A dual mode combustion chamber and engine

Abstract

The application relates to the technical field of aero-engines and discloses a dual-mode combustion chamber and an engine, which comprise a casing, an auxiliary power intake system, an emergency power intake system and an intake switching mechanism, and a flame tube is arranged in the casing; the auxiliary power intake system and the emergency power intake system on the casing are connected with the flame tube; in an auxiliary power mode of the dual-mode combustion chamber, the intake switching mechanism closes the emergency power intake system, and the auxiliary power intake system is opened; in an emergency power mode of the dual-mode combustion chamber, the intake switching mechanism closes the auxiliary power intake system, and the emergency power intake system is opened. In the working process of the two modes, the flame tube is shared, the design of traditional independent two sets of combustion chambers is cancelled, components are reduced, and the system weight and space occupation are reduced. The dual-mode combustion chamber provided by the application solves the problems of complex structure, large installation space occupation and large weight of an existing second power system.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a dual-mode combustion chamber and engine. Background Technology

[0002] The second power system is mainly used to start the main engine, provide compressed air to the aircraft's environmental control system, and drive the aircraft's hydraulic pumps and generators to provide hydraulic and electrical power to the aircraft.

[0003] In existing technologies, the second power system utilizes integrated technology, adding an Emergency Power Unit (EPU) to the Auxiliary Power Unit (APU), and combining the functions of the two to achieve functional integration. The second power system, composed of the APU and EPU, not only enables the main engine to start on the ground and at limited altitudes in the air, but also has the capability to provide emergency power throughout the entire flight envelope.

[0004] However, the existing second power system requires two independent combustion chambers, resulting in a complex structure, large installation space occupation, and heavy weight. Summary of the Invention

[0005] This invention provides a dual-mode combustion chamber and engine to solve the problems of existing second power systems having complex structures, large installation space requirements, and heavy weight.

[0006] In a first aspect, the present invention provides a dual-mode combustion chamber, comprising: a casing, an auxiliary power intake system, an emergency power intake system, and an intake switching mechanism. A flame tube is disposed inside the casing, and the flame tube contains a combustion chamber. A nozzle is disposed on the flame tube and connected to a fuel supply device. The nozzle is used to inject fuel into the combustion chamber. The auxiliary power intake system is disposed on the casing and connected to the flame tube. The emergency power intake system is disposed on the casing and connected to the flame tube. The intake switching mechanism is disposed on the casing and is used to switch the connection state between the auxiliary power intake system and the flame tube. In the auxiliary power mode of the dual-mode combustion chamber, the intake switching mechanism closes the emergency power intake system and opens the auxiliary power intake system; in the emergency power mode of the dual-mode combustion chamber, the intake switching mechanism closes the auxiliary power intake system and opens the emergency power intake system.

[0007] Beneficial effects: During operation, the auxiliary power intake system and the emergency power intake system are switched via the intake switching system, enabling the dual-mode combustor to switch between auxiliary power mode and emergency power mode. In both modes, a single flame tube within the casing is shared, eliminating the need for the traditional design of two separate combustors, reducing components, system weight, and space occupation. Furthermore, in both modes, aircraft fuel is injected into the combustion chamber of the flame tube through nozzles, replacing the hydrazine fuel used in the emergency power unit of the traditional second power system, thus eliminating the installation hazards and maintenance inconvenience caused by the highly toxic nature of hydrazine fuel. The dual-mode combustor provided by this invention solves the problems of complex structure, large installation space occupation, and heavy weight of existing second power systems.

[0008] In one optional embodiment, the intake switching mechanism includes: a first switching component and a second switching component. The first switching component is disposed on the auxiliary power intake system and is used to turn off or on the auxiliary power intake system. The second switching component is disposed on the emergency power intake system and is used to turn off or on the emergency power intake system. In the auxiliary power mode of the dual-mode combustion chamber, the first switching component turns on the auxiliary power intake system and the second switching component turns off the emergency power intake system. In the emergency power mode of the dual-mode combustion chamber, the first switching component turns off the auxiliary power intake system and the second switching component turns on the emergency power intake system.

[0009] Beneficial effects: The auxiliary power intake system is controlled by the first switching component, and the emergency power intake system is controlled by the second switching component, thereby enabling the dual-mode combustion chamber to switch between auxiliary power mode and emergency power mode.

[0010] In one optional embodiment, the auxiliary power system is provided with a first air intake channel, the air intake end of the first air intake channel is connected to a compressor, and the air outlet end of the first air intake channel is connected to the flame tube; the first switching component includes: a drive device, a transmission component, and a sealing blade, the drive device is disposed on the casing, the sealing blade is drivenly connected to the drive device through the transmission component, and the sealing blade is disposed in the first air intake channel; wherein, in the auxiliary power mode of the dual-mode combustion chamber, the drive device drives the sealing blade to rotate to a first position through the transmission component, and the first air intake channel is opened; in the emergency power mode of the dual-mode combustion chamber, the drive device drives the sealing blade to rotate to a second position through the transmission component, and the first air intake channel is closed.

[0011] Beneficial effects: The drive unit drives the sealing blade to rotate in the first air intake channel of the auxiliary power system through the transmission component. When the sealing blade rotates to the first position, the first air intake channel is opened and connected to the combustion chamber of the flame tube. When the sealing blade rotates to the second position, the first air intake channel is closed, realizing the opening and closing of the auxiliary power mode.

[0012] In one optional embodiment, the transmission assembly includes: a first transmission member and a second transmission member. The first transmission member is rotatably mounted on the housing and is connected to the drive device. The first transmission member is annular and has a first toothed structure circumferentially arranged thereon. The second transmission member is rotatably mounted on the housing and has multiple second transmission members circumferentially arranged on the first transmission member. The second transmission member is fan-shaped and has a second toothed structure on its arc-shaped side that meshes with the first toothed structure. The sealing blade is mounted on the second transmission member.

[0013] Beneficial effects: A first toothed structure is circumferentially arranged on the first annular transmission component to form a main gear, and a second toothed structure is arranged on the second transmission component to form a sector gear. The first transmission component is driven to rotate by a drive device, and the meshing transmission of the first and second toothed structures causes the sector-shaped second transmission component to drive the sealing blade to rotate, thereby realizing the opening or closing of the sealing blade to the first air intake channel. The drive device and gear transmission reduce the switching time of the auxiliary power intake system to within 0.5 seconds.

[0014] In one optional embodiment, the outlet end of the first air intake channel is provided with a radial diffuser and an axial diffuser, and the first switching component is disposed between the radial diffuser and the axial diffuser.

[0015] Beneficial effect: The first switching component is installed in the airflow transition section between the radial diffuser and the axial diffuser, eliminating the need for additional installation space.

[0016] In one alternative embodiment, the sealing blade is made of a lightweight material.

[0017] Beneficial effects: Using lightweight materials to make the sealing blades can reduce the rotational inertia of the sealing blades switching auxiliary power intake system, which is conducive to compressing the switching time to within 0.5 seconds in conjunction with the drive device and transmission components, meeting the requirements of high dynamic operating conditions; at the same time, the lightweight materials are light in weight, which helps to reduce the overall weight of the dual-mode combustion chamber.

[0018] In one optional embodiment, the emergency power intake system includes: a volute and a high-pressure gas tank, the volute being disposed on the housing, the second switching component being disposed on the volute, the volute having a second intake channel inside, the intake end of the second intake channel being connected to the high-pressure gas tank, the outlet end of the second intake channel being connected to the flame tube, and the second switching component being used to open or close the second intake channel.

[0019] Beneficial effects: The high-pressure gas in the high-pressure storage tank is transported to the combustion chamber of the flame tube through the second air intake channel inside the volute. The second switching component on the volute can open or close the second air intake channel, thereby realizing the control and switching of the emergency power air intake system.

[0020] In one optional embodiment, the volute is provided with an annular vent portion surrounding the circumference of the casing, and the annular vent portion is provided with a plurality of vent holes communicating with the interior of the casing; one side of the annular vent portion is provided with an inlet portion for connecting to the high-pressure gas storage tank.

[0021] Beneficial effects: High-pressure gas from the high-pressure gas tank enters the annular outlet section through the inlet, and is then delivered to the combustion chamber of the flame tube through multiple circumferential outlet holes in the annular outlet section. The inlet section is located on one side of the annular outlet section, forming an asymmetrical volute structure, which reduces airflow loss and pressure pulsation within the volute, improves the total pressure recovery coefficient of the emergency power intake system, and is compatible with the low-temperature and high-pressure gas source characteristics of the high-pressure gas tank.

[0022] In one alternative embodiment, the diameter of the air outlet has multiple values ​​along the circumference of the annular air outlet to improve the uniformity of the air flow rate and velocity of the multiple air outlets.

[0023] Beneficial effects: By selecting various air outlets of different specifications along the circumference of the annular air outlet, in emergency power mode, the air flow and velocity along the entire annular air outlet are uniform, enabling rapid and reliable ignition, stable and efficient combustion, and obtaining a suitable combustion chamber outlet temperature field.

[0024] Secondly, the present invention also provides an engine, comprising: a fuel supply device and a dual-mode combustion chamber as described in the above embodiments, wherein the fuel supply device is connected to the nozzle of the dual-mode combustion chamber.

[0025] Beneficial effects: The fuel supply system delivers aircraft fuel to the nozzles, which then inject it into the combustion chamber within the flame tube. In the auxiliary power mode of the dual-mode combustor, high-pressure airflow from the compressor enters the combustion chamber via the auxiliary power intake system. In the emergency power mode, high-pressure airflow from the gas tank enters the combustion chamber via the emergency power intake system, allowing the high-pressure airflow to mix with the aircraft fuel for combustion and power generation, thus providing emergency power support across the entire flight envelope. Because of the dual-mode combustor described in the above embodiment, it possesses any of the advantages mentioned above. Attached Figure Description

[0026] 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.

[0027] Figure 1 This is a schematic diagram of a dual-mode combustion chamber according to an embodiment of the present invention; Figure 2 for Figure 1 A partially enlarged schematic diagram of the dual-mode combustion chamber shown; Figure 3 for Figure 1 A left-view diagram; Figure 4 for Figure 1 Schematic diagram of the central intake switching mechanism; Figure 5 for Figure 4 A partially enlarged schematic diagram of the intake switching mechanism shown; Figure 6 for Figure 1 Schematic diagram of the middle volute; Figure 7 A comparison diagram of the pore size distribution of the exhaust holes in the all-ring equal pore size exhaust mode and the all-ring unequal pore size exhaust mode; Figure 8 A comparison diagram of the uniformity of air flow rate at the outlet holes in the all-ring equal-diameter air outlet method and the all-ring unequal-diameter air outlet method; Figure 9 The simulation diagram of the exhaust velocity field for the all-ring equal-aperture exhaust method; Figure 10 This is a simulation diagram of the exhaust velocity field for an exhaust system with unequal orifice diameters throughout the ring.

[0028] Explanation of reference numerals in the attached figures: 1. Casing; 2. Flame tube; 3. Nozzle; 4. First air intake passage; 41. Radial diffuser; 42. Axial diffuser; 5. Volute; 51. Annular air outlet; 52. Air outlet; 53. Air intake; 6. First switching assembly; 61. First transmission component; 62. Second transmission component; 63. Sealing blade. Detailed Implementation

[0029] 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.

[0030] In related technologies, the auxiliary power unit of the second power system uses aircraft fuel as fuel, and the emergency power unit uses hydrazine fuel. The disadvantages are that the structure is complex, the weight is large, and hydrazine fuel is toxic, and the system is difficult to maintain.

[0031] The following is combined Figures 1 to 10 The following describes embodiments of the present invention.

[0032] According to embodiments of the present invention, in one aspect, such as Figure 1 , Figure 2 As shown, a dual-mode combustor is provided, comprising: a casing 1, an auxiliary power intake system, an emergency power intake system, and an intake switching mechanism. A flame tube 2 is disposed inside the casing 1, and the flame tube 2 has a combustion chamber inside. A nozzle 3 is disposed on the flame tube 2, and the nozzle 3 is connected to a fuel supply device for injecting fuel into the combustion chamber. The auxiliary power intake system is disposed on the casing 1 and connected to the flame tube 2. The emergency power intake system is disposed on the casing 1 and connected to the flame tube 2. The intake switching mechanism is disposed on the casing 1 and is used to switch the connection state between the auxiliary power intake system and the flame tube 2. In the auxiliary power mode of the dual-mode combustor, the intake switching mechanism closes the emergency power intake system and opens the auxiliary power intake system; in the emergency power mode of the dual-mode combustor, the intake switching mechanism closes the auxiliary power intake system and opens the emergency power intake system.

[0033] In operation, the auxiliary power intake system and the emergency power intake system are switched via the intake switching system to achieve the switching between the auxiliary power mode and the emergency power mode of the dual-mode combustor. During operation in both modes, a single flame tube 2 within the casing 1 is shared, eliminating the need for the traditional design of two separate combustors, reducing components, system weight, and space occupation. Simultaneously, in both modes, aircraft fuel is injected into the combustion chamber of the flame tube 2 through the nozzle 3, replacing the hydrazine fuel used in the emergency power unit of the traditional second power system, thus eliminating the installation hazards and maintenance inconvenience caused by the highly toxic nature of hydrazine fuel. The dual-mode combustor provided in this embodiment solves the problems of complex structure, large installation space occupation, and heavy weight of existing second power systems.

[0034] Specifically, the nozzle 3 is configured as an adjustable structure, which can adapt to different oil-gas ratio requirements in auxiliary power mode and emergency power mode.

[0035] Specifically, the structure of the flame tube 2 adopts a segmented combustion design to reduce thermal stress concentration.

[0036] In one embodiment, such as Figure 1 , Figure 2 As shown, the intake switching mechanism includes: a first switching component 6 and a second switching component. The first switching component 6 is disposed on the auxiliary power intake system and is used to turn the auxiliary power intake system off or on. The second switching component is disposed on the emergency power intake system and is used to turn the emergency power intake system off or on. In the auxiliary power mode of the dual-mode combustor, the first switching component 6 turns on the auxiliary power intake system and the second switching component turns off the emergency power intake system. In the emergency power mode of the dual-mode combustor, the first switching component 6 turns off the auxiliary power intake system and the second switching component turns on the emergency power intake system. The first switching component 6 controls the auxiliary power intake system, and the second switching component controls the emergency power intake system, thereby enabling the dual-mode combustor to switch between auxiliary power mode and emergency power mode. Alternatively, as an alternative implementation, the intake switching mechanism can also be equipped with a single switching component to switch between the auxiliary power intake system and the emergency power intake system.

[0037] In one embodiment, such as Figure 1-5As shown, the auxiliary power system is provided with a first air intake channel 4, the air intake end of the first air intake channel 4 is connected to the compressor, and the air outlet end of the first air intake channel 4 is connected to the flame tube 2; the first switching component 6 includes: a driving device, a transmission component, and a sealing blade 63, the driving device is disposed on the casing 1, the sealing blade 63 is connected to the driving device through the transmission component, and the sealing blade 63 is disposed in the first air intake channel 4; wherein, in the auxiliary power mode of the dual-mode combustion chamber, the driving device drives the sealing blade 63 to rotate to the first position through the transmission component, and the first air intake channel 4 is opened; in the emergency power mode of the dual-mode combustion chamber, the driving device drives the sealing blade 63 to rotate to the second position through the transmission component, and the first air intake channel 4 is closed. The driving device drives the sealing blade 63 to rotate within the first air intake channel 4 via the transmission assembly. When the sealing blade 63 rotates to the first position, the first air intake channel 4 opens and communicates with the combustion chamber of the flame tube 2. When the sealing blade 63 rotates to the second position, the first air intake channel 4 is closed, thus realizing the opening and closing of the auxiliary power mode. Alternatively, as an alternative implementation, the sealing blade 63 can also be configured as a retractable structure. In the auxiliary power mode of the dual-mode combustion chamber, the sealing blade 63 retracts, and the first air intake channel 4 opens. In the emergency power mode of the dual-mode combustion chamber, the sealing blade 63 extends into the first air intake channel 4 to close it.

[0038] In one embodiment, such as Figure 1-5As shown, the transmission assembly includes: a first transmission member 61 and a second transmission member 62. The first transmission member 61 is rotatably mounted on the housing 1 and is connected to the drive device. The first transmission member 61 is annular and has a first toothed structure in its circumferential direction. The second transmission member 62 is rotatably mounted on the housing 1 and has multiple second transmission members 62 arranged in the circumferential direction of the first transmission member 61. The second transmission member 62 is fan-shaped and has a second toothed structure on its arc-shaped side that meshes with the first toothed structure. The sealing blade 63 is mounted on the second transmission member 62. The first transmission member 61, which is annular, has a toothed structure forming a main gear. The second transmission member 62 has a toothed structure forming a sector gear. The first transmission member 61 is driven to rotate by the driving device. Through the meshing of the first and second toothed structures, the sector-shaped second transmission member 62 drives the sealing blade 63 to rotate, thereby opening or closing the first air intake channel 4. The driving device, in conjunction with the gear transmission, shortens the switching time of the auxiliary power intake system to within 0.5 seconds. Alternatively, as an alternative embodiment, the second transmission member 62 can also be circular.

[0039] In one embodiment, such as Figure 1 , Figure 2 As shown, the outlet end of the first air intake channel 4 is provided with a radial diffuser 41 and an axial diffuser 42, and the first switching assembly 6 is disposed between the radial diffuser 41 and the axial diffuser 42. The first switching assembly 6 is installed in the airflow transition section between the radial diffuser 41 and the axial diffuser 42, eliminating the need for additional installation space. Alternatively, as an alternative embodiment, the first switching assembly 6 can also be disposed at the air intake end of the radial diffuser 41.

[0040] In one embodiment, the sealing blade 63 is made of a lightweight material. Using a lightweight material to make the sealing blade 63 reduces the rotational inertia of the sealing blade 63 when switching the auxiliary power intake system, which helps to work with the drive device and the transmission assembly to compress the switching time to within 0.5 seconds, meeting the requirements of high dynamic operating conditions. At the same time, the lightweight material reduces the overall weight of the dual-mode combustion chamber.

[0041] Specifically, the sealing blade 63 is preferably, but not limited to, a ceramic matrix composite material (CMC), which has the advantages of good sealing performance and light weight.

[0042] In one embodiment, such as Figure 1 , Figure 2 , Figure 3 , Figure 6 As shown, the emergency power intake system includes a volute 5 and a high-pressure gas tank. The volute 5 is mounted on the casing 1. The second switching component is mounted on the volute 5. The volute 5 has a second intake channel inside. The intake end of the second intake channel is connected to the high-pressure gas tank, and the outlet end of the second intake channel is connected to the flame tube 2. The second switching component is used to open or close the second intake channel. High-pressure gas from the high-pressure gas tank is transported to the combustion chamber of the flame tube 2 through the second intake channel within the volute 5. The second switching component on the volute 5 can open or close the second intake channel, thereby achieving the control and switching of the emergency power intake system. Alternatively, as an alternative implementation, the second switching component can also be mounted on the high-pressure gas tank.

[0043] Specifically, the second switching component can be configured as an electric valve.

[0044] In one embodiment, such as Figure 1 , Figure 2 , Figure 3 , Figure 6 As shown, the volute 5 is provided with an annular air outlet 51 surrounding the casing 1. The annular air outlet 51 has multiple air outlet holes 52 communicating with the interior of the casing 1. An air inlet 53 for connecting to the high-pressure gas tank is provided on one side of the annular air outlet 51. High-pressure gas from the high-pressure gas tank enters the annular air outlet 51 through the air inlet 53, and is then transported to the combustion chamber of the flame tube 2 through the multiple air outlet holes 52 circumferentially arranged on the annular air outlet 51. The air inlet 53 is located on one side of the annular air outlet 51, forming an asymmetrical structure of the volute 5. This reduces airflow loss and pressure pulsation within the volute 5, improves the total pressure recovery coefficient of the emergency power air intake system, and is compatible with the low-temperature, high-pressure gas source characteristics of the high-pressure gas tank. Alternatively, as an alternative implementation, the volute 5 can also be configured as a symmetrical structure, with two or more air inlets 53 evenly arranged circumferentially around the annular air outlet 51.

[0045] In one embodiment, such as Figure 1 , Figure 2 , Figure 6As shown, the diameter of the air outlet 52 has multiple values ​​along the circumference of the annular air outlet 51 to improve the uniformity of the air flow rate and velocity of the multiple air outlets 52. By selecting air outlets 52 with multiple values ​​along the circumference of the annular air outlet 51, in emergency power mode, the air flow rate and velocity are uniform throughout the entire circumference of the annular air outlet 51, enabling rapid and reliable ignition, stable and efficient combustion, and obtaining a suitable combustion chamber outlet temperature field. Alternatively, as an alternative implementation, the diameter of the air outlet 52 can also be the same along the circumference of the annular air outlet 51.

[0046] It should be further explained that, in emergency power mode, when the diameters of the air outlets 52 are the same, it is a full-ring equal-diameter air outlet method; when the diameters of the air outlets 52 are inconsistent, it is a full-ring unequal-diameter air outlet method. Comparing the two air outlet methods, the number of air outlets 52 is the same in both methods, and the total opening area of ​​the air outlets 52 is equal. For example... Figure 7 The diagram shows a comparison of the aperture distribution of the outlet holes 52 in the full-ring equal aperture outlet method and the full-ring unequal aperture outlet method. Figure 8 The image shows a comparison of the uniformity of the outlet flow rate of the outlet holes 52 in the all-ring equal-aperture outlet method and the all-ring unequal-aperture outlet method. The outlet flow rate in the all-ring equal-aperture outlet method is in the range of 1.4~6.8 g / s, while the outlet flow rate in the all-ring unequal-aperture outlet method is in the range of 3.2~5.2 g / s. It can be seen that the outlet flow rate in the all-ring unequal-aperture outlet method is more uniform. Figure 9 The figure shown is a simulation diagram of the exhaust velocity field for a uniform aperture exhaust system. Figure 10 The figure shown is a simulation diagram of the outlet velocity field for an all-ring unequal aperture outlet method. Figure 9 and Figure 10 The data comparison shows that the gas jet velocity of the two gas outlet methods is uniform, and the gas jet velocity of the full-ring equal aperture gas outlet method is in the range of 2~20m / s, while the gas jet velocity of the full-ring unequal aperture gas outlet method is in the range of 2~17m / s. It can be seen that the gas velocity field of the full-ring unequal aperture gas outlet method is more uniform.

[0047] According to an embodiment of the present invention, another aspect provides an engine, comprising: a fuel supply device and a dual-mode combustion chamber as described in the above embodiment, wherein the fuel supply device is connected to a nozzle 3 of the dual-mode combustion chamber. The fuel supply device delivers aircraft fuel to the nozzle 3, which then injects it into the combustion chamber within the flame tube 2. In the auxiliary power mode of the dual-mode combustion chamber, high-pressure airflow from the compressor enters the combustion chamber via the auxiliary power intake system. In the emergency power mode of the dual-mode combustion chamber, high-pressure airflow from the gas storage tank enters the combustion chamber via the emergency power intake system, causing the high-pressure airflow to mix and burn with aircraft fuel to generate power, thus achieving emergency power support across the entire flight envelope.

[0048] It should be further noted that the dual-mode combustor provided in this embodiment has its airflow organization and temperature field distribution verified through computational fluid dynamics (CFD) simulation. The results show that the combustion efficiency of the dual-mode combustor is greater than or equal to 98%. The intake switching mechanism has passed durability tests, achieving more than 1000 cycles without leakage, and has also passed the dual-mode combustor performance test. The dual-mode combustor provided in this embodiment is compatible with the third-generation Integrated Power Unit (IPU system) and can be applied to the auxiliary power systems of next-generation combat aircraft, civil aircraft, etc.

[0049] 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-mode combustion chamber, characterized in that, include: The casing (1) has a flame tube (2) inside, the flame tube (2) has a combustion chamber inside, and a nozzle (3) is provided on the flame tube (2). The nozzle (3) is connected to a fuel supply device and is used to inject fuel into the combustion chamber. An auxiliary power intake system is provided on the casing (1) and is connected to the flame tube (2); An emergency power intake system is installed on the casing (1) and is connected to the flame tube (2); An air intake switching mechanism is provided on the casing (1). The air intake switching mechanism is used to switch the connection state between the auxiliary power air intake system and the flame tube (2). In the auxiliary power mode of the dual-mode combustion chamber, the intake switching mechanism shuts down the emergency power intake system and turns on the auxiliary power intake system; in the emergency power mode of the dual-mode combustion chamber, the intake switching mechanism shuts down the auxiliary power intake system and turns on the emergency power intake system.

2. The dual-mode combustion chamber according to claim 1, characterized in that, The intake switching mechanism includes: A first switching component (6) is disposed on the auxiliary power intake system, and the first switching component (6) is used to turn off or on the auxiliary power intake system; A second switching component is disposed on the emergency power intake system, and the second switching component is used to turn the emergency power intake system off or on. In the auxiliary power mode of the dual-mode combustion chamber, the first switching component (6) turns on the auxiliary power intake system and the second switching component turns off the emergency power intake system. In the emergency power mode of the dual-mode combustion chamber, the first switching component (6) turns off the auxiliary power intake system and the second switching component turns on the emergency power intake system.

3. The dual-mode combustion chamber according to claim 2, characterized in that, The auxiliary power system is provided with a first air intake channel (4), the air intake end of the first air intake channel (4) is connected to the compressor, and the air outlet end of the first air intake channel (4) is connected to the flame tube (2). The first switching component (6) includes: a drive device, a transmission component and a sealing blade (63). The drive device is disposed on the casing (1). The sealing blade (63) is connected to the drive device through the transmission component. The sealing blade (63) is disposed in the first air intake channel (4). In the auxiliary power mode of the dual-mode combustion chamber, the drive device drives the sealing blade (63) to rotate to the first position through the transmission component, and the first air intake channel (4) is opened. In the emergency power mode of the dual-mode combustion chamber, the drive device drives the sealing blade (63) to rotate to the second position through the transmission component, and the first air intake channel (4) is closed.

4. The dual-mode combustion chamber according to claim 3, characterized in that, The transmission assembly includes: The first transmission member (61) is rotatably mounted on the casing (1). The first transmission member (61) is connected to the drive device. The first transmission member (61) is ring-shaped and has a first toothed structure in the circumferential direction. The second transmission member (62) is rotatably disposed on the casing (1). Multiple second transmission members (62) are disposed around the first transmission member (61). The second transmission member (62) is fan-shaped. A second tooth structure that meshes with the first tooth structure is disposed on the arc-shaped side of the second transmission member (62). The sealing blade (63) is disposed on the second transmission member (62).

5. The dual-mode combustion chamber according to claim 3, characterized in that, The first air intake channel (4) is provided with a radial diffuser (41) and an axial diffuser (42) at its outlet end, and the first switching component (6) is disposed between the radial diffuser (41) and the axial diffuser (42).

6. The dual-mode combustion chamber according to claim 3, characterized in that, The sealing blade (63) is made of lightweight material.

7. The dual-mode combustion chamber according to any one of claims 2-6, characterized in that, The emergency power intake system includes: a volute (5) and a high-pressure gas tank. The volute (5) is disposed on the casing (1). The second switching component is disposed on the volute (5). The volute (5) has a second intake channel inside. The intake end of the second intake channel is connected to the high-pressure gas tank. The outlet end of the second intake channel is connected to the flame tube (2). The second switching component is used to open or close the second intake channel.

8. The dual-mode combustion chamber according to claim 7, characterized in that, The volute (5) is provided with an annular vent (51) surrounding the circumference of the casing (1), and the annular vent (51) is provided with a plurality of vent holes (52) communicating with the interior of the casing (1). An air inlet (53) for connecting the high-pressure gas storage tank is provided on one side of the annular air outlet (51).

9. The dual-mode combustion chamber according to claim 8, characterized in that, Along the circumference of the annular air outlet (51), the diameter of the air outlet (52) has a variety of values ​​to improve the uniformity of the air flow rate and velocity of the multiple air outlets (52).

10. An engine, characterized in that, include: The fuel supply device and the dual-mode combustion chamber according to any one of claims 1-9, wherein the fuel supply device is connected to the nozzle (3) of the dual-mode combustion chamber.

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