Aircraft engine casing sealing test device

Abstract

The utility model relates to the technical field of aero-engine casing sealing test, and discloses an aero-engine casing sealing test device, which comprises a base, an air tightness detector is fixedly mounted on the left side of the upper surface of the base, a connecting pipe is arranged on one side of the air tightness detector, and a first fixing box is fixedly connected to the middle of the upper surface of the base; the aero-engine case can be clamped and fixed through the clamping assembly, shaking of the aero-engine case during testing is avoided, the second fixing box is driven by the electric telescopic rod to be attached to the first fixing box so as to guarantee the airtightness during detection, the aero-engine case can be inflated through the airtightness detector, and the airtightness of the aero-engine case is guaranteed. And if air leakage occurs in the aero-engine case, air is inflated into the air bag, so that the air bag is not bulged and is not reversed or regular, meanwhile, the overall structure is relatively simple, the device is very convenient to use, and the practicability of the device is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine casing sealing test, in particular to an aero-engine casing sealing test device. BACKGROUND

[0002] As the core power device of an airplane, the performance and reliability of an aero-engine directly determine the flight safety, operation efficiency and mission execution capability of the airplane. The casing, as a key structural component of the aero-engine, undertakes the important task of containing, supporting and protecting the high-speed rotating components (such as rotors, blades, etc.) inside the aero-engine, and is also the basic guarantee for maintaining the integrity of the airflow channel inside the aero-engine, ensuring normal work of the gas and realizing various control functions. Traditional tests mostly rely on manual operation, and a large amount of manpower is required for pressure regulation, data recording and result judgment. Manual operation is not only inefficient, but also prone to inaccurate and unstable test results due to differences in technical level of operators and fatigue. CONTENT OF THE UTILITY MODEL

[0003] In order to solve the problems raised in the background art, the present application provides an aero-engine casing sealing test device.

[0004] The aero-engine casing sealing test device provided by the present application adopts the following technical scheme:

[0005] The aero-engine casing sealing test device comprises a base, a gas tightness detector is fixedly installed on the left side of the upper surface of the base, a connecting pipe is arranged on one side of the gas tightness detector, a first fixed box is fixedly connected to the middle of the upper surface of the base, an electric telescopic rod is fixedly installed on the right side of the upper surface of the base, the output end of the electric telescopic rod is fixedly connected to a second fixed box located at the top of the base, the opposite sides of the first fixed box and the second fixed box are both provided in an open manner, a fixing assembly for fixing the aero-engine casing is arranged in the first fixed box, and an air bag is fixedly connected to the side wall of the second fixed box.

[0006] Preferably, the fixing assembly comprises a clamping plate and a screw rod, the screw rod penetrates through the side wall of the first fixed box and is threadedly connected thereto, one end of the screw rod located in the first fixed box is rotatably connected to the side wall of the clamping plate, and the other end of the screw rod extending out of the first fixed box is fixedly connected to a knob.

[0007] Preferably, limit rods are symmetrically and slidingly installed through the side wall of the first fixed box, and one end of each limit rod is fixedly connected to the side wall of the clamping plate.

[0008] Preferably, a groove is provided on the right side of the upper surface of the base, and a slider is slidably installed inside the groove. The upper surface of the slider is fixedly connected to the lower surface of the second fixing box.

[0009] Preferably, support legs are provided at all four corners of the lower surface of the base.

[0010] In summary, this application includes the following beneficial technical effects:

[0011] Compared to existing technologies, this device features a clamping assembly that can securely hold the aircraft engine casing in place, preventing it from shaking during testing. An electric telescopic rod brings the second mounting box into contact with the first, ensuring a tight seal during testing. An airtightness tester can then pump air into the aircraft engine casing to check its seal. If a leak is detected, air will be pumped into the airbag to inflate it; otherwise, no leak will occur. The overall structure is also relatively simple and easy to use, enhancing the device's practicality. Attached Figure Description

[0012] Fig. 1 This is a three-dimensional structural diagram of an embodiment of the application;

[0013] Fig. 2 This is a schematic diagram of the slider structure in an embodiment of the application;

[0014] Fig. 3 This is a schematic diagram of the structure of the fixed component in the embodiment of the application.

[0015] Explanation of reference numerals in the attached drawings: 1. Base; 2. Air tightness tester; 3. Connecting pipe; 4. First fixing box; 5. Clamping plate; 6. Airbag; 7. Electric telescopic rod; 8. Support leg; 9. Second fixing box; 10. Slider; 11. Slide groove; 12. Screw; 13. Knob; 14. Limiting rod. Detailed Implementation

[0016] The following is in conjunction with the appendix Figs. 1-3 This application will be described in further detail.

[0017] This application discloses an aircraft engine casing sealing test apparatus. (Refer to...) Figs. 1-3An aircraft engine casing sealing test device includes a base 1. An airtightness tester 2 is fixedly mounted on the left side of the upper surface of the base 1. A connecting pipe 3 is provided on one side of the airtightness tester 2. A first fixed box 4 is fixedly connected to the middle of the upper surface of the base 1. An electric telescopic rod 7 is fixedly mounted on the right side of the upper surface of the base 1. A second fixed box 9 located at the top of the base 1 is fixedly connected to the output end of the electric telescopic rod 7. A slide groove 11 is formed on the right side of the upper surface of the base 1. A slider 10 is slidably mounted inside the slide groove 11. The upper surface of the slider 10 is fixedly connected to the lower surface of the second fixed box 9. The first fixed box 4 and the second fixed box 9 are opposite to each other. One side of each is open. The first fixed box 4 is equipped with a fixing assembly for fixing the aircraft engine casing. The fixing assembly includes a clamping plate 5 and a screw 12. The screw 12 passes through the side wall of the first fixed box 4 and is threaded to it. One end of the screw 12 inside the first fixed box 4 is rotatably connected to the side wall of the clamping plate 5. A knob 13 is fixedly connected to the end of the screw 12 extending to the outside of the first fixed box 4. Limiting rods 14 are symmetrically and slidably installed through the side wall of the first fixed box 4. One end of the limiting rod 14 is fixedly connected to the side wall of the clamping plate 5. An airbag 6 is fixedly connected to the side wall of the second fixed box 9.

[0018] The implementation principle of the aircraft engine casing sealing test device in this application embodiment is as follows: All electrical components in this application are externally connected to a power supply and control switch during use. In use, the aircraft engine casing to be tested is placed inside the first fixed box 4. Rotating the knob 13 rotates the screw 12, and under the limit of the limiting rod 14, the clamping plate 5 can move, clamping and fixing the aircraft engine casing. Then, the connecting pipe 3 on the airtightness tester 2 is connected to the aircraft engine casing. Activating the electric telescopic rod 7 moves the second fixed box 9 towards the first fixed box 4. When the first fixed box 4 and the second fixed box 9 are tightly fitted together, the operation of the electric telescopic rod 7 is paused. Furthermore, when the second fixed box 9 moves, it drives the slider 10 to slide within the slide groove 11. The airtightness tester 2 can be connected via the connecting pipe... 3. Air is pumped into the aircraft engine casing to test its sealing performance. The detected data is directly fed back to the display screen on the airtightness tester 2 for easy viewing by the staff. If the aircraft engine casing leaks, air will be pumped into the airbag 6 to inflate it; otherwise, it will not. During this process, the aircraft engine casing is clamped and fixed by the clamping assembly to prevent it from shaking during the test. The electric telescopic rod 7 drives the second fixed box 9 to fit against the first fixed box 4 to ensure the sealing performance during the test. Air can be pumped into the aircraft engine casing through the airtightness tester 2 to test its sealing performance. If the aircraft engine casing leaks, air will be pumped into the airbag 6 to inflate it; otherwise, it will not. At the same time, the overall structure is relatively simple and easy to use, which improves the practicality of the device.

[0019] Reference Fig. 1 Support legs 8 are provided at the four corners of the lower surface of the base 1, which facilitates the support of the entire device.

[0020] Finally, the following points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection", and "linkage" should be interpreted broadly, and can be mechanical or electrical connections, or internal connections between two components, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may change.

[0021] Secondly: The accompanying drawings of the embodiments disclosed in this utility model only involve the structures involved in the embodiments disclosed in this utility model. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this utility model can be combined with each other.

[0022] Finally: The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

[0023] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. An aircraft engine casing sealing test device, comprising a base (1), characterized in that: An airtightness tester (2) is fixedly installed on the left side of the upper surface of the base (1). A connecting pipe (3) is provided on one side of the airtightness tester (2). A first fixed box (4) is fixedly connected to the middle of the upper surface of the base (1). An electric telescopic rod (7) is fixedly installed on the right side of the upper surface of the base (1). The output end of the electric telescopic rod (7) is fixedly connected to a second fixed box (9) located at the top of the base (1). The opposite sides of the first fixed box (4) and the second fixed box (9) are both open. The interior of the first fixed box (4) is provided with a fixing component for fixing the aircraft engine casing. An airbag (6) is fixedly connected to the side wall of the second fixed box (9).

2. The aircraft engine casing sealing test device according to claim 1, characterized in that: The fixing assembly includes a clamping plate (5) and a screw (12). The screw (12) passes through the side wall of the first fixing box (4) and is threaded to it. One end of the screw (12) inside the first fixing box (4) is rotatably connected to the side wall of the clamping plate (5). A knob (13) is fixedly connected to one end of the screw (12) extending to the outside of the first fixing box (4).

3. The aircraft engine casing sealing test device according to claim 2, characterized in that: Limiting rods (14) are symmetrically and slidably installed through the side wall of the first fixed box (4), and one end of the limiting rods (14) is fixedly connected to the side wall of the clamping plate (5).

4. The aircraft engine casing sealing test device according to claim 1, characterized in that: A groove (11) is provided on the right side of the upper surface of the base (1), and a slider (10) is slidably installed inside the groove (11). The upper surface of the slider (10) is fixedly connected to the lower surface of the second fixed box (9).

5. The aircraft engine casing sealing test device according to claim 1, characterized in that: The base (1) has support legs (8) at all four corners of its lower surface.

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