Ignition electric nozzle with cooling structure for aero-engine

Abstract

The invention belongs to the field of ignition electric nozzle structure design, and particularly relates to an ignition electric nozzle with a cooling structure for an aero-engine, which comprises an ignition electric nozzle body, a filler neck and an ignition electric nozzle mounting edge, the sparking plug body is in threaded connection with the sparking plug mounting edge, and the sparking plug mounting edge is fixedly connected with the filler neck; a first cooling channel is arranged in the pipe joint nozzle, a second cooling channel is arranged in the sparking plug mounting edge, and the first cooling channel and the second cooling channel are communicated with each other; engine cooling air enters from the filler neck, passes through the first cooling channel and the second cooling channel and then flows into the outer surface of the sparking plug body. The ignition electric nozzle and the cooling structure are integrally designed, so that the reliability of the temperature resistance of the ignition electric nozzle of the structure to be cooled is ensured, the air tightness meets the requirement when the ignition electric nozzle leaves a factory, the problems of difficulty in debugging, easiness in interference under comprehensive stress such as long-term vibration and the like in an external factory are solved, and good economic benefits and social benefits are achieved.

Description

Technical Field

[0001] This application belongs to the field of ignition nozzle structure design, and specifically relates to an ignition nozzle with cooling structure for aero engines. Background Technology

[0002] Currently, mainstream ignition nozzles do not have a cooling structure. The cooling structure is provided by the engine. The ignition nozzle is assembled with the engine's cooling structure at an external manufacturer. The ignition nozzle is a long cylindrical shape with external threads, and the engine cooling structure is a long cylindrical shape with internal threads. The internal and external threads are connected and the ignition nozzle is cooled by the cooling air from the engine.

[0003] Since both the ignition nozzle and the cooling structure are long cylindrical shapes, the two parts must have high coaxiality requirements and be well assembled to ensure that they do not interfere with each other under the combined stress of long-term engine vibration. Furthermore, after the ignition nozzle and the cooling structure are threaded together, the airtightness of the contact point between the two parts must be tested. If it fails to meet the requirements, repeated disassembly and assembly are necessary, which is inconvenient for external manufacturers to conduct tests.

[0004] Therefore, designing a stable cooling structure for the ignition nozzle is a problem that needs to be solved. Summary of the Invention

[0005] To address the aforementioned issues, this application provides an ignition nozzle with a cooling structure for an aero-engine, thereby resolving the problem of difficulty in installing a cooling structure on the ignition nozzle in the prior art.

[0006] The technical solution of this application is: an ignition nozzle with a cooling structure for an aero-engine, including a nozzle body, a connecting nozzle, and a nozzle mounting edge;

[0007] The electric nozzle body is threadedly connected to the electric nozzle mounting edge, and the electric nozzle mounting edge is fixedly connected to the connecting nozzle.

[0008] The pipe fitting is provided with a first cooling channel, and the electric nozzle mounting edge is provided with a second cooling channel. The first cooling channel and the second cooling channel are connected to each other.

[0009] Engine cooling air enters through the connector nozzle, passes through the first and second cooling channels, and then flows into the outer surface of the electric nozzle body.

[0010] Preferably, the outer surface of the electric nozzle body is provided with a thin-walled shell, and a cavity is provided between the thin-walled shell and the electric nozzle body. A cooling air outlet is provided at the end of the thin-walled shell, and engine cooling air flows into the space between the thin-walled shell and the electric nozzle body and flows out from the cooling air outlet.

[0011] Preferably, an annular connecting sleeve is provided at the position of the electric nozzle mounting edge corresponding to the electric nozzle body. The annular connecting sleeve is threadedly connected to the electric nozzle body, and the coaxiality is 0.05.

[0012] Preferably, a copper washer is provided between the mounting edge of the electric nozzle and the annular connecting sleeve, and the material of the copper washer is T2 copper plate.

[0013] Preferably, the outer diameter of the copper washer (Φ24-0.065-0.195) is clearance-fitted with the outer diameter of the annular connecting sleeve (Φ24+0.045). The inner diameter of the copper washer (Φ20.3+0.13) is transition-fitted with the inner diameter of the cooling structure. The ignition nozzle passes through the copper washer and extends into the cooling structure, and can be tightened using a torque wrench.

[0014] Preferably, the diameter of the first cooling channel is larger than that of the second cooling channel.

[0015] The aircraft engine with a cooling structure ignition nozzle of this application has the following advantages:

[0016] The ignition nozzle and cooling structure were integrated into a design, ensuring the reliability of the temperature resistance of the ignition nozzle in the structure to be cooled. The airtightness met the requirements at the time of delivery. This solved the problems of difficult external debugging and easy interference under the combined stress of long-term vibration, and has good economic and social benefits. Attached Figure Description

[0017] Figure 1 This is a partial cross-sectional schematic diagram of the thin-walled shell of this application;

[0018] Figure 2 This is a schematic diagram of the copper washer structure of this application;

[0019] Figure 3 This is a partial cross-sectional view of the structure of the ignition nozzle in this application.

[0020] 1. Connecting nozzle; 2. Electric nozzle mounting edge; 3. Thin-walled housing; 4. Cooling gas outlet; 5. Circular connecting sleeve; 6. Copper gasket; 7. Ignition electric nozzle. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0022] The first aspect of this application provides an ignition nozzle for an aircraft engine with a cooling structure, such as... Figure 1 Figure 3 shows the electric nozzle body, the connecting nozzle 1, and the electric nozzle mounting edge 2.

[0023] The ignition nozzle 7 is positioned at the "axial positioning point" along the cooling structure. The nozzle body is threadedly connected to the nozzle mounting edge 2, and the nozzle mounting edge 2 is fixedly connected to the connecting nozzle 1. The connecting nozzle 1 and the nozzle mounting edge 2 are made of GH3044 high-temperature alloy, which has excellent high-temperature resistance and three-proof performance compared to stainless steel.

[0024] A first cooling channel is provided inside the pipe fitting, and a second cooling channel is provided inside the electric nozzle mounting edge 2. The first cooling channel and the second cooling channel are connected to each other.

[0025] Engine cooling air enters through connector 1, passes through the first and second cooling channels, and then flows into the outer surface of the electric nozzle body.

[0026] Eliminating the separate cooling structure avoids accumulated assembly errors and improves overall structural rigidity and vibration resistance. Shortening the cooling airflow path improves heat dissipation efficiency and reduces the risk of high-temperature failure. Reducing external piping connection points lowers the probability of leakage, making it suitable for the long-term high-temperature and vibration environment of aero engines.

[0027] Preferably, a thin-walled shell 3 is provided on the outer surface of the electric nozzle body, and a cavity is provided between the thin-walled shell 3 and the electric nozzle body. A cooling air outlet 4 is provided at the end of the thin-walled shell 3. Engine cooling air flows into the space between the thin-walled shell 3 and the electric nozzle body and flows out from the cooling air outlet 4. The cavity between the thin-walled shell 3 and the electric nozzle body forms a surrounding air film, which uniformly cools the key parts of the electric nozzle. The outlet guides the airflow to be discharged in a directional manner, avoiding heat accumulation in local areas and improving temperature resistance reliability.

[0028] Preferably, an annular connecting sleeve 5 is provided at the position of the nozzle mounting edge 2 corresponding to the nozzle body. The annular connecting sleeve 5 is threadedly connected to the nozzle body, and the coaxiality is 0.05. Strict control of coaxiality ensures the coaxial relationship between the nozzle and the cooling channel, avoiding vibration wear and reduced airtightness.

[0029] Preferably, a copper washer 6 is provided between the mounting edge 2 of the electric nozzle and the annular connecting sleeve 5. The material of the copper washer 6 is T2 copper plate. T2 copper undergoes plastic deformation under extrusion to form a metal sealing surface, which is resistant to high temperature and aging. The upper and lower surfaces of the copper washer 6 have parallelism requirements, and the inner and outer holes have circular runout requirements to ensure a good fit between the sealing ring and the cooling structure.

[0030] Preferably, the outer diameter of the copper washer 6 (Φ24-0.065-0.195) is clearance-fitted with the outer diameter of the annular connecting sleeve 5 (Φ24+0.045). The inner diameter of the copper washer 6 (Φ20.3+0.13) is transition-fitted with the inner diameter of the cooling structure. The ignition nozzle 7 passes through the copper washer 6 and extends into the cooling structure, and can be tightened using a torque wrench. The clearance fit on the outer diameter facilitates installation and positioning, while the transition fit on the inner diameter ensures uniform contact of the sealing surface. Tightening with a torque wrench allows for precise control of the compression of the copper washer 6, ensuring consistent sealing and reliable reusability.

[0031] Preferably, the diameter of the first cooling channel is larger than that of the second cooling channel. A larger inlet channel diameter reduces intake resistance and increases flow rate; a smaller outlet channel diameter increases flow velocity and enhances end-stage cooling. This balances smooth intake with end-stage impact cooling, preventing uneven temperature caused by cooling air stagnation at the far end.

[0032] In summary, this application has the following advantages:

[0033] The ignition nozzle and cooling structure were integrated into a design, ensuring the reliability of the temperature resistance of the ignition nozzle in the structure to be cooled. The airtightness met the requirements at the time of delivery. This solved the problems of difficult external debugging and easy interference under the combined stress of long-term vibration, and has good economic and social benefits.

[0034] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An ignition nozzle with a cooling structure for an aero-engine, characterized in that, It includes the electric nozzle body, the connecting nozzle (1), and the electric nozzle mounting edge (2); The electric nozzle body is threadedly connected to the electric nozzle mounting edge (2), and the electric nozzle mounting edge (2) is fixedly connected to the connecting nozzle (1); The pipe fitting is provided with a first cooling channel, and the electric nozzle mounting edge (2) is provided with a second cooling channel. The first cooling channel and the second cooling channel are connected to each other. Engine cooling air enters through the connector (1), passes through the first and second cooling channels, and then flows into the outer surface of the electric nozzle body.

2. The ignition nozzle with cooling structure for an aero-engine as described in claim 1, characterized in that, The outer surface of the electric nozzle body is provided with a thin-walled shell (3), and a cavity is provided between the thin-walled shell (3) and the electric nozzle body. A cooling gas outlet (4) is provided at the end of the thin-walled shell (3). Engine cooling gas flows into the space between the thin-walled shell (3) and the electric nozzle body and flows out from the cooling gas outlet (4).

3. The ignition nozzle with cooling structure for an aero-engine as described in claim 1, characterized in that, The electric nozzle mounting edge (2) is provided with an annular connecting sleeve (5) at the position corresponding to the electric nozzle body. The annular connecting sleeve (5) is threadedly connected to the electric nozzle body and the coaxiality is 0.

05.

4. The ignition nozzle with cooling structure for an aero-engine as described in claim 3, characterized in that, A copper washer (6) is provided between the mounting edge (2) of the electric nozzle and the annular connecting sleeve (5), and the material of the copper washer (6) is T2 copper plate.

5. The ignition nozzle with cooling structure for an aero-engine as described in claim 4, characterized in that, The outer diameter of the copper washer (6) Φ24-0.065-0.195 is clearance-fitted with the outer diameter of the annular connecting sleeve (5) Φ24+0.045 0. The inner diameter of the copper washer (6) Φ20.3+0.13 0. is transition-fitted with the inner diameter of the cooling structure. The ignition nozzle (7) passes through the copper washer (6) and extends into the cooling structure, and can be tightened by a torque wrench.

6. The ignition nozzle with cooling structure for an aero-engine as described in claim 1, characterized in that, The diameter of the first cooling channel is larger than that of the second cooling channel.

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