Aero-engine exhaust nozzle structure

Abstract

The utility model discloses an aero-engine exhaust nozzle structure, which relates to the technical field of aero-engines and comprises an exhaust nozzle body, a mounting plate is fixedly mounted at the end of the exhaust nozzle body, a plurality of mounting pins are connected to the edge of the mounting plate in a penetrating manner, and a plurality of drainage pipes are connected to the side wall of the exhaust nozzle body. The ends of the multiple drainage pipes are connected with connectors, multiple drainage holes are formed in the side wall of the exhaust nozzle body, and the outer side of the exhaust nozzle body is connected with an auxiliary bearing structure. According to the aero-engine exhaust nozzle structure, through the arrangement of the auxiliary bearing structure, auxiliary bearing can be conducted on the connecting pipe of the exhaust nozzle, the connecting stability of the connecting pipe of the exhaust nozzle can be improved, the falling-off situation is prevented, through the arrangement of the connecting ring and the flow guide cover, airflow in the exhaust nozzle can be guided, and the connecting ring is not prone to falling off. And meanwhile, the condition of backflow of hot air flow can be avoided.

Description

Technical Field

[0001] This utility model relates to the field of aero-engine technology, and in particular to an aero-engine tail nozzle structure. Background Technology

[0002] The core engine of an aero-engine is a test device used to verify the performance of high-pressure components. During the test, the high-pressure gas that has passed through the compressor, combustion chamber, and turbine is discharged. The tail nozzle of an aero-engine is an important component of the aero-engine.

[0003] Chinese patent CN213899133U discloses a tail nozzle and a turbojet engine. The tail nozzle includes a nozzle body with an inlet and an outlet. The outlet sidewall is corrugated. The inlet connects to the combustion chamber of the turbojet engine, and the outlet connects to the outside air. A turbine casing is located at the inlet and can be connected to the outer wall of the turbojet engine's combustion chamber. An end-face casing is located at the outlet and connected to the outer casing of the turbojet engine. The end-face casing near the outlet has a corrugated structure, and the corrugated structure of the end-face casing and the corrugated structure of the outlet are integrally formed. A fuel line is integrally formed on the end-face casing for injecting fuel into the combustion chamber. With this structure, the tail nozzle is not only lightweight and has low manufacturing costs, but also solves the problems of easy cracking and extrusion deformation.

[0004] Traditional aero-engine exhaust nozzle structures lack supporting structures when cooling pipes supply cold air to the nozzle, making them prone to detachment. This not only affects the cooling function of the exhaust nozzle but may also cause safety hazards. Furthermore, the exhaust nozzle's airflow guidance effect is poor, resulting in hot airflow recirculation, which greatly reduces the exhaust nozzle's working efficiency and performance stability. Utility Model Content

[0005] The main objective of this invention is to provide a tailpipe structure for an aero-engine, which can effectively solve the problems mentioned in the background art regarding the traditional tailpipe structure for aero-engines. These problems include the lack of a supporting structure in the cooling pipes when cold air is introduced into the tailpipe, leading to a risk of detachment. This not only affects the cooling function of the tailpipe but may also cause safety hazards. Furthermore, the tailpipe's poor airflow guidance effect and the problem of hot air backflow significantly reduce its working efficiency and performance stability.

[0006] To achieve the above objectives, the technical solution adopted by this utility model is as follows:

[0007] An aero-engine tail nozzle structure includes a tail nozzle body, an mounting plate fixedly installed at the end of the tail nozzle body, multiple mounting pins penetrating the edge of the mounting plate, multiple drain pipes connected to the side wall of the tail nozzle body, connectors connected to the ends of the multiple drain pipes, multiple drain holes opened on the side wall of the tail nozzle body, and an auxiliary support structure connected to the outer side of the tail nozzle body.

[0008] As a further embodiment of this utility model, the auxiliary receiving structure includes a connecting sleeve, a support frame, a first card holder, and a second card holder. The connecting sleeve is fitted onto the outer surface of the tail nozzle body, the support frame is fixed to the outside of the connecting sleeve, the first card holder is fixedly installed at the end of the support frame, and the second card holder is located outside the first card holder.

[0009] As a further embodiment of this utility model, a connecting post is fixedly connected to the outer surface of the second card holder and inserted into the interior of the first card holder. A reset spring is connected between the connecting post and the first card holder. A fixing slot for accommodating the connecting post and the reset spring is opened inside the first card holder.

[0010] As a further embodiment of this utility model, the second card holder is movably connected to the first card holder via a connecting post and a return spring, and a card slot is formed between the first card holder and the second card holder.

[0011] As a further embodiment of this utility model, a connecting ring is fixedly connected to the inner wall of the tail nozzle body, and a flow guide is provided on the outer side of the connecting ring, with the flow guide and the connecting ring being in the same axial direction.

[0012] As a further embodiment of this utility model, the outer surface of the flow guide is fixedly connected with a snap-fit ​​post, and the inside of the connecting ring is provided with a snap-fit ​​groove that is adapted to the snap-fit ​​post. The flow guide is snapped into the snap-fit ​​groove and engaged with the connecting ring through the snap-fit ​​post.

[0013] The beneficial effects of this utility model are as follows: by setting an auxiliary support structure, the connecting pipe of the tail nozzle can be supported, which can improve the stability of the tail nozzle connecting pipe connection and prevent it from falling off.

[0014] By setting a connecting ring and a deflector, the airflow inside the tail nozzle can be guided, while preventing the hot airflow from flowing back. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure of an aero-engine tail nozzle structure according to the present invention.

[0016] Figure 2 This is a cross-sectional view of the tail nozzle body of an aero-engine tail nozzle structure according to the present invention.

[0017] Figure 3 This is a schematic diagram of an auxiliary support structure for an aero-engine tail nozzle structure according to the present invention.

[0018] Figure 4 This is a schematic diagram showing the connection between the No. 1 and No. 2 mounting brackets of an aero-engine tail nozzle structure according to this utility model.

[0019] Figure 5 This is a schematic diagram showing the connection of the connecting ring and the deflector of an aero-engine tail nozzle structure according to this utility model.

[0020] In the diagram: 1. Tail nozzle body; 2. Mounting plate; 3. Mounting pin; 4. Drain pipe; 5. Connector; 6. Drain hole; 7. Auxiliary support structure; 8. Connecting sleeve; 9. Support frame; 10. No. 1 clamp; 11. No. 2 clamp; 12. Connecting post; 13. Return spring; 14. Connecting ring; 15. Flow guide; 16. Snap-fit ​​post; 17. Snap-fit ​​groove. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] Example 1

[0023] Combination Figures 1-5 An aero-engine tail nozzle structure includes a tail nozzle body 1, an mounting plate 2 fixedly installed at the end of the tail nozzle body 1, multiple mounting pins 3 penetrating the edge of the mounting plate 2, multiple drain pipes 4 connected to the side wall of the tail nozzle body 1, connectors 5 connected to the ends of the multiple drain pipes 4, multiple drain holes 6 opened on the side wall of the tail nozzle body 1, and an auxiliary support structure 7 connected to the outer side of the tail nozzle body 1.

[0024] See Figure 1 and Figure 3 Furthermore, the auxiliary support structure 7 includes a connecting sleeve 8, a support frame 9, a first card holder 10, and a second card holder 11. The connecting sleeve 8 is sleeved on the outer surface of the tail nozzle body 1. The support frame 9 is fixed to the outside of the connecting sleeve 8. The first card holder 10 is fixedly installed at the end of the support frame 9. The second card holder 11 is located on the outside of the first card holder 10.

[0025] Specifically, the No. 1 clamp 10, together with the No. 2 clamp 11, limits and clamps the tail nozzle connecting pipe, while the connecting sleeve 8 and the support frame 9 provide auxiliary support, which can improve the stability of the tail nozzle connecting pipe connection and prevent it from falling off.

[0026] See Figure 3 and Figure 4 Furthermore, the outer surface of the second card holder 11 is fixedly connected to a connecting post 12 that is inserted into the first card holder 10. A return spring 13 is connected between the connecting post 12 and the first card holder 10. The first card holder 10 has a fixed slot for accommodating the connecting post 12 and the return spring 13. The second card holder 11 is movably connected to the first card holder 10 through the connecting post 12 and the return spring 13. A card slot is formed between the first card holder 10 and the second card holder 11.

[0027] Specifically, pull the second clamp 11, which unfolds relative to the first clamp 10. Insert the tail nozzle connecting pipe into the groove formed between the first clamp 10 and the second clamp 11. Release the second clamp 11, which moves relative to the first clamp 10 through the connecting post 12 and the return spring 13. The second clamp 11 cooperates with the first clamp 10 to clamp the connecting pipe.

[0028] Example 2

[0029] See Figure 1 , Figure 2 and Figure 5 Furthermore, based on Embodiment 1, the inner wall of the tail nozzle body 1 is fixedly connected to a connecting ring 14, and a flow guide 15 is provided on the outer side of the connecting ring 14. The flow guide 15 and the connecting ring 14 are in the same axial direction. A snap-fit ​​post 16 is fixedly connected to the outer surface of the flow guide 15. A snap-fit ​​groove 17 adapted to the snap-fit ​​post 16 is opened inside the connecting ring 14. The flow guide 15 is snapped into the snap-fit ​​groove 17 and engaged with the connecting ring 14 through the snap-fit ​​post 16.

[0030] Specifically, the deflector 15 is engaged with the connecting ring 14 by snapping the snap-fit ​​post 16 into the snap-fit ​​groove 17. The deflector 15 guides the hot and cold airflows flowing through the tail nozzle, while preventing the hot airflow from flowing back.

[0031] It should be noted that this utility model is a tailpipe structure for an aircraft engine. In use, the tailpipe is connected to the exhaust end of the aircraft engine through the mounting plate 2 and the mounting pin 3. The tailpipe is connected to the bleed air device of the aircraft engine through the drain pipe 4 and the connector 5. Cold air can be introduced into the tailpipe through the drain pipe 4 and the drain hole 6 to cool the tailpipe. Pulling the second clamp 11 unfolds the second clamp 11 relative to the first clamp 10. The tailpipe connecting pipe is placed into the groove formed between the first clamp 10 and the second clamp 11. Releasing the second clamp 11 allows it to move relative to the first clamp 10 through the connecting post 12 and the return spring 13. The second clamp 11, together with the first clamp 10, clamps the connecting pipe. At the same time, the connecting sleeve 8 and the support frame 9 provide auxiliary support, which can improve the stability of the tailpipe connecting pipe connection and prevent it from falling off.

[0032] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model.

Claims

1. An aircraft engine tail nozzle structure, comprising a tail nozzle body (1), characterized in that: The end of the tail nozzle body (1) is fixedly installed with a mounting plate (2), and multiple mounting pins (3) are connected through the edge of the mounting plate (2). Multiple drainage pipes (4) are connected to the side wall of the tail nozzle body (1), and connectors (5) are connected to the ends of the multiple drainage pipes (4). Multiple drainage holes (6) are opened on the side wall of the tail nozzle body (1), and an auxiliary support structure (7) is connected to the outside of the tail nozzle body (1).

2. The tail nozzle structure of an aero-engine according to claim 1, characterized in that: The auxiliary receiving structure (7) includes a connecting sleeve (8), a support frame (9), a first card holder (10), and a second card holder (11). The connecting sleeve (8) is fitted onto the outer surface of the tail nozzle body (1). The support frame (9) is fixed to the outside of the connecting sleeve (8). The first card holder (10) is fixedly installed at the end of the support frame (9). The second card holder (11) is located on the outside of the first card holder (10).

3. The tail nozzle structure of an aero-engine according to claim 2, characterized in that: The outer surface of the second card holder (11) is fixedly connected to a connecting post (12) that is inserted into the first card holder (10). A return spring (13) is connected between the connecting post (12) and the first card holder (10). The first card holder (10) has a fixed slot for accommodating the connecting post (12) and the return spring (13).

4. The tail nozzle structure of an aero-engine according to claim 3, characterized in that: The second card holder (11) is movably connected to the first card holder (10) via a connecting post (12) and a return spring (13), and a card slot is formed between the first card holder (10) and the second card holder (11).

5. The tail nozzle structure of an aero-engine according to claim 1, characterized in that: The inner wall of the tail nozzle body (1) is fixedly connected to a connecting ring (14), and a flow guide (15) is provided on the outer side of the connecting ring (14). The flow guide (15) and the connecting ring (14) are in the same axial direction.

6. The tail nozzle structure of an aero-engine according to claim 5, characterized in that: The outer surface of the flow guide (15) is fixedly connected with a snap-fit ​​post (16), and the inside of the connecting ring (14) is provided with a snap-fit ​​groove (17) that is adapted to the snap-fit ​​post (16). The flow guide (15) is snapped into the snap-fit ​​groove (17) and engaged with the connecting ring (14) through the snap-fit ​​post (16).

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