Combustion chamber structure and aircraft engine

Abstract

The present invention discloses a combustion chamber structure and aircraft engine, comprising a flame tube, a combustion chamber casing, a fuel nozzle, a main combustion tube, a blending tube, and a transmission system. The transmission system is used to adjust the installation position and angular position of the main combustion tube to control the main combustion gas flow within the flame tube. The transmission system is also used to adjust the installation position and angular position of the blending tube to control the blending gas flow within the blending tube. The transmission system provided in this combustion chamber structure can control the installation position and angular position of the main combustion tube to adjust the position and intake angle of the first air inlet relative to the fuel nozzle and airflow, thereby controlling the flow direction of the main combustion gas flow. Adjustment is made according to different operating conditions to improve the combustion environment within the combustion chamber.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to a combustion chamber structure and an aero-engine. Background Art

[0002] The combustor is a critical component of an aviation auxiliary power unit (APU). Located between the compressor and turbine, the high-pressure air boosted by the compressor reacts fully with the aviation kerosene in the combustor, providing high-temperature, high-pressure combustion gas for the turbine. The combustor's aerodynamic and structural design is directly related to reliable ignition and stable combustion, which in turn affects performance parameters such as combustion efficiency and outlet temperature distribution, directly impacting overall engine performance.

[0003] The combustion chamber mainly consists of a flame tube, a combustion chamber casing, and a fuel nozzle. Its working principle is: when the engine is working, all the high-pressure air provided by the compressor flows into the flame tube through the small holes on the flame tube, mixes with the aviation kerosene injected by the fuel nozzle and burns, forming high-temperature and high-pressure combustion gas in the flame tube. The combustion gas is transported to the turbine through the flow channel for power conversion.

[0004] The main disadvantages of the existing combustion chamber structure:

[0005] 1) The positions of the main combustion holes and mixing holes on the flame tube of the combustion chamber remain unchanged. The small holes on the flame tube are composed of main combustion holes, mixing holes, diverging holes and air film cooling holes. The positions of the main combustion holes and mixing holes directly affect the size of the main combustion zone and mixing zone in the flame tube, and thus play an important role in the effective combustion and mixing of aviation kerosene. The opening positions of the main combustion holes and mixing holes on the flame tube of the existing combustion chamber cannot be changed. The size of the main combustion zone and mixing zone changes relatively little under various engine operating conditions, making it impossible for the performance of the combustion chamber to achieve optimal performance in all conditions;

[0006] 2) It is difficult for a single-structure combustion chamber to simultaneously meet the requirements for low carbon monoxide, nitrogen oxides, and hydrocarbons in pollutant emissions during a working cycle. In tests of combustion chambers with certain structures, carbon monoxide levels were measured to be higher than the requirements, but nitrogen oxides and hydrocarbons were lower than the requirements; in tests of combustion chambers with certain structures, nitrogen oxides were measured to be higher than the requirements, but carbon monoxide and hydrocarbons were lower than the requirements; in tests of combustion chambers with certain structures, all three levels were lower than the requirements, but only slightly less. Once the performance declines, emissions may exceed the standards, resulting in great pressure on the combustion chamber structure design. Summary of the Invention

[0007] The present invention provides a combustion chamber structure and an aircraft engine to solve the technical problem that the main combustion area and the mixing area of the existing combustion chamber structure cannot be adjusted to adapt to the engine working state.

[0008] The technical solution adopted in the present invention is as follows:

[0009] A combustion chamber structure includes a flame tube, a combustion chamber casing, a fuel nozzle, a main combustion tube, a mixing tube and a transmission system. The transmission system is used to adjust the installation position and angular position of the main combustion tube to control the main fuel gas flow in the flame tube. The transmission system is also used to adjust the installation position and angular position of the mixing tube to control the mixed gas flow in the mixing tube.

[0010] As a further improvement of the above technical solution, the combustion chamber structure also includes a mounting base for installing the main combustion cylinder and the mixing cylinder, and the mounting base is respectively provided with a first mounting groove for limiting the installation position adjustment range of the main combustion cylinder and a second mounting groove for limiting the installation position adjustment range of the mixing cylinder.

[0011] As a further improvement of the above technical solution, the transmission system includes a first rotating shaft arranged on the mounting seat on one side of the first mounting groove and a second rotating shaft arranged on the mounting seat on one side of the second mounting groove; the first rotating shaft is connected to the main combustion cylinder through a first connecting rod, and the first rotating shaft is used to be driven to rotate to swing the first connecting rod to drive the main combustion cylinder to move in the first mounting groove, and the first mounting groove is an arc-shaped groove and the curvature matches the swing curvature of the first connecting rod; the second rotating shaft is connected to the mixing cylinder through a second connecting rod, and the second rotating shaft is used to be driven to rotate to swing the second connecting rod to drive the mixing cylinder to move in the second mounting groove, and the second mounting groove is an arc-shaped groove and the curvature matches the swing curvature of the second connecting rod.

[0012] As a further improvement of the above technical solution, the first rotating shaft and the second rotating shaft are both gear shafts; a first gear meshing with the teeth of the first rotating shaft is coaxially fixed on the main combustion cylinder, and the first gear can be connected to the first connecting rod by rotating along its own axis; a second gear meshing with the teeth of the second rotating shaft is coaxially fixed on the mixing cylinder, and the second gear can be connected to the second connecting rod by rotating along its own axis.

[0013] As a further improvement of the above technical solution, the first rotating shaft and the first gear are set according to a first transmission ratio; the second rotating shaft and the second gear are set according to a second transmission ratio.

[0014] As a further improvement of the above technical solution, the first connecting rod has a first preset length, and the second connecting rod has a second preset length.

[0015] As a further improvement of the above technical solution, the mounting seat is arranged on the flame tube and serves as a flame tube sealing seat.

[0016] As a further improvement of the above technical solution, the transmission system includes a first driving member for driving the first rotating shaft to rotate and a second driving member for driving the second rotating shaft to rotate, or the transmission system includes a linkage driving member for synchronously driving the first rotating shaft to rotate and driving the second rotating shaft to rotate.

[0017] As a further improvement of the above technical solution, the linkage drive member is a gear shaft, and the transmission system also includes a first tooth sleeve arranged on the first rotating shaft and a second tooth sleeve arranged on the second rotating shaft; the first tooth sleeve is provided with teeth for engaging with the linkage drive member, and the second tooth sleeve is provided with teeth for engaging with the linkage drive member.

[0018] According to another aspect of the present invention, there is provided an aircraft engine, which is equipped with any of the above-mentioned combustion chamber structures.

[0019] The present invention has the following beneficial effects: in the working state, the combustion chamber structure receives the high-pressure air flowing in from the compressor, and the high-pressure air enters the channel between the flame tube and the combustion chamber casing. Part of the high-pressure air enters the main combustion tube through the first air inlet hole and enters the interior of the flame tube from the main combustion hole. The high-pressure air entering the flame tube from the main combustion hole will react with the aviation kerosene atomized by the fuel nozzle to form high-temperature and high-pressure combustion gas. Part of the high-pressure air enters the mixing tube through the second air inlet hole and enters the interior of the flame tube from the mixing hole. The high-pressure air entering the flame tube from the mixing hole will be used for mixing the high-temperature combustion gas. The transmission system provided in this combustion chamber structure can control the installation position of the main combustion tube and the main combustion tube. Angular position, to adjust the position and intake angle of the first air intake hole relative to the fuel nozzle and the airflow, so as to control the flow direction of the main fuel gas flow, and adjust according to different working conditions to improve the combustion environment in the combustion chamber; similarly, the transmission system can control the installation position of the mixing cylinder and the angular position of the mixing cylinder, to adjust the position and intake angle of the second air intake hole relative to the fuel nozzle and the airflow, so as to control the flow direction of the mixed airflow, and adaptively adjust according to different working conditions to improve the combustion environment in the combustion chamber, adapt to the intake parameters under multiple working conditions, improve the working performance of the combustion chamber, effectively reduce pollutant emissions, and avoid the problem that the size of the main combustion zone and the mixing zone of the combustion chamber is difficult to control.

[0020] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0022] Figure 1 is a cross-sectional view of a preferred embodiment of the present invention;

[0023] Figure 2 yes Figure 1 A partial enlarged view of

[0024] Figure 3 This is a schematic structural diagram of a flame tube sealing seat according to a preferred embodiment of the present invention;

[0025] Figure 4 1 is a top view of the first sealing ring and the second sealing ring of the preferred embodiment of the present invention;

[0026] Figure 5 This is a top view of the flame tube sealing cover plate of a preferred embodiment of the present invention;

[0027] Figure 6 1. It is a top view of the casing sealing seat of the preferred embodiment of the present invention;

[0028] Figure 7 1 is a schematic diagram of the transmission system structure of a preferred embodiment of the present invention;

[0029] Figure 8 Schematic diagram of the airflow direction before the main combustion hole is adjusted in a preferred embodiment of the present invention;

[0030] Figure 9 Schematic diagram of the airflow direction after the main combustion hole is adjusted in a preferred embodiment of the present invention;

[0031] 10, flame tube 11, nozzle mounting hole 12, flame tube sealing seat 121, first mounting groove 122, second mounting groove 123, movable groove 13, first sealing ring 131, first through hole 132, first sealing plate 14, second sealing ring 141, second through hole 142, second sealing plate 15, first rotating shaft 16, second rotating shaft 17, flame tube body 18, flame tube sealing cover 181, first through groove 182, second through groove 183, first shaft mounting hole 184, second shaft Mounting hole 20, combustion chamber casing 21, nozzle fixing seat 22, casing sealing seat 221, first sleeve mounting hole 222, second sleeve mounting hole 23, casing barrel 30, fuel nozzle 40, main combustion barrel 41, first gear 42, first air inlet hole 43, main combustion hole 50, mixing barrel 51, second gear 52, second air inlet hole 53, mixing hole 60, transmission system 61, first connecting rod 62, first gear sleeve 63, second gear sleeve 64, linkage drive member 65, second connecting rod. DETAILED DESCRIPTION

[0032] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0033] Reference Figures 1 to 9 A preferred embodiment of the present invention provides a combustion chamber structure, including a flame tube 10, a combustion chamber casing 20, a fuel nozzle 30, a main combustion tube 40, a mixing tube 50 and a transmission system 60. The transmission system 60 is used to adjust the installation position and angular position of the main combustion tube 40 to control the main gas flow in the flame tube 10. The transmission system 60 is also used to adjust the installation position and angular position of the mixing tube 50 to control the mixed air flow in the mixing tube 50.

[0034] The flame tube 10 includes a flame tube body 17, which is provided with a nozzle mounting hole 11. The combustion chamber casing 20 includes a casing body 23, a casing sealing seat 22, and a nozzle fixing seat 21 mounted on the casing body 23. The fuel nozzle 30 is mounted on the nozzle fixing seat 21 and passes through the nozzle mounting hole 11. The main combustion tube 40 has a first air inlet hole 42 and a main combustion hole 43. The first air inlet hole 42 is opened on the side wall of the main combustion tube 40. The mixing tube 50 has a second air inlet hole 52 and a mixing hole 53. The second air inlet hole 52 is opened on the side wall of the mixing hole 53.

[0035] It can be understood that, in the working state, the combustion chamber structure receives the high-pressure air flowing in from the compressor, and the high-pressure air enters the channel between the flame tube 10 and the combustion chamber casing 20. Part of the high-pressure air enters the main combustion tube 40 through the first air inlet hole 42 and enters the interior of the flame tube 10 from the main combustion hole 43. The high-pressure air entering the flame tube 10 from the main combustion hole 43 will react with the aviation kerosene atomized by the fuel nozzle 30 to form high-temperature and high-pressure combustion gas. Part of the high-pressure air enters the mixing tube 50 through the second air inlet hole 52 and enters the interior of the flame tube 10 from the mixing hole 53. The high-pressure air entering the flame tube 10 from the mixing hole 53 will be used for mixing of high-temperature combustion gas. The transmission system 60 provided in this combustion chamber structure can control the installation position of the main combustion tube 40 And the angular position of the main combustion cylinder 40, so as to adjust the position and intake angle of the first air inlet 42 relative to the fuel nozzle 30 and the airflow, thereby controlling the flow direction of the main fuel gas flow, and adjusting according to different working conditions to improve the combustion environment in the combustion chamber; similarly, the transmission system 60 can control the installation position of the mixing cylinder 50 and the angular position of the mixing cylinder 50, so as to adjust the position and intake angle of the second air inlet 52 relative to the fuel nozzle 30 and the airflow, thereby controlling the flow direction of the mixed airflow, and adaptively adjusting according to different working conditions to improve the combustion environment in the combustion chamber, adapting to the intake parameters under multiple working conditions, improving the working performance of the combustion chamber, effectively reducing pollutant emissions, and avoiding the problem of difficulty in controlling the size of the main combustion zone and the mixing zone of the combustion chamber.

[0036] It should be understood that the working state of the combustion chamber structure includes but is not limited to the no-load state, the environmental control air bleed state, and the start-up state;

[0037] In this embodiment, the combustion chamber structure includes a mounting base for mounting the main combustion cylinder 40 and the dilution cylinder 50. The mounting base is respectively provided with a first mounting groove 121 for limiting the adjustment range of the installation position of the main combustion cylinder 40 and a second mounting groove 122 for limiting the adjustment range of the installation position of the dilution cylinder 50. That is, the main combustion cylinder 40 moves only within the range of the first mounting groove 121, and the dilution cylinder 50 moves only within the range of the second mounting groove 122. The adjustment range should be able to match various operating states of the engine.

[0038] Among them, this mounting seat is arranged on the flame tube 10 and serves as the flame tube sealing seat 12, and a flame tube sealing cover plate 18 is arranged on the flame tube sealing seat 12; a first through groove 181 and a second through groove 182 are arranged in the flame tube sealing cover plate 18, and specifically, a movable groove 123 is opened on the flame tube sealing seat 12 for embedding the first sealing ring 13 and the second sealing ring 14, the first sealing ring 13 has a first sealing plate 132 and a first through hole 131 opened in the first sealing plate 132, and the second sealing ring 14 has a second sealing plate 142 and a second through hole 141 opened in the second sealing plate 142; the flame tube sealing cover plate 18 is covered by the flame tube sealing seat 12 The first sealing ring 13 and the second sealing ring 14 are restricted between the flame tube sealing cover plate 18 and the flame tube sealing seat 12 and are movable in the movable groove 123. During assembly, the main combustion cylinder 40 passes through the first through groove 181 of the flame tube sealing cover plate 18 and then passes through the first through hole 131 opened on the first sealing ring 13. The mixing cylinder 50 passes through the second through groove 182 opened on the flame tube sealing cover plate 18 and then passes through the second through hole 141 opened on the second sealing ring 14. That is, when the installation position of the main combustion cylinder 40 is adjusted, the first sealing ring 13 moves in the movable groove 123 with the movement of the main combustion cylinder 40, thereby realizing gas sealing and preventing gas leakage. The same applies to the mixing cylinder 50.

[0039] In this embodiment, the transmission system 60 includes a first rotating shaft 15 arranged on the mounting seat on one side of the first mounting groove 121 and a second rotating shaft 16 arranged on the mounting seat on one side of the second mounting groove 122, and a first shaft mounting hole 183 and a second shaft mounting hole 184 are provided on the flame tube sealing cover 18; the first rotating shaft 15 is connected to the main combustion tube 40 through the first connecting rod 61, and the first rotating shaft 15 is used to be driven to rotate to swing the first connecting rod 61 so as to drive the main combustion tube 40 to move in the first mounting groove 121, and the first mounting groove 121 is an arc-shaped groove and the curvature matches the swing curvature of the first connecting rod 61; the second rotating shaft 16 is connected to the mixing tube 50 through the second connecting rod 65, and the second rotating shaft 16 is used to be driven to rotate to swing the second connecting rod 65 so as to drive the mixing tube 50 to move in the second mounting groove 122, and the second mounting groove 122 is an arc-shaped groove and the curvature matches the swing curvature of the second connecting rod 61. The swing arc of 65 matches; that is, driving the first rotating shaft 15 to rotate can drive the first connecting rod 61 to swing, so as to drive the main combustion cylinder 40 to move in the direction of the first rotating shaft 15, thereby adjusting the direction and position of the main combustion hole 43 on the main combustion cylinder 40, and driving the second rotating shaft 16 to rotate can drive the second connecting rod 65 to swing, thereby driving the mixing cylinder 50 to move in the direction of the second rotating shaft 16, thereby adjusting the direction and position of the mixing hole 53 on the mixing cylinder 50; it should be understood that the main combustion hole 43 is opened at the bottom of the main combustion cylinder 40 at a certain angle relative to the axial direction of the main combustion cylinder 40, so that the main gas flow flows out toward the bottom side thereof, and the main combustion cylinder 40 rotates around the first rotating shaft 15, thereby adjusting its installation position relative to the combustion chamber structure and the angle of the main combustion hole 43, thereby achieving the function of controlling the flow direction of the main gas flow, improving the combustion environment in the combustion chamber, and thus improving the performance of the combustion chamber; the design structure of the mixing hole 53 is similar;

[0040] Furthermore, the first rotating shaft 15 and the second rotating shaft 16 are both gear shafts; a first gear 41 meshing with the teeth of the first rotating shaft 15 is coaxially fixed on the main combustion cylinder 40, and the first gear 41 can be connected to the first connecting rod 61 rotatable along its own axis; a second gear 51 meshing with the teeth of the second rotating shaft 16 is coaxially fixed on the mixing cylinder 50, and the second gear 51 can be connected to the second connecting rod 65 rotatable along its own axis; that is, the first rotating shaft 15 is driven to rotate and causes the first connecting rod 61 to swing and drive the main combustion cylinder 40 to move, while the rotating first rotating shaft 15 is transmitted to the first gear 41 to drive the main combustion cylinder 40 to rotate around its own axis, further The angular position of the main combustion hole 43 is adjusted, and the angle of the main combustion hole 43 is changed. Then, the installation position and angular position angle of the main combustion hole 43 can be precisely controlled to match according to the working state, thereby improving the combustion environment in the combustion chamber and enhancing the performance. Similarly, the second rotating shaft 16 is driven to rotate and causes the second connecting rod 65 to swing and drive the mixing cylinder 50 to move. At the same time, the rotating second rotating shaft 16 transmits the power to the second gear 51 to drive the mixing cylinder 50 to rotate around its own axis, further adjusting the angular position of the mixing hole 53 and changing the angle of the mixing hole 53, thereby achieving the function of controlling the flow direction of the mixed airflow, improving the combustion environment in the combustion chamber, and thus improving the performance of the combustion chamber.

[0041] It should be understood that the first rotating shaft 15 and the first gear 41 are set according to the first transmission ratio; the first rotating shaft 15 and the second gear 51 are set according to the second transmission ratio. For example, when the first rotating shaft 15 has 30 teeth and the first gear 41 on the main burner 40 has 15 teeth, when the main burner 40 moves 24 degrees in the circumferential direction around the main gear shaft, the main burner 40 rotates 48 degrees in the circumferential direction around itself, thereby changing the position of the main burner 40 and further adjusting the angle of the main burner hole 43.

[0042] In this embodiment, the first connecting rod 61 has a first preset length, and the second connecting rod 65 has a second preset length.

[0043] In some embodiments, the transmission system 60 includes a first driving member for driving the first rotating shaft 15 to rotate and a second driving member for driving the second rotating shaft 16 to rotate, that is, driving members are respectively provided corresponding to the first rotating shaft 15 and the second rotating shaft 16 to control them respectively.

[0044] In this embodiment, the transmission system 60 includes a linkage drive member 64 for synchronously driving the first rotating shaft 15 and the second rotating shaft 16 to rotate. The linkage drive member 64 is actuated to simultaneously drive the first rotating shaft 15 and the second rotating shaft 16 to rotate, thereby realizing linkage control. The length of the first connecting rod 61, the length of the second connecting rod 65, the first transmission ratio, and the second transmission ratio are designed and matched according to the working mode requirements of different working states, so that the linkage drive member 64 can realize linkage control of the main combustion hole 43 and the mixing hole 53. When the linkage drive member 64 is actuated, the installation position and angular position of the two are adjusted to match the target adjustment results, making the structure of the transmission system 60 more streamlined, compact, and reasonable.

[0045] Specifically, the linkage driving member 64 is a gear shaft, and the transmission system 60 also includes a first gear sleeve 62 provided on the first rotating shaft 15 and a second gear sleeve 63 provided on the second rotating shaft 16. A first sleeve mounting hole 221 for penetrating the first gear sleeve 62 and a second sleeve mounting hole 222 for penetrating the second gear sleeve 63 are provided in the casing sealing seat 22; the first gear sleeve 62 is connected to the first connecting rod 61 after passing through the first sleeve mounting hole 221, and the second gear sleeve 63 is connected to the second connecting rod 65 after passing through the second sleeve mounting hole 222; the first gear sleeve 62 is provided with teeth for meshing with the linkage driving member 64, and the second gear sleeve 63 is provided with teeth for meshing with the linkage driving member 64, that is, the rotation of the linkage driving member 64 drives the first gear sleeve 62 to rotate, thereby driving the first connecting rod 61 to swing and driving the first rotating shaft 15 to rotate, and at the same time, the rotation of the second gear sleeve 63 drives the second connecting rod 65 to swing and drives the second rotating shaft 16 to rotate, thereby achieving common adjustment;

[0046] Furthermore, the teeth on the first gear sleeve 62 are arranged in a fan shape, and the range thereof matches the adjustment range to simplify the structure and weight; the teeth on the second gear sleeve 63 are arranged in the same manner.

[0047] On the other hand, this embodiment also provides an aircraft engine that utilizes the above-mentioned combustion chamber structure.

[0048] On the other hand, the combustion chamber structure of this embodiment can also be applied to structures such as gas turbines that require premixing of fuel oil or gas with air.

[0049] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A combustion chamber structure, characterized in that: The invention comprises a flame tube (10), a combustion chamber casing (20), a fuel nozzle (30), a main combustion tube (40), a mixing tube (50) and a transmission system (60), wherein the main combustion tube (40) has a first air inlet hole (42) and a main combustion hole (43), and the mixing tube (50) has a second air inlet hole (52) and a mixing hole (53). The transmission system (60) is used to adjust the installation position and angular position of the main combustion tube (40) so as to control the main fuel gas flow in the flame tube (10). The system (60) is also used to adjust the installation position and angular position of the mixing cylinder (50) so as to control the mixed airflow in the mixing cylinder (50); the combustion chamber structure also includes a mounting seat for mounting the main combustion cylinder (40) and the mixing cylinder (50), and the mounting seat is respectively provided with a first mounting groove (121) for limiting the installation position adjustment range of the main combustion cylinder (40) and a second mounting groove (122) for limiting the installation position adjustment range of the mixing cylinder (50); the transmission system The system (60) includes a first rotating shaft (15) provided on the mounting seat at one side of the first mounting groove (121) and a second rotating shaft (16) provided on the mounting seat at one side of the second mounting groove (122); the first rotating shaft (15) is connected to the main combustion barrel (40) through a first connecting rod (61), and the first rotating shaft (15) is used to be driven to rotate to swing the first connecting rod (61) so as to drive the main combustion barrel (40) in the first mounting groove (121). The mixing barrel (50) is connected to the mixing barrel (50) through the second connecting rod (65). The second rotating shaft (16) is driven to rotate to swing the second connecting rod (65) so as to drive the mixing barrel (50) to move in the second mounting groove (122). The second mounting groove (122) is an arc-shaped groove and the arc matches the swing arc of the second connecting rod (65).

2. The combustion chamber structure according to claim 1, characterized in that: The first rotating shaft (15) and the second rotating shaft (16) are both gear shafts; a first gear (41) is coaxially fixed on the main combustion cylinder (40) and meshes with the teeth of the first rotating shaft (15), and the first gear (41) can be connected to the first connecting rod (61) by rotating along its own axis; a second gear (51) is coaxially fixed on the mixing cylinder (50) and meshes with the teeth of the second rotating shaft (16), and the second gear (51) can be connected to the second connecting rod (65) by rotating along its own axis.

3. The combustion chamber structure according to claim 2, characterized in that: The first rotating shaft (15) and the first gear (41) are arranged at a first transmission ratio; and the second rotating shaft (16) and the second gear (51) are arranged at a second transmission ratio.

4. The combustion chamber structure according to any one of claims 1 to 3, characterized in that: The first connecting rod (61) has a first preset length, and the second connecting rod (65) has a second preset length.

5. The combustion chamber structure according to any one of claims 1 to 3, characterized in that: The mounting seat is arranged on the flame tube (10) and serves as a flame tube sealing seat (12).

6. The combustion chamber structure according to any one of claims 1 to 3, characterized in that: The transmission system (60) includes a first driving member for driving the first rotating shaft (15) to rotate and a second driving member for driving the second rotating shaft (16) to rotate.

7. The combustion chamber structure according to any one of claims 1 to 3, characterized in that: The transmission system (60) includes a linkage driving member (64) for synchronously driving the first rotating shaft (15) to rotate and driving the second rotating shaft (16) to rotate.

8. The combustion chamber structure according to claim 7, characterized in that: The linkage drive member (64) is a gear shaft, and the transmission system (60) further includes a first tooth sleeve (62) arranged on the first rotating shaft (15) and a second tooth sleeve (63) arranged on the second rotating shaft (16); the first tooth sleeve (62) is provided with teeth for engaging with the linkage drive member (64), and the second tooth sleeve (63) is provided with teeth for engaging with the linkage drive member (64).

9. An aircraft engine, characterized in that: The combustion chamber structure according to any one of claims 1 to 8 is applied.

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