Connection structure of large curved pipe of recirculation combustion chamber and turbine and aircraft engine

Abstract

The invention discloses a connection structure between a large bend pipe of a reflow combustion chamber and a turbine and an aircraft engine, comprising a large bend pipe matching structure and a turbine guide assembly, the turbine guide assembly comprising a support assembly and a turbine guide, the end of the turbine guide facing the combustion chamber being a matching end for matching with the large bend pipe matching structure; the large bend pipe has an outer layer and an inner layer, the large bend pipe matching structure comprising a first annular connecting structure formed on the outer wall of the outlet end of the inner layer of the large bend pipe, the first connecting structure is axially arranged along one side of the turbine guide assembly and enclosed with the inner layer of the large bend pipe to form a first annular groove, the matching end of the turbine guide extends into the groove and abuts against the outer annular surface of the groove, and the matching end of the turbine guide has an axial spacing with the bottom of the groove and a radial spacing with the outer annular surface of the groove, so that the outlet end of the large bend pipe has a certain movable gap, ensuring that the large bend pipe has sufficient movable space to release stress after deformation, and also preventing the large bend pipe from being affected by the deformation of the diffuser.

Description

Technical Field

[0001] The invention relates to the technical field of gas turbine engines, and in particular to a connection structure between a large bend pipe of a reflow combustion chamber and a turbine, and an aero-engine. Background Art

[0002] With the advancement of aviation engine technology, the cycle parameters of the engine are getting higher and higher, the inlet temperature and temperature rise of the combustion chamber are constantly increasing, and the compressor pressure ratio is gradually increasing. This makes the aerodynamic and thermal loads on the combustion chamber flame tube continue to increase, while the requirements for the design life of the combustion chamber are constantly increasing, and the requirements will be even higher in the future. The recirculation combustion chamber is a common structural form used in small and medium-sized gas turbine engines. It has the advantages of compact structure and short engine shaft system. The large elbow is a key component of the recirculation combustion chamber. Due to the design of the large elbow, the increase in cycle parameters leads to a significant increase in the aerodynamic and thermal stresses on the large elbow, which makes the large elbow prone to deformation, cracks and other problems, affecting the life and reliability of the combustion chamber.

[0003] At present, there are two main types of connection structures between the large elbow and the turbine. One is the bird's beak connection structure, or the turbine side is designed as a bird's beak, and the large elbow is inserted into the turbine, or the large elbow side is designed as a bird's beak structure, and the turbine guide is inserted into the large elbow. With the increase of cycle parameters, the aerodynamic force and thermal stress of the large elbow are significantly increased. Due to the simple bird's beak connection, it is easy to have serious leakage problems due to factors such as processing accuracy and deformation of the large elbow, which affects the design accuracy of the combustion chamber; the other connection structure is to bolt the large elbow and the turbine guide to the diffuser assembly. The large elbow outlet is connected to the diffuser assembly by bolts. On the one hand, it is not easy to release the stress of the large elbow through elastic deformation, and on the other hand, it is also easily affected by the deformation of the diffuser assembly. Summary of the invention

[0004] The invention provides a connection structure between a large curved pipe of a reflow combustion chamber and a turbine and an aero-engine, so as to solve the technical problems of deformation and cracks caused by stress concentration of the large curved pipe in the prior art.

[0005] The technical solution adopted by the present invention is as follows:

[0006] A connection structure between a large curved pipe of a reflow combustion chamber and a turbine, the connection structure comprising a large curved pipe matching structure and a turbine guide assembly,

[0007] The turbine guide assembly includes a support assembly and a turbine guide, wherein the support assembly is used to be fixed to the diffuser assembly and used to fix the turbine guide to the outlet end of the combustion chamber, and the end of the turbine guide facing the combustion chamber is a mating end, which is used to match the mating structure of the large elbow;

[0008] The large bend pipe comprises a large bend pipe outer layer fixed to the diffuser assembly and a large bend pipe inner layer fixed to the diffuser assembly, the large bend pipe mating structure comprises a first annular connecting structure formed on the outer wall of the outlet end of the large bend pipe inner layer, the first connecting structure is axially arranged on one side toward the turbine guide assembly and is surrounded by the outer wall of the large bend pipe inner layer to form a first annular groove, the mating end of the turbine guide extends into the first annular groove, the mating end of the turbine guide abuts against the outer annular surface of the inner wall of the first annular groove, and the mating end of the turbine guide has an axial spacing with the bottom of the first annular groove and a radial spacing with the inner annular surface of the inner wall of the first annular groove.

[0009] As a further improvement of the above technical solution, the first connecting structure is axially directed toward the combustion chamber and is surrounded by the outer wall of the inner layer of the large bend pipe to form a second annular groove, which is used to allow the outlet end of the outer layer of the large bend pipe to extend into the second annular groove for cooperation.

[0010] As a further improvement of the above technical solution, the large bend pipe matching structure also includes a second connecting structure in an annular shape, which is formed on the outer wall of the outlet end of the outer layer of the large bend pipe and extends radially outward and axially toward the direction of the turbine guide assembly. The second connecting structure is surrounded by the outer wall of the outer layer of the large bend pipe along the side facing the turbine guide assembly to form a third annular groove, which is used to allow the first connecting structure to extend into the third annular groove when the end of the outlet end of the outer layer of the large bend pipe extends into the second annular groove, thereby forming an interlocking structure with the second annular groove.

[0011] As a further improvement of the above technical solution, the support assembly includes a first support member fixedly connected to the diffuser assembly and a second support member fixedly connected to the diffuser assembly, which are used to respectively support the two sides of the outer annular surface of the turbine guide; a fourth annular groove is formed at one end of the first support member facing the combustion chamber; the inner annular surface of the second connecting structure is located outside the outer annular surface of the first connecting structure, and the end of the second connecting structure extends into the fourth annular groove and has an axial air gap with the fourth annular groove.

[0012] As a further improvement of the above technical solution, the second connecting structure is provided with a first air film hole for connecting the inner annular surface of the second connecting structure with the combustion chamber.

[0013] As a further improvement of the above technical solution, the inner annular surface of the first support member is connected to the first side of the outer annular surface of the turbine guide, and the inner annular surface of the second support member is connected to the second side of the outer annular surface of the turbine guide; the first side of the outer annular surface of the turbine guide radially protrudes to form a first lap plate, the first lap plate abuts against the inner annular surface of the first support member, and the inner annular surface of the first support member also radially protrudes to form a second lap plate for overlapping with the first lap plate.

[0014] As a further improvement of the above technical solution, the first support member axially protrudes toward the second support member to form a third lap plate, and the second support member axially protrudes toward the first support member to form a fourth lap plate, and the third lap plate and the fourth lap plate are overlapped.

[0015] As a further improvement of the above technical solution, the first connecting structure is provided with a second air film hole, which is used to connect the first annular groove and the second annular groove, and the radial position of the second air film hole is located between the outer layer of the large bend pipe and the inner layer of the large bend pipe.

[0016] As a further improvement of the above technical solution, the outer wall of the inner layer of the large curved pipe radially protrudes to form a radial boss, and a plurality of the radial bosses are evenly arranged in the first annular groove along the circumference of the outer wall of the inner layer of the large curved pipe, and the radial bosses are used to make a radial air gap between the turbine guide device and the inner layer of the large curved pipe when the inner layer of the large curved pipe abuts against the mating end of the turbine guide device;

[0017] The end of the first connection structure protrudes axially to form an axial boss, and a plurality of the axial bosses are evenly arranged along the circumferential direction on the end surface of the first connection structure, and the axial bosses are used to allow an axial air gap to exist between the turbine guide assembly and the first connection structure when the first connection structure abuts against the turbine guide assembly;

[0018] An axial spacing is provided between the first connection structure and the turbine guide assembly.

[0019] On the other hand, an aircraft engine is also provided, which is equipped with any of the above-mentioned connection structures between the large bend pipe of the reflow combustion chamber and the turbine.

[0020] The present invention has the following beneficial effects: the large bend pipe matching structure forms a first annular groove by setting a first connection structure and enclosing the outer wall of the inner layer of the large bend pipe, and the matching end of the turbine guide extends into the first annular groove and abuts against the outer annular surface of the inner wall of the first annular groove, so as to keep it relatively fixed and prevent air leakage; the matching end of the turbine guide has an axial spacing with the groove bottom of the first annular groove, that is, there is enough axial activity space to release stress, and at the same time, the axial activity range is limited to prevent it from coming out and avoiding vibration, and it has a radial spacing with the outer annular surface of the first annular groove, that is, there is enough radial activity space to release stress, and at the same time, the radial activity range is limited to prevent it from coming out and avoiding vibration; in the working state, the matching end of the turbine guide keeps abutting against the first annular groove to prevent air leakage and increase friction at the same time, and avoid large displacement caused by impact and vibration. Based on the axial spacing and radial spacing between the two, the outlet end of the large bend pipe has a certain activity gap, so as to ensure that the large bend pipe has enough activity space to release stress after deformation, and thus the large bend pipe can be prevented from being affected by the deformation of the diffuser assembly.

[0021] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0023] Figure 1 It is a structural schematic diagram of a preferred embodiment of the present invention;

[0024] Figure 2 yes Figure 1 A partial enlarged view of

[0025] Figure 3 It is a partial structural schematic diagram of a preferred embodiment of the present invention;

[0026] Figure 4 is a schematic structural diagram of a first supporting member in a preferred embodiment of the present invention;

[0027] 1. Support assembly 11, first support member 111, fourth annular groove 12, second support member 13, second lap plate 14, third lap plate 15, bolt 16, fourth lap plate 2, turbine guide 21, mating end 22, first lap plate 3, casing 4, large bend pipe outer layer 41, second connection structure 411, first air film hole 42, third annular groove 5, large bend pipe inner layer 51, first connection structure 511, second air film hole 512, axial boss 52, first annular groove 521, radial boss 53, second annular groove 6, fuel nozzle 7, diffuser assembly 8, combustion chamber flame tube DETAILED DESCRIPTION

[0028] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present 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.

[0029] Reference Figures 1 to 4 The preferred embodiment of the present invention provides a connection structure between a large curved pipe of a reflow combustion chamber and a turbine, the connection structure comprising a large curved pipe matching structure and a turbine guide assembly,

[0030] The turbine guide assembly includes a support assembly 1 and a turbine guide 2. The support assembly 1 is fixed to the diffuser assembly 7 and is used to fix the turbine guide 2 to the outlet end of the combustion chamber. The end of the turbine guide 2 facing the combustion chamber is a mating end 21, which is used to match the large elbow mating structure.

[0031] The large bend pipe has a large bend pipe outer layer 4 fixed to the diffuser assembly 7 and a large bend pipe inner layer 5 fixed to the diffuser assembly 7. The large bend pipe mating structure includes a first annular connecting structure 51 formed on the outer wall of the outlet end of the large bend pipe inner layer 5. The first connecting structure 51 is axially toward the turbine guide assembly and is surrounded by the outer wall of the large bend pipe inner layer 5 to form a first annular groove 52. The mating end 21 of the turbine guide 2 extends into the first annular groove 52. The mating end 21 of the turbine guide 2 abuts against the inner annular surface of the inner wall of the first annular groove 52. In addition, the mating end 21 of the turbine guide 2 has an axial spacing with the bottom of the first annular groove 52 and a radial spacing with the outer annular surface of the inner wall of the first annular groove 52.

[0032] It should be understood that the combustion chamber flame tube 8 is connected to the fuel nozzle 6, and the arrangement and working principle of the combustion chamber casing 3 and the diffuser assembly 7 are mature existing technologies;

[0033] It can be understood that the large bend pipe matching structure forms a first annular groove 52 by setting a first connecting structure 51 and enclosing the outer wall of the large bend pipe inner layer 5. The matching end 21 of the turbine guide 2 extends into the first annular groove 52 and abuts against the outer annular surface of the inner wall of the first annular groove 52 to maintain relative fixity and prevent air leakage; the matching end 21 of the turbine guide 2 and the bottom of the first annular groove 52 have an axial spacing, that is, there is enough axial activity space to release stress, and at the same time, the axial activity range is limited to prevent it from coming out and avoiding vibration. It has a radial spacing with the outer annular surface of the inner wall of the first annular groove 52. In the working state, the mating end 21 of the turbine guide vane 2 is kept in contact with the outer annular surface of the inner wall of the first annular groove 52 to prevent air leakage and increase friction, and avoid large displacement caused by impact and vibration. Based on the axial and radial spacing between the two, the outlet end of the large bend has a certain movable gap, which ensures that the large bend has sufficient movable space to release stress after deformation, thereby preventing the large bend from being affected by the deformation of the diffuser assembly 7.

[0034] Furthermore, the first connecting structure 51 is axially arranged along one side toward the combustion chamber and is enclosed with the outer wall of the large bend pipe inner layer 5 to form a second annular groove 53, which is used to allow the end of the outlet end of the large bend pipe outer layer 4 to extend into the second annular groove 53 for cooperation. Because the large bend pipe outer layer 4 is located on the cold air side, the deformation amount under the working state is smaller than that of the large bend pipe inner layer 5. Based on the above structure, the large bend pipe inner layer 5 and the large bend pipe outer layer 4 can maintain overlap when the deformation amounts are different. At the same time, the setting of the second annular groove 53 forms an impact cavity between the large bend pipe inner layer 5 and the large bend pipe outer layer 4. By using the impact combined with divergent cooling method, the cooling efficiency of the cooling gas is improved, the wall temperature is reduced, and the service life of the flame tube is increased.

[0035] Furthermore, the large bend pipe matching structure also includes a second connecting structure 41 in an annular shape, which is formed on the outer wall of the outlet end of the large bend pipe outer layer 4 and extends radially outward and axially toward the turbine guide assembly. The second connecting structure 41 is surrounded by the outer wall of the large bend pipe outer layer 4 along the side facing the turbine guide assembly to form a third annular groove 42, which is used to make the first connecting structure 51 extend into the third annular groove 42 when the end of the outlet end of the large bend pipe outer layer 4 extends into the second annular groove 53, and cooperate with the second annular groove 53 to form an interlocking structure. Based on the above structure, while there is a movable gap at the outlet end of the large bend pipe, the interlocking structure set can prevent air leakage caused by deformation of the large bend pipe, reduce the amount of leakage, and thus achieve precise control of the turbine cooling air volume, thereby improving efficiency and work performance.

[0036] In this embodiment, the outer wall of the inner layer 5 of the large curved pipe is radially protruded to form a radial boss 521, and multiple radial bosses 521 are evenly arranged along the circumference of the outer wall of the inner layer 5 of the large curved pipe in the first annular groove 52. The radial boss 521 is used to make a radial air gap between the turbine guide device 2 and the inner layer 5 of the large curved pipe when the inner layer 5 of the large curved pipe is in contact with the matching end 21 of the turbine guide device 2; the end of the first connecting structure 51 is axially protruded to form an axial boss 512, and multiple axial bosses 512 are evenly arranged along the circumference on the end surface of the first connecting structure 51, and the axial boss 512 is used to connect the first connecting structure 51 with the turbine guide group. When the parts are abutted, an axial air gap is created between the turbine guide assembly and the first connecting structure 51, ensuring that a gap is retained for smooth circulation of cooling air after thermal deformation of the large bend pipe matching structure, so that the introduced cold air flows out through the axial air gap between the turbine guide assembly and the first connecting structure 51, the axial spacing between the groove bottom of the first annular groove 52 and the turbine guide assembly, and the radial air gap between the turbine guide 2 and the inner layer 5 of the large bend pipe. The radial air gap formed by the circumferentially uniformly spaced arrangement can ensure that the cooling gas flows out at high speed from the narrow gap while achieving circumferentially uniform coverage, forming an air film with good wall adhesion to protect the root of the turbine guide vane.

[0037] In this embodiment, there is an axial spacing between the first connection structure 51 and the turbine guide assembly, and thus there is an axial movable space to adapt to the thermal deformation of the large elbow and to introduce and circulate the cooling gas at the same time.

[0038] In this embodiment, the support assembly 1 includes a first support member 11 and a second support member 12, the inner annular surface of the first support member 11 is connected to the first side of the outer annular surface of the turbine guide 2, and the inner annular surface of the second support member 12 is connected to the second side of the outer annular surface of the turbine guide 2. The first support member 11 and the second support member 12 are locked and fixed to the diffuser assembly 7 by a bolt 15, so as to support the two sides of the outer annular surface of the support assembly 1 respectively; a fourth annular groove 111 is formed at one end of the first support member 11 facing the combustion chamber; the inner annular surface of the second connecting structure 41 is located outside the outer annular surface of the first connecting structure 51, and the end of the second connecting structure 41 extends into the fourth annular groove 111 and has an axial air gap with the fourth annular groove 111. Since the outer layer 4 of the large bend pipe is located on the cold air side, the deformation amount is small in the working state, and the axial air gap between the two can be controlled by controlling the overlap size of the second connecting structure 41 of the outer layer 4 of the large bend pipe and the fourth annular groove 111 of the first support member 11, thereby reducing the leakage;

[0039] Furthermore, the second connection structure 41 is provided with a first air film hole 411, which is used to connect the inner annular surface of the second connection structure 41 with the combustion chamber, so that the cooling air outside the outer layer 4 of the large bend pipe can be introduced through the first air film hole 411, and flow out through the axial air gap between the turbine guide assembly and the first connection structure 51, the axial interval between the first connection structure 51 and the turbine guide assembly, and the radial air gap between the turbine guide 2 and the inner layer 5 of the large bend pipe;

[0040] Furthermore, the first connection structure 51 is provided with a plurality of second air film holes 511 evenly distributed in the circumferential direction, and the second air film holes 511 are used to connect the first annular groove 52 and the second annular groove 53, and the radial position of the second air film holes 511 is located between the outer layer 4 of the large bend pipe and the inner layer 5 of the large bend pipe, so that the cooling air of the hollow layer of the large bend pipe is introduced into the radial air gap between the turbine guide vane 2 and the inner layer 5 of the large bend pipe through the second air film holes 511, and flows out to form an air film;

[0041] Specifically, the axial air gap between the second connecting structure 41 and the bottom of the fourth annular groove 111 should be smaller than the axial spacing between the first connecting structure 51 and the first supporting member 11, thereby ensuring that when the second connecting structure 41 abuts against the bottom of the fourth annular groove 111 after the large bend is deformed, the first connecting structure 51 and the first supporting member 11 still retain an axial spacing, ensuring that the inner layer of the large bend has sufficient axial space to release thermal stress after heat deformation. At the same time, the amount of air leakage between the second connecting structure 41 and the first supporting member 11 can be accurately controlled to ensure a stable working state.

[0042] The outlet end of the large bend pipe of the connection structure has a movable space, and has movable gaps in the radial and axial directions, which ensures the stress release of the large bend pipe and prevents deformation caused by the deformation of the diffuser assembly 7; at the same time, by utilizing the characteristic that the outer layer 4 of the large bend pipe has a small deformation amount during the working process on the cold air side, the overlap size of the outer layer 4 of the large bend pipe and the supporting structure is accurately controlled to reduce the amount of air leakage; and by setting the axial boss 512 and the radial boss 521 to form an axial air gap and a radial air gap, the introduced cooling air flows out through the narrow gap, forming an air film with good wall adhesion to protect the guide vane root.

[0043] In this embodiment, a first lap plate 22 is radially protruded on the first side of the outer annular surface of the turbine guide vane 2, and the first lap plate 22 abuts against the inner annular surface of the first support member 11. The inner annular surface of the first support member 11 also radially protrudes to form a second lap plate 13 for overlapping with the first lap plate 22, thereby axially and radially positioning the turbine guide vane 2. By setting the aforementioned support assembly 1, the large bend pipe, the turbine guide vane 2, and the diffuser assembly 7 are connected, thereby ensuring that the movable space at the outlet end of the large bend pipe is not affected by the deformation of the diffuser assembly 7.

[0044] In this embodiment, the first support member 11 axially protrudes toward the direction of the second support member 12 to form a third lap plate 14, and the second support member 12 axially protrudes toward the direction of the first support member 11 to form a fourth lap plate 16. The third lap plate 14 and the fourth lap plate 16 are overlapped to provide auxiliary support to avoid the influence caused by thermal deformation.

[0045] By separately designing the overlap structure between the inner layer 5 of the large bend pipe and the outer layer 4 of the large bend pipe and the overlap structure with the turbine guide vane 2, the advantages of the low operating temperature and small deformation degree of the outer layer 4 of the large bend pipe are fully utilized to accurately control the overlap size of the outer layer 4 of the large bend pipe and the turbine guide vane 2, thereby reducing the amount of air leakage.

[0046] Embodiment 1

[0047] The preferred embodiment of the present invention was numerically simulated and tested for verification. Compared with the existing combustion chamber structure, the numerical simulation analysis results show that the deformation of the large elbow is significantly reduced, and the temperature at the root of the combustion chamber outlet is relatively lower, which can meet the turbine cooling requirements.

[0048] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A connection structure between a large curved pipe of a recirculation combustion chamber and a turbine, characterized in that: The connection structure includes a large elbow matching structure and a turbine guide assembly, The turbine guide assembly comprises a support assembly (1) and a turbine guide (2); the support assembly (1) is used to be fixed to the diffuser assembly (7) and to fix the turbine guide (2) to the outlet end of the combustion chamber; the end of the turbine guide (2) facing the combustion chamber is a mating end (21) used to match the large elbow mating structure; The large bend pipe comprises a large bend pipe outer layer (4) fixed to the diffuser assembly (7) and a large bend pipe inner layer (5) fixed to the diffuser assembly (7); the large bend pipe matching structure comprises a first annular connecting structure (51) formed on the outer wall of the outlet end of the large bend pipe inner layer (5); the first connecting structure (51) is axially directed toward the turbine guide assembly and is surrounded by the outer wall of the large bend pipe inner layer (5) to form a first annular groove (52); the matching end (21) of the turbine guide (2) extends into the first annular groove (52); the matching end (21) of the turbine guide (2) abuts against the outer annular surface of the inner wall of the first annular groove (52); and the matching end (21) of the turbine guide (2) is axially spaced from the bottom of the first annular groove (52) and radially spaced from the inner annular surface of the inner wall of the first annular groove (52); the first connecting structure The structure (51) is axially arranged on one side toward the combustion chamber and is enclosed with the outer wall of the inner layer (5) of the large bend pipe to form a second annular groove (53), which is used to allow the outlet end of the outer layer (4) of the large bend pipe to extend into the second annular groove (53) for cooperation; the large bend pipe cooperation structure also includes an annular second connecting structure (41) formed on the outer wall of the outlet end of the outer layer (4) of the large bend pipe, which extends radially outward and axially toward the direction of the turbine guide assembly, and the second connecting structure (41) is enclosed with the outer wall of the outer layer (4) of the large bend pipe to form a third annular groove (42), which is used to allow the first connecting structure (51) to extend into the third annular groove (42) when the outlet end of the outer layer (4) of the large bend pipe extends into the second annular groove (53), thereby forming an interlocking structure with the second annular groove (53).

2. The connection structure of the large curved pipe of the recirculation combustion chamber and the turbine according to claim 1, characterized in that: The support assembly (1) comprises a first support member (11) fixedly connected to the diffuser assembly (7) and a second support member (12) fixedly connected to the diffuser assembly (7), and is used to respectively support two sides of the outer annular surface of the turbine guide vane (2); a fourth annular groove (111) is formed at one end of the first support member (11) facing the combustion chamber; the inner annular surface of the second connection structure (41) is located outside the outer annular surface of the first connection structure (51), and an end of the second connection structure (41) extends into the fourth annular groove (111) and has an axial air gap with the fourth annular groove (111).

3. The connection structure between the large curved pipe of the recirculation combustion chamber and the turbine according to claim 2, characterized in that: The second connection structure (41) is provided with a first air film hole (411) for connecting the inner annular surface of the second connection structure (41) with the combustion chamber.

4. The connection structure between the large curved pipe of the recirculation combustion chamber and the turbine according to claim 2, characterized in that: The inner annular surface of the first support member (11) is connected to the first side of the outer annular surface of the turbine guide (2), and the inner annular surface of the second support member (12) is connected to the second side of the outer annular surface of the turbine guide (2); the first side of the outer annular surface of the turbine guide (2) radially protrudes to form a first lap plate (22), the first lap plate (22) abuts against the inner annular surface of the first support member (11), and the inner annular surface of the first support member (11) also radially protrudes to form a second lap plate (13) for lap-joining with the first lap plate (22).

5. The connection structure between the large curved pipe of the recirculation combustion chamber and the turbine according to claim 4, characterized in that: The first support member (11) protrudes axially toward the second support member (12) to form a third lap plate (14), and the second support member (12) protrudes axially toward the first support member (11) to form a fourth lap plate (16), and the third lap plate (14) and the fourth lap plate (16) are overlapped.

6. The connection structure of the large curved pipe of the recirculation combustion chamber and the turbine according to claim 1, characterized in that: The first connection structure (51) is provided with a second air film hole (511), and the second air film hole (511) is used to connect the first annular groove (52) and the second annular groove (53), and the radial position of the second air film hole (511) is located between the outer layer (4) of the large curved pipe and the inner layer (5) of the large curved pipe.

7. The connection structure of the large elbow of the reflow combustion chamber and the turbine according to any one of claims 1 to 6, characterized in that: The outer wall of the inner layer (5) of the large curved pipe radially protrudes to form a radial boss (521), and a plurality of the radial bosses (521) are evenly arranged along the circumference of the outer wall of the inner layer (5) of the large curved pipe in the first annular groove (52), and the radial bosses (521) are used to provide a radial air gap between the turbine guide (2) and the inner layer (5) of the large curved pipe when the inner layer (5) of the large curved pipe abuts against the mating end (21) of the turbine guide (2); An axial boss (512) is formed at the end of the first connection structure (51) in an axially protruding manner, and a plurality of the axial bosses (512) are evenly arranged along the circumferential direction on the end surface of the first connection structure (51), and the axial bosses (512) are used to provide an axial air gap between the turbine guide assembly and the first connection structure (51) when the first connection structure (51) abuts against the turbine guide assembly; An axial spacing is provided between the first connection structure (51) and the turbine guide assembly.

8. An aircraft engine, characterized in that: The invention relates to a connection structure of a large bend pipe of a recirculation combustion chamber and a turbine as described in any one of claims 1 to 7.

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