head casing shell.

[0017] In one optional embodiment, the full-annular combustion chamber assembly further includes a full-annular flame tube volute, the full-annular flame tube volute including a volute outer shell, the volute outer shell being disposed within the full-annular casing housing, and a cooling flow channel being formed between the volute outer shell and the full-annular casing housing.

[0018] In one optional embodiment, the single-head flame tube is further provided with a gas communication pipe, which is connected to the volute of the full-ring flame tube.

[0019] Secondly, the present invention also provides an aero-engine, including the aforementioned single-head rotating full-annular combined auxiliary combustion chamber.

[0020] Thirdly, the present invention also provides a control method for a single-head rotating full-ring combined auxiliary combustion chamber. Attached Figure Description 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.

[0021] Figure 1 This is a schematic diagram of a single-head rotating full-ring combined auxiliary combustion chamber according to an embodiment of the present invention; Figure 2 This is a cross-sectional view of a single-head rotating full-ring combined auxiliary combustion chamber according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the single-head rotating full-ring combined auxiliary combustion chamber from another angle according to an embodiment of the present invention; Figure 4 This is a schematic diagram of the inner ring plate of a single-head flame tube according to an embodiment of the present invention; Figure 5 This is a schematic diagram of the outer ring plate of a single-head flame tube according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the airflow in the APU start-up mode of the single-head rotating full-ring combined auxiliary combustion chamber according to an embodiment of the present invention; Figure 7 This is a control principle diagram of the single-head rotating full-ring combined auxiliary combustion chamber according to an embodiment of the present invention; Figure 8 This is a schematic diagram of the single-head rotating full-ring combined auxiliary combustion chamber in APU start-up mode according to an embodiment of the present invention; Figure 9 This is a schematic diagram of the single-head rotating full-ring combined auxiliary combustion chamber in APU bleed mode according to an embodiment of the present invention; Figure 10This is a schematic diagram of the single-head rotating full-ring combined auxiliary combustion chamber in EPU starting mode according to an embodiment of the present invention; Figure 11 This is a schematic diagram of the single-head rotating full-ring combined auxiliary combustion chamber in the main engine air supply mode according to an embodiment of the present invention; Figure 12 This is a schematic diagram of the single-head rotating full-ring combined auxiliary combustion chamber in the APU+EPU combined starting mode according to an embodiment of the present invention; Figure 13 This is a schematic diagram of the single-head rotating full-ring combined auxiliary combustion chamber in the main generator air supply + EPU starting mode according to an embodiment of the present invention; Figure 14 This is a schematic diagram of the single-head rotating full-ring combined auxiliary combustion chamber in the APU+EPU+main generator air supply starting mode according to an embodiment of the present invention.

[0022] Explanation of reference numerals in the attached drawings: 1. Single-head combustion chamber assembly; 101. Single-head casing housing; 1011. First flange end; 1012. Second flange end; 1013. Intake passage; 102. Single-head flame tube; 1021. Inner ring plate; 10211. Inner ring mixing hole; 10212. Inner ring main combustion hole; 10213. Inner ring film cooling hole; 1022. Outer ring plate; 10221. Outer ring mixing hole; 10222. Outer ring main combustion hole; 10223. Outer ring film cooling hole; 1023. Swirler; 1024. Drain plate; 1025. Connecting side plate; 10251. Side plate cooling hole; 103. First connecting seat; 104. Second connecting seat; 106. Guide plate; 2. Full-ring combustion chamber assembly; 201. Full-ring casing housing 1. Body; 2011. Third flange end; 2012. Fourth flange end; 202. Full-ring flame tube volute; 2021. Volute head end; 2022. Volute outer shell; 2023. Volute inner shell; 203. Cooling channel; 204. Gas connecting pipe; 205. Impact channel; 206. Turbine gas channel; 3. Intake pipe assembly; 301. First intake pipe; 302. Second intake pipe; 303. Third intake pipe; 304. First intake port; 305. Second intake port; 306. Single-head intake interface; 4. Fuel nozzle assembly; 401. Nozzle connection port; 402. Nozzle; 5. Ignition nozzle; 6. Turbine; 7. Compressor; 8. Gas tank; 9. Main generator; 10. Gearbox; 11. Starter / generator; 12. Hydraulic pump. Detailed Implementation

[0023] 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.

[0024] The following is combined with Figures 1 to 14 The following describes embodiments of the present invention.

[0025] According to an embodiment of the present invention, in one aspect, a single-head rotating full-ring combined auxiliary combustion chamber is provided, comprising: an intake pipe assembly 3, including a first intake pipe 301, a second intake pipe 302 and a third intake pipe 303, wherein the first intake pipe 301 is adapted to connect to a compressor 7, the second intake pipe 302 is adapted to connect to a gas tank 8, and the third intake pipe 303 is connected to the first intake pipe 301 and the second intake pipe 302 respectively, and the third intake pipe 303 is provided with a single-head intake interface 306; and a single-head combustion chamber assembly 1, including a single-head casing 101, a single-head flame tube 102 and an intake passage 1013, wherein the single-head casing 101 is provided with a receiving space, the single-head flame tube 102 is disposed in the receiving space, one end of the intake passage 1013 is connected to the single-head intake interface 306, and the other end of the intake passage 1013 is connected to the receiving space.

[0026] During the transition from EPU to APU mode, the gas tank 8 gradually stops supplying gas to the second intake pipe 302, and the compressor 7 starts supplying gas to the first intake pipe 301. This causes the gas in the compressor 7 to enter the third intake pipe 303 through the first intake pipe 301, while the gas in the gas tank 8 enters the third intake pipe 303 through the second intake pipe 302. The gas in the third intake pipe 303 then enters the single-head flame tube 102 along the intake channel 1013, where it is powered by the combustion of the gas.

[0027] By connecting the first intake pipe 301 to the compressor 7 and the second intake pipe 302 to the gas tank 8, the high-pressure gas in either the first or second intake pipe 301 enters the third intake pipe 303 to form a mixed gas. Instead of the compressor connecting to the combustion chamber via an axial diffuser and then entering the single-head flame tube 102 within the single-head combustion chamber assembly 1 through the single-head intake port 306 of the third intake pipe 303, this avoids high-pressure gas backflow into the compressor 7 during switching between different intake pipes, ensuring a smooth EPU-to-APU conversion and normal operation. This configuration eliminates the need for an axial diffuser on the compressor.

[0028] It should be noted that the third air intake pipe 303 has a first air intake port 304 at one end and a second air intake port 305 at the other end. The first air intake port 304 is connected to the Daihatsu air inlet interface, and the second air intake port 305 is connected to the Daihatsu air supply interface. It should also be noted that control valves are respectively installed at the first air intake pipe 301, the second air intake pipe 302, the first air intake port 304, and the second air intake port 305 to control the air intake pipes or ports and prevent backflow of airflow.

[0029] In one embodiment, such as Figure 1 , Figure 2 As shown, the single-head combustion chamber assembly 1 includes a baffle plate 105, and an air intake passage 1013 is formed between the baffle plate 105 and the single-head casing 101. By providing the air intake passage 1013, high-pressure gas flowing into the first air intake pipe 301, or the second air intake pipe 302, or the third air intake pipe 303 flows into the air intake passage 1013 through the single-head air intake interface 306, and then enters the receiving space of the single-head casing 101.

[0030] In one embodiment, such as Figure 2 , Figure 4 and Figure 5 As shown, the single-head flame tube 102 includes an outer ring plate 1022, an inner ring plate 1021, and two connecting side plates 1025. The outer ring plate 1022 and the inner ring plate 1021 are connected to the connecting side plates 1025 to enclose and form a combustion space. The outer ring plate 1022 is provided with an outer ring main combustion hole 10222, an outer ring mixing hole 10221, and an outer ring gas film cooling hole 10223. The inner ring plate 1021 is provided with an inner ring main combustion hole 10212, an inner ring mixing hole 10211, and an inner ring gas film cooling hole 10213. The connecting side plate 1025 is provided with a side plate cooling hole 10251. The high-pressure gas in the containment space is collected and enters the combustion space through the outer ring mixing hole 10221, the inner ring mixing hole 10211, the outer ring main combustion hole 10222, and the inner ring main combustion hole 10212, or through the outer ring gas film cooling hole 10223, the inner ring gas film cooling hole 10213, and the side plate cooling hole 10251.

[0031] In one embodiment, such as Figure 2 , Figure 3As shown, it also includes a fuel nozzle assembly 4, which is disposed on the single-head casing 101. The fuel nozzle assembly 4 includes a nozzle 402 and a nozzle connection port 401. The nozzle connection port 401 is disposed on the outside of the single-head casing 101, and the nozzle 402 is disposed in the receiving space. One end of the nozzle 402 is connected to the nozzle connection port 401, and the other end of the nozzle 402 is connected to the vortex generator 1023 of the single-head flame tube 102. The vortex generator 1023 is disposed at the head of the single-head flame tube 102. The nozzle connection port 401 is located on the first connecting seat 103 of the single-head casing 101. The nozzle 402 connects the nozzle connection port 401 and the vortex generator 1023 of the single-head flame tube 102. Atomized aviation kerosene flows inside the nozzle 402. The head of the single-head flame tube 102 is also provided with a guide plate 1024 so that the aviation kerosene enters the combustion space through the vortex generator 1023 and the guide plate 1024.

[0032] In one embodiment, such as Figure 2 , Figure 3 As shown, it also includes an ignition nozzle, which passes through the single-head casing 101 and is connected to the single-head flame tube 102. The ignition nozzle is located on the second connecting seat 104 of the single-head casing 101 to ignite the mixture of aviation kerosene and high-pressure gas in the combustion space, thereby generating high-temperature gas through combustion in the single-head flame tube 102.

[0033] In one embodiment, such as Figure 2 , Figure 3 As shown, the system also includes a full-ring combustion chamber assembly 2, which further includes a full-ring casing housing 201. The full-ring casing housing 201 is fixedly connected to the single-head casing housing 101. In this embodiment, the single-head casing housing 101 includes a first flange end 1011 and a second flange end 1012, which are located at opposite ends of the single-head casing housing 101. The full-ring casing housing 201 includes a third flange end 2011. The second flange end 1012 and the third flange end 2011 are fixedly connected to the full-ring casing housing 201 and the single-head casing housing 101 by fasteners. The first flange end 1011 is connected to a third intake pipe 303, thereby fixing the third intake pipe 303 to the single-head casing housing 101. Specifically, the fastener is a nut.

[0034] In one embodiment, such as Figure 2 , Figure 3 and Figure 6As shown, the full-annular combustion chamber assembly 2 also includes a full-annular flame tube volute 202. The full-annular flame tube volute 202 includes a volute outer shell 2022, which is disposed within the full-annular casing 201. A cooling channel 203 is formed between the volute outer shell 2022 and the full-annular casing 201. High-pressure gas that does not enter the single-head flame tube 102 enters the space between the volute outer shell 2022 and the full-annular casing 201 through the cooling channel 203.

[0035] In one embodiment, such as Figure 2 , Figure 3 and Figure 6 As shown, the single-head flame tube 102 is also equipped with a gas connecting pipe 204, which is connected to the full-ring flame tube volute 202. The high-temperature gas generated by combustion in the single-head flame tube 102 enters the full-ring flame tube volute 202 through the gas connecting pipe 204. The full-ring flame tube volute 202 is annular. The high-temperature gas is rectified within the full-ring flame tube volute 202 before reaching the annular outlet of the full-ring flame tube 202, impacting the rotor and thus driving it to rotate. Figure 1 As shown, the full-ring flame tube volute 202 includes a volute head end 2021, a volute outer shell 2022, a volute inner shell 2023, and a volute connection port. The volute connection port is used to connect to a gas communication pipe. The volute outer shell 2022 and the volute inner shell 2023 are respectively provided with volute cooling holes, allowing high-pressure gas entering the space between the volute outer shell 2022 and the full-ring casing 201 through the cooling channel 203 to enter the full-ring flame tube volute 202. This achieves mixing of the high-pressure gas and high-temperature gas entering the full-ring flame tube volute 202, and then rectifying it before it enters the turbine 6 to supply power. In this embodiment, the full-ring flame tube volute 202 is placed inside the turbine 6 guide vane of the turbine 6 and is connected to the compressor 7 via the fourth flange end 2012.

[0036] In this embodiment, as Figure 6 As shown, the full-ring casing 201 is also connected to an impact flow channel 205, within which is installed the rotor of the turbine 6. High-pressure gas and high-temperature combustion gas from the full-ring flame tube volute 202 mix and impact the rotor within the impact flow channel 205, causing it to rotate. The mixture then enters the turbine gas flow channel 206. Since the rotor is connected to the gearbox 10, and the gearbox 10 is connected to the starter / generator 11, the rotor ultimately drives the starter / generator 11 to generate electricity. This electricity is used for cooling, lighting, and other control functions, and also provides power to the hydraulic pump 12.

[0037] A control method for a single-head rotating full-ring combined auxiliary combustion chamber includes the following steps: (1) High-pressure gas flows into the intake channel 1013 through the single-head intake port 306 and then enters the accommodating space of the single-head casing 101; (2) A portion of the high-pressure gas entering the containment space enters the combustion space through the outer ring mixing hole 10221, the inner ring mixing hole 10211, the outer ring main combustion hole 10222, the inner ring main combustion hole 10212, the outer ring gas film cooling hole 10223, and the inner ring gas film cooling hole 10213. The ignition nozzle ignites the mixture of aviation kerosene and high-pressure gas in the combustion space, thereby achieving combustion in the single-head flame tube 102 to generate high-temperature gas. (3) Another part of the high-pressure gas that does not enter the single-head flame tube 102 enters the space between the volute shell 2022 and the full-ring casing 201 through the cooling channel 203. In addition, the high-temperature gas generated by the combustion in the single-head flame tube 102 enters the full-ring flame tube volute 202 through the gas connecting pipe 204, so that the high-pressure gas and high-temperature gas entering the full-ring flame tube volute 202 are mixed and rectified to enter the turbine 6 to supply power.

[0038] An aero-engine, comprising the aforementioned single-head rotating full-annular combined auxiliary combustion chamber.

[0039] The single-head rotating full-ring combined auxiliary combustion chamber of this embodiment, through connection with components such as compressor 7, air tank 8, main engine 9, and turbine 6, has the following operating conditions: 1) APU startup mode ( Figure 8 (As shown): When the APU is working, the high-pressure air flowing out of the diffuser of the compressor 7 enters the third intake pipe 303 from the first intake pipe 301. At this time, the second intake pipe 302, the second intake port 305 and the first intake port 304 are closed, and the single-head intake port 306 is open. 2) APU bleed mode ( Figure 9 (As shown): After the APU stabilizes, it needs to be switched to bleed air mode. At this time, the high-pressure air flowing out of the diffuser of compressor 7 enters the third intake pipe 303 from the first intake pipe 301. At this time, the second intake pipe 302 and the first intake port 304 are closed, and the single-head intake port 306 and the second intake port 305 are opened. At this time, part of the high-pressure air flowing out of the diffuser of compressor 7 is consistent with the flow pattern of the APU working mode and enters the single-head flame tube 102 for combustion. The other part flows out from the bleed air volute of compressor 7 to supply the bleed air and environmental control of Daihatsu. 3) EPU start-up mode ( Figure 10(As shown): The second air intake pipe 302 and the single-head air intake port 306 are open, while the first air intake pipe 301, the second air intake port 305, and the first air intake port 304 are closed; the gas tank 8 supplies high-pressure air directly into the combustion chamber casing, instead of being supplied by the compressor 7. This is commonly used at altitudes above 13,000 meters, or when the compressor 7 malfunctions and cannot supply air. The high-pressure air supplied by the gas tank 8 enters the single-head flame tube 102 to participate in combustion; 4) Dafeng Gas Supply Mode (New) Figure 11 As shown): When the Daihatsu is working normally, air is drawn from the Daihatsu engine for APU startup; it can be used, but is not limited to, single-engine shutdown situations in twin-engine aircraft above 13,000 meters (the air pressure is more stable than the EPU working mode air supply). 5) APU+EPU combined start-up mode ( Figure 12 (As shown): The first air intake pipe 301, the second air intake pipe 302 and the single-head air intake interface 306 are open, and the second air intake 305 and the first air intake 304 are closed; when the APU start-up mode cannot start normally, for example, when the APU malfunction causes the compressor 7 diffuser to produce less high-pressure air, the air tank 8 can be opened at the same time to supply air for the normal start-up of the APU; 6) EPU+APU combined start-up mode ( Figure 12 (As shown): The first intake pipe 301, the second intake pipe 302, and the single-head intake port 306 are open, while the second intake port 305 and the first intake port 304 are closed; In the middle and later stages of the EPU start-up mode, the turbine 6 has reached a certain speed, the compressor 7 has also started to rotate, and the diffuser outlet of the compressor 7 has a certain amount of high-pressure air. If it is not vented, it will cause pressure buildup, leading to casing rupture. If it is vented, this part of the energy is wasted. Therefore, it can be used to form a combined start-up mode. Compared with the simple EPU start-up mode, the air supply volume of the air tank 8 can be appropriately reduced, and the air supply time can be extended; Compared with operating condition 5), the valve opening is inconsistent; 7) Daifu gas supply + EPU start-up mode ( Figure 13 (As shown): The second air intake pipe 302, the first air intake port 304 and the single-head air intake interface 306 are open, and the second air intake port 305 and the first air intake pipe 301 are closed; when the single engine is working normally, but the high-pressure air drawn from the engine does not meet the air intake requirements of the single-head combustion chamber assembly 1, the air tank 8 can be opened at the same time to supply air. 8) APU+EPU+Daifa air supply starting mode ( Figure 14 As shown): the first air intake pipe 301, the second air intake pipe 302, the first air intake port 304 and the single-head air intake interface 306 are open, and the second air intake port 305 is closed; all air intakes are open, which is commonly used in the middle and later processes of the Daihatsu air supply + EPU start-up mode.

[0040] It should be noted that in this embodiment, "dafa" refers to a type of engine among turboshaft, turboprop, turbojet, and turbofan engines. That is, the main engine of an aircraft, which serves as the main power of the aircraft, and the auxiliary combustion chamber of the present application serves as the auxiliary power of the aircraft. The air pressure range of the high-pressure gas in the present application is 200 - 5000 kPa, and "environmental control" refers to controlling the environmental temperature, humidity, etc. in the cockpit and cabin through air conditioning.

[0041] The single-head to full-ring combined auxiliary combustion chamber provided by the present invention has the following advantages: (1) By setting the first intake pipe 301 to be connected to the compressor 7 and the second intake pipe 302 to be connected to the gas tank 8, the high-pressure gas in either the first intake pipe 301 or the second intake pipe 302 will enter the third intake pipe 303, rather than setting the EPU inlet at the circular hole on the combustion chamber casing and then entering the single-head flame tube 102 in the single-head combustion chamber assembly 1 through the single-head intake interface 306 of the third intake pipe 303 for combustion, avoiding the backflow of high-pressure gas into the compressor 7 during the switching of different intake pipes, realizing the normal conversion of EPU to APU, and ensuring normal operation; (2) It has different modal working conditions, realizing the diversification of functions and modes.

[0042] Although the embodiments of the present 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 present invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A single-head rotating full-ring combined auxiliary combustion chamber, characterized in that, include: An intake pipe assembly (3) includes a first intake pipe (301), a second intake pipe (302) and a third intake pipe (303). The first intake pipe (301) is adapted to connect to a compressor (7), the second intake pipe (302) is adapted to connect to an air tank (8), and the third intake pipe (303) is connected to the first intake pipe (301) and the second intake pipe (302) respectively. The third intake pipe (303) is provided with a single-head intake port (306). A single-head combustion chamber assembly (1) includes a single-head casing (101), a single-head flame tube (102), and an air intake passage (1013). The single-head casing (101) has a receiving space, the single-head flame tube (102) is located in the receiving space, one end of the air intake passage (1013) is connected to the single-head air intake port (306), and the other end of the air intake passage (1013) is connected to the receiving space.

2. The single-head rotating full-ring combined auxiliary combustion chamber according to claim 1, characterized in that, The single-head combustion chamber assembly (1) includes a baffle (105) and an air intake passage (1013) is formed between the baffle (105) and the single-head casing (101).

3. The single-head rotating full-ring combined auxiliary combustion chamber according to claim 2, characterized in that, The single-head flame tube (102) includes an outer ring plate (1022), an inner ring plate (1021), and two connecting side plates (1025). The outer ring plate (1022) and the inner ring plate (1021) are respectively connected to the connecting side plates (1025) to enclose and form a combustion space. The outer ring plate (1022) is provided with an outer ring main combustion hole (10222), an outer ring mixing hole (10221), and an outer ring gas film cooling hole (10223). The inner ring plate (1021) is provided with an inner ring main combustion hole (10212), an inner ring mixing hole (10211), and an inner ring gas film cooling hole (10213). The connecting side plate (1025) is provided with a side plate cooling hole (10251).

4. The single-head rotating full-ring combined auxiliary combustion chamber according to claim 3, characterized in that, It also includes a fuel nozzle assembly (4), which is disposed on the single-head casing housing (101). The fuel nozzle assembly (4) includes a nozzle pipe (402) and a nozzle connection port (401). The nozzle connection port (401) is disposed on the outside of the single-head casing housing (101). The nozzle pipe (402) is disposed in the receiving space. One end of the nozzle pipe (402) is connected to the nozzle connection port (401), and the other end of the nozzle pipe (402) is connected to the vortex generator (1023) of the single-head flame tube (102). The vortex generator (1023) is disposed at the head of the single-head flame tube (102).

5. The single-head rotating full-ring combined auxiliary combustion chamber according to claim 4, characterized in that, It also includes an ignition nozzle, which passes through the single-head casing (101) and is connected to the single-head flame tube (102).

6. The single-head rotating full-ring combined auxiliary combustion chamber according to any one of claims 1-5, characterized in that, It also includes a full-ring combustion chamber assembly (2), which further includes a full-ring casing housing (201), which is fixedly connected to a single-head casing housing (101).

7. The single-head rotating full-ring combined auxiliary combustion chamber according to claim 6, characterized in that, The full-ring combustion chamber assembly (2) further includes a full-ring flame tube volute (202), which includes a volute outer shell (2022) disposed within the full-ring casing housing (201). A cooling channel (203) is formed between the full-ring flame tube volute (202) and the full-ring casing housing (201).

8. The single-head rotating full-ring combined auxiliary combustion chamber according to claim 7, characterized in that, The single-head flame tube (102) is also provided with a gas connection pipe (204), which is connected to the volute of the full-ring flame tube (202).

9. An aircraft engine, characterized in that, Includes the single-head rotating full-ring combined auxiliary combustion chamber as described in any one of claims 1-8.

10. A control method for a single-head rotating full-annular combined auxiliary combustion chamber, used in the single-head rotating full-annular combined auxiliary combustion chamber of claim 1, characterized in that, During the transition from EPU to APU mode, the gas tank (8) gradually stops supplying gas to the second intake pipe (302), and the compressor (7) supplies gas to the first intake pipe (301), so that the gas in the compressor (7) enters the third intake pipe (303) through the first intake pipe (301). The gas in the gas tank (8) enters the third intake pipe (303) through the second intake pipe (302), and the gas in the third intake pipe (303) enters the single-head flame tube (102) along the intake channel (1013), where the gas is powered by the combustion of the gas in the single-head flame tube (102).

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