Reflux combustion chamber head structure and aero-engine

Abstract

The invention discloses a backflow combustion chamber head structure and an aero-engine. The structure comprises a flame tube mechanism and a pneumatic atomization mechanism arranged between a cartridge receiver and the flame tube mechanism. The flame tube mechanism comprises a flame tube assembly used for being arranged in the cartridge receiver and a flow guide plate assembly which is arranged in the flame tube assembly in a penetrating mode in the axial direction and connected with the flame tube assembly in a floating and clamping mode. The pneumatic atomization mechanism comprises a swirler assembly and a fuel nozzle assembly which are coaxially arranged with the flame tube assembly, the swirler assembly is inserted into the flow guide plate assembly and fixed to the flame tube assembly, the spraying end of the fuel nozzle assembly is fixed to the swirler assembly, and the mounting end of the fuel nozzle assembly is used for being in floating connection with a cartridge receiver. The flame tube assembly, the swirler assembly and the fuel nozzle assembly are fixed into a whole, relative displacement of the flame tube assembly, the swirler assembly and the fuel nozzle assembly in the axial direction and the radial direction can be effectively prevented, it can be ensured that the center lines of the fuel nozzle assembly and the flame tube assembly are centered under all working conditions of an aero-engine, and it is ensured that fuel is evenly distributed.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular, to a recirculation combustion chamber head structure. Furthermore, it also relates to an aero-engine including this recirculation combustion chamber head structure. Background Technology

[0002] A gas turbine recirculation combustion chamber typically includes an outer casing, a flame tube located within the outer casing, a vortex generator mounted on the flame tube, and a fuel nozzle mounted on the outer casing. The vortex generator and fuel nozzle are usually assembled into a combined atomizing nozzle to provide a uniformly mixed fuel-air mixture into the flame tube, enabling efficient combustion within the combustion chamber.

[0003] In existing recirculating combustor head structures, a split-stage, two-stage radial vortex generator is typically used, consisting of a primary vortex generator and a secondary vortex generator. The secondary vortex generator is welded to the flame tube head, while the primary and secondary vortex generators are connected in a floating manner. The spray tip of the fuel nozzle is inserted into the primary vortex generator, and its mounting edge is bolted to the outer casing. Typically, the fuel nozzle and secondary vortex generator are connected in a radially and axially floating plug-in manner. In this design, under initial assembly or cold conditions, the centerline of the fuel nozzle coincides with the centerline of the primary vortex generator, and the spray tip of the fuel nozzle is aligned with the center of the flame tube head. However, when the aero-engine is operating, the wall temperature of the flame tube is much higher than that of the outer casing, resulting in a difference in radial thermal expansion between the flame tube and the combustor casing. This causes the centerlines of the fuel nozzle and the primary vortex generator to no longer coincide under hot conditions, leading to uneven distribution of gas flowing out of the vortex generator and fuel sprayed from the fuel nozzle, resulting in a poorer temperature distribution at the combustor exit.

[0004] In addition, to create a stable flow field at the head of the flame tube and ensure that the combustion chamber outlet temperature field meets design requirements, a guide plate is typically installed at the head of the flame tube, with the vortex generator inserted inside. The guide plate guides the airflow of the vortex generator, preventing the airflow at the flame tube head from being disturbed by the flame tube wall. Existing guide plates are fixed to the flame tube head wall by welding; however, welded structures are prone to flame tube deformation, which is detrimental to the flame tube's processing and shaping, and the thermal stress generated by welding shortens the flame tube's service life. Summary of the Invention

[0005] This invention provides a recirculation combustion chamber head structure to solve the technical problem in the prior art where the center lines of the fuel nozzle and the flame tube are misaligned during the operation of an aero-engine, resulting in uneven fuel distribution.

[0006] According to one aspect of the present invention, a recirculation combustion chamber head structure is provided, comprising: The flame tube mechanism includes a flame tube assembly disposed within a casing, and a baffle assembly that passes through the flame tube assembly axially and is floatingly engaged with the flame tube assembly. A pneumatic atomizing mechanism is used to be located between the casing and the flame tube assembly. The pneumatic atomizing mechanism includes a vortex assembly and a fuel nozzle assembly that are coaxially arranged with the flame tube assembly. The vortex assembly is inserted into the guide plate assembly and fixed to the flame tube assembly. The spray end of the fuel nozzle assembly is fixed to the vortex assembly, and the mounting end is used to float to the casing.

[0007] Furthermore, the flame tube assembly includes a flame tube with a fuel oil hole opened along the axial direction, and a fixing ring arranged around the outer periphery of the fuel oil hole and fixed to the outer wall of the flame tube; The baffle assembly is inserted axially into the fuel hole and engages with the opening of the fuel hole.

[0008] Furthermore, the deflector assembly includes a deflector that passes through the fuel hole and extends into the flame tube, and a support ring disposed outside the flame tube and located inside the fixing ring, the support ring being disposed around the outer wall of the deflector and fixed to the deflector; An annular groove for movably locking the flame tube is provided between the guide plate and the support ring. The annular groove extends axially to form a first limiting space for axial movement of the flame tube. A radial gap is provided between the outer wall of the guide plate and the inner wall of the flame tube.

[0009] Furthermore, the outer wall of the support ring is provided with a protrusion, and the fixed ring is provided with a groove for engaging the protrusion. The groove extends axially to form a second limiting space for the axial movement of the protrusion. A radial gap is provided between the fixed ring and the support ring.

[0010] Furthermore, the vortex generator assembly includes a primary vortex generator and a secondary vortex generator arranged sequentially along the axial direction of the fuel port toward the inside of the flame tube, with the primary vortex generator and the secondary vortex generator being fixedly connected. The secondary vortex generator is inserted into the guide plate and fixed with the retaining ring. The spray end of the fuel nozzle assembly is inserted into the primary vortex generator and fixed with the primary vortex generator.

[0011] Furthermore, the fuel nozzle assembly includes a fuel nozzle coaxially disposed and fixed on the swirl assembly, and a mounting edge disposed on the side of the fuel nozzle away from the swirl assembly. The mounting edge is used for a radial floating connection relative to the casing.

[0012] Furthermore, the fuel injector assembly also includes a resilient gasket for placement between the mounting edge and the casing, the resilient gasket being mounted on the mounting edge and / or for mounting on the casing.

[0013] Furthermore, the secondary eddy current generator is connected to the fixed ring by welding, and the weld is an intermittent annular weld.

[0014] Furthermore, cooling holes for introducing cooling gas are provided on the wall of the flame tube, and the cooling holes are set towards the outer wall of the guide plate.

[0015] According to another aspect of the present invention, an aircraft engine is also provided, including the aforementioned recirculation combustion chamber head structure.

[0016] The present invention has the following beneficial effects: The recirculation combustion chamber head structure of the present invention uses a flame tube mechanism located inside the casing to coaxially set the baffle assembly and the flame tube assembly and adopt a floating snap-fit ​​connection. This not only ensures that the baffle assembly and the flame tube assembly are always aligned to efficiently guide the airflow into the flame tube assembly, reduce the disturbance of the airflow on the wall of the flame tube assembly, and improve the flow field distribution in the combustion chamber, but also avoids the deformation and thermal stress concentration problems of the flame tube assembly caused by traditional welding methods. This improves the processing accuracy and service life of the flame tube assembly, and prevents the thermal expansion of the flame tube assembly in the combustion chamber from causing stress damage to the baffle assembly. The pneumatic atomizing mechanism located between the casing and the flame tube assembly effectively prevents relative displacement along the axial and radial directions by coaxially mounting and fixing the vortex generator assembly and fuel nozzle assembly with the flame tube assembly as a whole. Furthermore, the floating snap-fit ​​design between the guide vane assembly and the flame tube assembly, as well as the floating connection between the fuel nozzle assembly and the casing, effectively coordinates the radial thermal expansion differences between the flame tube assembly and the casing. This ensures that the centerlines of the fuel nozzle assembly, vortex generator assembly, and flame tube assembly are aligned under all operating conditions of the aero-engine, preventing uneven fuel distribution at the combustion chamber head, effectively improving the flow field distribution within the combustion chamber, and increasing combustion efficiency. Simultaneously, it avoids excessive stress or jamming caused by thermal expansion, improving the reliability and durability of the structure.

[0017] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0018] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the recirculation combustion chamber head structure according to a preferred embodiment of the present invention.

[0019] Legend: 10. Casing; 20. Flame tube mechanism; 21. Flame tube assembly; 211. Flame tube; 2111. Fuel port; 212. Retaining ring; 22. Deflector assembly; 221. Deflector; 222. Support ring; 30. Pneumatic atomizing mechanism; 31. Swirl assembly; 311. First-stage swirler; 312. Second-stage swirler; 32. Fuel nozzle assembly. Detailed Implementation

[0020] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0021] like Figure 1 As shown, the recirculation combustion chamber head structure of this embodiment includes a flame tube mechanism 20 and a pneumatic atomizing mechanism 30. The flame tube mechanism 20 is disposed within the casing 10, and the pneumatic atomizing mechanism 30 is disposed between the casing 10 and the flame tube mechanism 20, and is used to introduce a uniformly mixed oil-air mixture into the flame tube mechanism 20. The pneumatic atomizing mechanism 30 is fixed to the flame tube mechanism 20. Specifically, the flame tube mechanism 20 includes a flame tube assembly 21 disposed within the casing 10 and a baffle assembly 22 disposed at the combustion chamber head. The baffle assembly 22 passes through the flame tube assembly 21 axially and is floatingly snapped into connection with the flame tube assembly 21. Preferably, a floating gap is provided between the baffle assembly 22 and the flame tube assembly 21 in both the axial and radial directions. Compared with the rigid welding method used in the prior art for the deflector assembly 22 and the flame tube assembly 21, the floating installation of the deflector assembly 22 cuts off the transmission path of thermal deformation of the flame tube assembly 21 to the pneumatic atomizing mechanism 30, ensuring the alignment of the pneumatic atomizing mechanism 30 and the flame tube assembly 21. Furthermore, the deflector assembly 22 can efficiently guide the oil-air mixture entering the flame tube assembly 21, reducing the disturbance of the airflow to the wall of the flame tube assembly 21, improving the flow field distribution in the combustion chamber, and avoiding the deformation problem caused by the heat stress concentration of the flame tube assembly 21 due to welding. This improves the processing accuracy and service life of the flame tube assembly 21, and prevents stress damage to the deflector assembly 22 caused by the thermal expansion of the flame tube assembly 21 in the combustion chamber.

[0022] A pneumatic atomizing mechanism 30 is located at the head of the combustion chamber. The pneumatic atomizing mechanism 30 includes a fuel nozzle assembly 32 and a vortex generator assembly 31. The fuel nozzle assembly 32 and the vortex generator assembly 31 are arranged sequentially towards the flame tube assembly 21 along its axial direction. The vortex generator assembly 31 is inserted into the guide plate assembly 22 and fixed to the outside of the flame tube assembly 21. This allows the guide plate assembly 22 to move synchronously with the vortex generator assembly 31 when the vortex generator assembly 31 undergoes thermal expansion with the flame tube assembly 21, and to float radially between the flame tube assembly 21 and the vortex generator assembly 31. This ensures the alignment of the guide plate assembly 22 with the flame tube assembly 21 and avoids stress concentration in the guide plate assembly 22. The spray end of the fuel nozzle assembly 32 is fixed to the vortex generator assembly 31, and the mounting end of the fuel nozzle assembly 32 is used for a floating connection with the casing 10. Preferably, a floating gap is provided between the fuel nozzle assembly 32 and the casing 10 along both the axial and radial directions. Therefore, by coaxially aligning and fixing the vortex generator assembly 31, fuel nozzle assembly 32, and flame tube assembly 21 as a single unit, relative displacement along the axial and radial directions can be effectively prevented. Furthermore, the floating connection between one end of the pneumatic atomizing mechanism 30 and the flame tube assembly 21 via the guide vane assembly 22, and the floating connection between the other end and the casing 10 via the fuel nozzle assembly 32, effectively coordinates the thermal expansion differences between the flame tube assembly 21 and the casing 10. This ensures that the centerlines of the fuel nozzle assembly 32, vortex generator assembly 31, and flame tube assembly 21 are aligned under all operating conditions of the aero-engine, preventing uneven fuel distribution at the combustion chamber head, ensuring a stable fuel mist field at the combustion chamber head, effectively improving the flow field distribution within the combustion chamber, and increasing combustion efficiency. Simultaneously, it avoids excessive stress or jamming caused by thermal expansion, improving the reliability and durability of the structure.

[0023] like Figure 1 As shown, the flame tube assembly 21 includes a flame tube 211 and a retaining ring 212 located at the head of the combustion chamber. A fuel port 2111 is axially formed on the flame tube 211, with its axial centerline coinciding with that of the flame tube 211. The retaining ring 212 is encircled by the fuel port 2111 and fixed to the outer wall of the flame tube 211. The wall of the flame tube 211 extends radially into the retaining ring 212, forming a snap-fit ​​ring between the inner wall of the retaining ring 212 and the wall of the fuel port 2111. A baffle assembly 22 is axially inserted into the fuel port 2111, and the snap-fit ​​ring of the flame tube 211 is inserted into the outer wall of the baffle assembly 22, achieving a floating snap-fit ​​between the flame tube 211 and the baffle assembly 22.

[0024] like Figure 1As shown, the deflector assembly 22 includes a deflector 221 and a support ring 222. The deflector 221 passes axially through the fuel port 2111 and extends into the flame tube 211. The support ring 222 is located outside the flame tube 211 and inside the fixing ring 212, and is fixed to the outer wall of the deflector 221. Preferably, the support ring 222 and the deflector 221 are fixed by welding. During assembly, the deflector 221 can be inserted into the flame tube 211 first, and then the support ring 222 can be welded to the deflector 221 outside the flame tube 211 to facilitate the assembly of the deflector assembly 22 on the flame tube 211.

[0025] An annular groove is provided between the guide plate 221 and the support ring 222. The snap-fit ​​ring of the flame tube 211 is inserted into the annular groove to achieve a snap-fit ​​connection between the guide plate assembly 221 and the flame tube 211. The annular groove extends axially to form a first limiting space for the axial movement of the snap-fit ​​ring of the flame tube 211. Preferably, the axial width of the annular groove is 2mm to ensure that it can accommodate the snap-fit ​​ring of the flame tube 211 while also leaving a floating gap axially between it and the snap-fit ​​ring to accommodate the axial thermal expansion of the flame tube 211. Preferably, the fixing ring 212 has an air hole for introducing cooling gas, so that the annular groove can serve as a flow channel for cooling gas. The cooling gas introduced through the air hole flows into the space between the guide plate 221 and the flame tube 211 through the annular groove for cooling. The guide vane 221 is fitted against the inner wall of the flame tube 211 and extends axially a certain distance towards the interior of the flame tube 211. This efficiently guides the airflow entering the flame tube 211 through the fuel port 2111, reduces turbulence on the flame tube 211 wall, and improves combustion efficiency. Furthermore, a radial gap is provided between the outer wall of the guide vane 221 and the inner wall of the flame tube 211 to accommodate the radial thermal expansion of the flame tube 211 and prevent stress damage to the flame tube 211 caused by the guide vane 221. Preferably, the radial gap between the outer wall of the guide vane 221 and the inner wall of the flame tube 211 is 2 mm. Preferably, a radial floating gap is provided between the outer wall of the guide plate 221 and the wall of the fuel hole 2111, and between the outer wall of the support ring 222 and the inner wall of the fixing ring 212. Preferably, the radial floating gap between the outer wall of the guide plate 221 and the wall of the fuel hole 2111, and between the outer wall of the support ring 222 and the inner wall of the fixing ring 212, is smaller than the radial gap between the outer wall of the guide plate 221 and the inner wall of the flame tube 211. Optionally, the radial floating gap between the outer wall of the guide plate 221 and the wall of the fuel hole 2111, and between the outer wall of the support ring 222 and the inner wall of the fixing ring 212, is set to 1 mm.

[0026] like Figure 1As shown, the outer wall of the support ring 222 has a protrusion, and the inner wall of the fixing ring 212 has a groove. The protrusion and the groove are correspondingly arranged and engaged within the groove. Through the engaging engagement of the protrusion of the support ring 222 and the groove of the fixing ring 212, the guide vane assembly 22 can be circumferentially limited to prevent circumferential rotation and ensure the reliability of the connection between the guide vane assembly 22 and the flame tube assembly 21. Preferably, the groove extends through the wall of the fixing ring 212, and a circumferential clearance of 1 mm is provided between the groove and the protrusion. Optionally, the groove can also be formed on the inner wall of the fixing ring 212. The groove extends axially to form a second limiting space for the axial movement of the protrusion, so that the protrusion of the support ring 222 can also engage axially with the groove in the fixing ring 212. Preferably, two protrusions are provided along the circumference of the support ring 222, and two corresponding grooves are provided along the circumference of the fixing ring 212; alternatively, more than two grooves and protrusions can be provided.

[0027] like Figure 1 As shown, the vortex generator assembly 31 includes a primary vortex generator 311 and a secondary vortex generator 312 arranged sequentially along the axial direction of the fuel port 2111 towards the flame tube 211. The primary vortex generator and the secondary vortex generator 312 are fixedly connected, which can effectively prevent relative displacement between the primary vortex generator 311 and the secondary vortex generator 312 along the axial and radial directions, so that the primary vortex generator 311 and the secondary vortex generator 312 remain aligned in all operating states of the aero-engine. Preferably, the primary vortex generator 311 and the secondary vortex generator 312 are fixed together by welding.

[0028] The secondary vortex generator 312 includes a first end near the flame tube 211 and a second end near the casing 10. The first and second ends are integrally formed. The outer diameter of the first end of the secondary vortex generator 312 is adapted to the inner diameter of the guide plate 221 so that the secondary vortex generator 312 can be axially inserted into the guide plate 221 and sealed with the guide plate 221. Preferably, an elastic sealing ring is used to seal between the secondary vortex generator 312 and the guide plate 221 to prevent high-temperature gas leakage. The outer diameter of the second end of the secondary vortex generator 312 is larger than the outer diameter of the first end, and the outer diameter of the second end is adapted to the outer diameter of the fixing ring 212 so that the side of the second end of the secondary vortex generator 312 near the flame tube 211 axially covers the fixing ring 212 and is fixed to the fixing ring 212. The side of the second end of the secondary vortex generator 312 away from the flame tube 211 is fixed to the primary vortex generator 311. Therefore, by coaxially arranging and fixing the flame tube 211, the secondary vortex generator 312, and the primary vortex generator 311 as a whole, the relative radial movement between the primary vortex generator 311 and the secondary vortex generator 312 and the flame tube 211 during thermal expansion can be avoided. This ensures that the center lines of the vortex generator assembly 31 and the flame tube 211 remain aligned when the combustion chamber head is hot, ensuring uniform fuel distribution at the combustion chamber head and optimizing the temperature field inside the flame tube 211.

[0029] like Figure 1As shown, the fuel nozzle assembly 32 is disposed between the vortex generator assembly 31 and the housing 10. The fuel nozzle assembly 32 includes a fuel nozzle and a mounting edge fixed to one end of the fuel nozzle near the housing 10. The mounting edge is floatingly connected to the housing 10. The spray end of the fuel nozzle is located on the side near the vortex generator assembly 31 and fixed to the vortex generator assembly 31. The centerline of the spray end of the fuel nozzle coincides with the centerline of the vortex generator assembly 31 and the flame tube assembly 21. Specifically, the spray end of the fuel nozzle passes axially through the first-stage vortex generator 311 and is fixed to the first-stage vortex generator 311. The mounting edge and the housing 10 are respectively provided with mounting holes. The mounting edge is connected to the housing 10 by inserting bolts into the mounting holes. A radial gap is provided between the bolts and the mounting holes in the mounting edge to achieve a radial floating connection between the mounting edge and the housing 10. Preferably, a floating gap is also provided axially between the mounting edge and the housing 10. Optionally, the connection between the mounting edge and the housing 10 can also be as follows: the inner ring of the mounting edge has a groove, and the housing 10 has a corresponding ring platform. By movably locking the ring platform in the groove, the ring platform is limited both axially and radially within the groove. A gap exists both circumferentially and radially between the groove of the mounting edge and the ring platform of the housing 10, allowing the fuel nozzle assembly 32 to be floated between the mounting edge and the housing 10. Optionally, the ring platform can also be located at one end of the mounting edge near the housing 10, and the groove can be located inside the housing 10. Preferably, the fuel nozzle and the first-stage swirl generator 311 are fixed by welding. Therefore, when the flame tube 211 undergoes radial thermal expansion, the guide vane assembly 22 can float between the secondary vortex generator 312 and the flame tube 211. The fuel nozzle assembly 32, vortex generator assembly 31, and flame tube 211 are rigidly fixed and remain aligned, ensuring uniform fuel distribution at the combustion chamber head. Only the floating connection between the fuel nozzle assembly 32 and the casing 10 is needed to accommodate the overall displacement. In this embodiment, the fuel nozzle assembly 32, vortex generator assembly 31, and flame tube assembly 21 are fixed as a whole. In a hot state, both the flame tube assembly 21 and the casing 10 expand due to heat. At this time, the vortex generator assembly 31 fixed to the flame tube assembly 21 will drive the fuel nozzle assembly 32 to expand synchronously with the flame tube assembly 21. Thus, through the floating connection between the fuel nozzle assembly 32 and the casing 10, the thermal deformation difference between the flame tube assembly 21 and the casing 10 can be absorbed.

[0030] like Figure 1 As shown, the fuel nozzle assembly 32 also includes an elastic gasket disposed between the mounting edge and the housing 10. The elastic gasket is disposed between the housing 10 and the mounting edge and is mounted on the housing 10 and / or the mounting edge to provide buffering for radial and / or axial displacement between the fuel nozzle assembly 32 and the housing 10 under hot conditions. At the same time, it can improve the stability of the connection between the fuel nozzle assembly 32 and the housing 10 and reduce the wear of the fuel nozzle assembly 32 and the housing 10.

[0031] like Figure 1As shown, the secondary eddy current generator 312 and the fixed ring 212 are connected by laser welding. The weld seam of the laser welding is an intermittent annular weld seam, which can effectively reduce the thermal stress generated by welding and extend the service life of the flame tube assembly 21.

[0032] like Figure 1 As shown, cooling holes for introducing cooling gas are provided on the wall surface of the flame tube 211, and the cooling holes are arranged towards the outer wall of the guide plate 221. Multiple cooling holes are provided on the wall surface of the flame tube 211, and the arrangement of the multiple cooling holes is determined based on the wall temperature test results of the guide plate 221. Cooling gas flows from the cold gas side of the cooling holes into the combustion gas side to impact the guide plate 221, and then forms a cooling gas film between the inner wall of the flame tube 211 and the outer wall of the guide plate 221 to achieve cooling of the walls of the flame tube 211 and the guide plate 221.

[0033] According to another aspect of the present invention, an aero-engine is also provided, including the aforementioned recirculating combustor head structure. The combustor head of an aero-engine is highly sensitive to fuel distribution; misalignment of the fuel nozzle, vortex assembly 31, and flame tube 211 can lead to localized high temperatures or combustion oscillations. Applying this recirculating combustor head structure to an aero-engine, by employing a single floating point design between the flame tube 211 and the casing 10, can make the system more stable and improve the controllability of the fuel nozzle spray direction, effectively increasing the lifespan of the aero-engine and enhancing fuel consumption stability. The position of the fuel nozzle in this recirculating combustor head structure is not affected by deformation of the flame tube 211 and is compatible with variable geometry combustors.

[0034] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A recirculation combustion chamber head structure, characterized in that, include: The flame tube mechanism (20) includes a flame tube assembly (21) disposed in the casing (10) and a baffle assembly (22) axially inserted into the flame tube assembly (21) and floatingly engaged with the flame tube assembly (21). A pneumatic atomizing mechanism (30) is provided between the housing (10) and the flame tube mechanism (20). The pneumatic atomizing mechanism (30) includes a vortex assembly (31) and a fuel nozzle assembly (32) coaxially arranged with the flame tube assembly (21). The vortex assembly (31) is inserted into the guide plate assembly (22) and fixed to the flame tube assembly (21). The spray end of the fuel nozzle assembly (32) is fixed to the vortex assembly (31). The mounting end of the fuel nozzle assembly (32) is used for floating connection with the housing (10).

2. The recirculation combustion chamber head structure according to claim 1, characterized in that, The flame tube assembly (21) includes a flame tube (211) with a fuel hole (2111) opened along the axial direction, and a fixing ring (212) arranged around the outer periphery of the fuel hole (2111) and fixed to the outer wall of the flame tube (211); The deflector assembly (22) is axially inserted into the fuel hole (2111) and engages with the opening of the fuel hole (2111).

3. The recirculation combustion chamber head structure according to claim 2, characterized in that, The guide plate assembly (22) includes a guide plate (221) that passes through the fuel hole (2111) and extends into the flame tube (211), and a support ring (222) disposed outside the flame tube (211) and located inside the fixing ring (212). The support ring (222) is circumferentially disposed on the outer wall of the guide plate (221) and fixed to the guide plate (221). An annular groove for movably locking the flame tube (211) is provided between the guide plate (221) and the support ring (222). The annular groove extends axially to form a first limiting space for axial movement of the flame tube (211). A radial gap is provided between the outer wall of the guide plate (221) and the inner wall of the flame tube (211).

4. The recirculation combustion chamber head structure according to claim 3, characterized in that, The outer wall of the support ring (222) is provided with a protrusion, and the fixed ring (212) is provided with a groove for locking the protrusion. The groove extends axially to form a second limiting space for the axial movement of the protrusion. A radial gap is provided between the fixing ring (212) and the supporting ring (222).

5. The recirculation combustion chamber head structure according to claim 3, characterized in that, The vortex assembly (31) includes a primary vortex (311) and a secondary vortex (312) arranged sequentially along the axial direction of the fuel port (2111) toward the flame tube, wherein the primary vortex (311) and the secondary vortex (312) are fixedly connected. The secondary vortex generator (312) is inserted into the guide plate (221) and fixed to the fixing ring (212). The spray end of the fuel nozzle assembly (32) is inserted into the primary vortex generator (311) and fixed to the primary vortex generator (311).

6. The recirculation combustion chamber head structure according to claim 1, characterized in that, The fuel nozzle assembly (32) includes a fuel nozzle coaxially disposed with and fixed on the vortex assembly (31), and a mounting edge disposed on the side of the fuel nozzle away from the vortex assembly (31). The mounting edge is used for a floating connection relative to the housing (10) along the radial direction of the housing (10).

7. The recirculation combustion chamber head structure according to claim 6, characterized in that, The fuel nozzle assembly (32) further includes an elastic gasket for being disposed between the mounting edge and the housing (10), the elastic gasket being mounted on the mounting edge and / or for mounting on the housing (10).

8. The recirculation combustion chamber head structure according to claim 5, characterized in that, The secondary eddy current generator (312) and the fixed ring (212) are connected by welding, and the weld is an intermittent annular weld.

9. The recirculation combustion chamber head structure according to claim 3, characterized in that, The flame tube (211) has cooling holes on its wall surface for introducing cooling gas, and the cooling holes are arranged toward the outer wall of the guide plate (221).

10. An aircraft engine, characterized in that, The recirculation combustion chamber head structure includes any one of claims 1 to 9 above.

Images