Civil aircraft generator stator shell part airtightness tool

Abstract

The utility model relates to the technical field of aircraft generator assembly detection devices, and specifically discloses a civil aircraft generator stator housing part air tightness tool comprising a test main body which is hollow inside; the test connector is detachably arranged on the test main body, and the interior of the test connector is hollow and is communicated with the interior of the test main body; wherein the copper binding post is arranged in the test connector; the first sealing ring sleeves the test connector and is located between the test connector and the test main body; the second sealing ring is sleeved on the copper binding post and is positioned between the test joint and the copper binding post; the first limiting component is used for limiting radial movement of the copper binding post; the second limiting component is used for limiting the axial movement of the copper binding post; the positive pressure assembly is used for providing positive pressure gas into the test main body; detection is carried out before the copper binding posts are integrally installed on the generator, part of the copper binding posts which do not meet the sealing requirement are eliminated in advance, and the overall assembly efficiency of the generator is improved.

Description

Technical Field

[0001] This utility model relates to the technical field of aircraft generator assembly and testing devices, and in particular to a tooling for the airtightness of stator housing components of civil aircraft generators. Background Technology

[0002] Modern civil aircraft power systems mainly consist of a main generator, an APU generator (also known as an auxiliary generator), batteries, and an emergency generator. The generator is typically a three-stage electrically excited synchronous generator. When the generator rotor cuts magnetic lines of force, it generates a three-phase alternating current in the generator stator coils. This current is led out through copper terminals on the casing. Simultaneously, the generator's internal casing operates at a relatively high temperature. To effectively mitigate this, the casing is cooled using aviation lubricating oil. Therefore, the copper terminals on the casing must be properly sealed to prevent lubricating oil from leaking outside the casing.

[0003] The sealing performance of the copper terminals needs to be tested. In the existing testing process, after the generator assembly is completed, the workers place the entire generator in a water tank, completely immersing it in water. Then, they use a pneumatic device to introduce 25 Psi of air pressure into the generator and observe whether there are air bubbles in the water tank, thus verifying the sealing performance of the copper terminals.

[0004] However, if the sealing performance of the copper terminals is not tested after the generator is fully assembled, and the sealing performance of the copper terminals does not meet the design requirements, the entire generator needs to be disassembled again and the copper terminals need to be reworked, which reduces the overall assembly efficiency of the generator. Utility Model Content

[0005] In view of the above problems, this utility model provides an airtight tooling for the stator housing components of a civil aircraft generator, the purpose of which is to improve the overall assembly efficiency of the generator.

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

[0007] A tooling for airtightness testing of a civil aircraft generator stator housing component is provided, comprising: a test body, which is hollow inside; a test connector, which is detachably mounted on the test body and is also hollow inside, communicating with the interior of the test body; wherein a copper terminal is placed inside the test connector; a first sealing ring, which is fitted onto the test connector and located between the test connector and the test body; a second sealing ring, which is fitted onto the copper terminal and located between the test connector and the copper terminal; a first limiting component for limiting radial movement of the copper terminal; a second limiting component for limiting axial movement of the copper terminal; and a positive pressure assembly for providing positive pressure gas into the test body.

[0008] Furthermore, several test holes are provided on the test body for installing test connectors.

[0009] Furthermore, both ends of the test hole are chamfered with rounded corners.

[0010] Furthermore, the test body is made of aluminum alloy.

[0011] Furthermore, the tooling also includes: several threaded countersunk holes on the test body; several first mounting through holes on the second limiting component; and several locking screws that can pass through the first mounting through holes and be threadedly connected to the threaded countersunk holes.

[0012] Furthermore, the tooling also includes: several second mounting through holes through which locking screws pass, the second mounting through holes being opened on the first limiting component, and the first limiting component being installed between the second limiting component and the test body.

[0013] Furthermore, the tooling also includes several limiting grooves formed on the first limiting component for the copper terminals to pass through.

[0014] Furthermore, the positive pressure component includes: a threaded through hole, a valve, an air supply pipe, and an air pump; the threaded through hole is formed on the test body and connects to the interior of the test body, the valve is set on the threaded through hole, and the two ends of the air supply pipe are respectively connected to the outlet of the valve and the air pump.

[0015] The beneficial effects of this utility model are as follows: by using this utility model, it is possible to simulate the actual installation of copper terminals on the generator housing of an aircraft, and to test the sealing performance of the copper terminals before they are fully assembled into the generator. This allows for the early elimination of some copper terminals that do not meet the sealing requirements, thereby improving the overall assembly efficiency of the generator. Attached Figure Description

[0016] Figure 1 This is an exploded view of the overall structure of the tooling provided in the embodiments of this application.

[0017] Among them, 1. Test body; 11. Test hole; 12. Rounded corner; 13. Threaded countersunk hole; 14. Threaded through hole; 2. Test connector; 21. First sealing ring; 22. Second sealing ring; 31. First limiting component; 32. Second limiting component; 33. First mounting through hole; 34. Locking screw; 35. Second mounting through hole; 36. Limiting groove; 4. Copper terminal block. Detailed Implementation

[0018] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0019] Reference Figure 1As shown in the embodiment of this application, an airtightness tooling for a stator housing component of a civil aircraft generator is disclosed, comprising: a test body 1, which is hollow inside; a test connector 2, which is detachably disposed on the test body 1 and is also hollow inside, communicating with the interior of the test body 1; wherein, a copper terminal 4 is placed inside the test connector 2; a first sealing ring 21 is sleeved on the test connector 2 and located between the test connector 2 and the test body 1; a second sealing ring 22 is sleeved on the copper terminal 4 and located between the test connector 2 and the copper terminal 4; a first limiting component 31 for limiting the radial movement of the copper terminal 4; a second limiting component 32 for limiting the axial movement of the copper terminal 4; and a positive pressure component for providing positive pressure gas into the test body 1.

[0020] In practical use, this fixture is placed in a water tank, and positive pressure gas is supplied to the test body 1 through the positive pressure component. By observing whether any bubbles emerge from the water tank, the sealing performance of the copper terminal 4 can be tested to see if it meets the design requirements.

[0021] By using this invention, the actual installation of the copper terminal 4 on the generator housing of an aircraft can be simulated. The sealing performance of the copper terminal 4 can be tested before it is fully installed on the generator, which can eliminate some copper terminals 4 that do not meet the sealing requirements in advance and improve the overall assembly efficiency of the generator.

[0022] In this embodiment, both the first sealing ring 21 and the second sealing ring 22 are made of fluorocarbon rubber that is resistant to high temperature and corrosion, and both the first sealing ring 21 and the second sealing ring 22 are O-rings. Of course, for different types of grooves on different types of copper terminals 4, different sealing rings should be flexibly selected in order to simulate the real use scenario as much as possible during the testing process.

[0023] Specifically, the test body 1 has several test holes 11 for installing test connectors 2, which can simultaneously perform sealing tests on multiple copper terminals 4, thereby improving testing efficiency.

[0024] Specifically, both ends of the test hole 11 are chamfered with rounded corners 12, which can prevent sharp corners from scratching the first sealing ring 21 and also provide installation guidance for the test connector 2.

[0025] In this embodiment, the test body 1 is made of aluminum alloy, specifically the same aluminum alloy material as the engine housing, to further simulate the actual installation situation.

[0026] Specifically, the fixture also includes: several threaded countersunk holes 13, which are formed on the test body 1; several first mounting through holes 33, which are formed on the second limiting component 32; several locking screws 34, which can pass through the first mounting through holes 33 and are threadedly connected to the threaded countersunk holes 13; the second limiting component 32 is pressed onto the test body 1 by the nuts of the locking screws 34, which restricts the movement of the copper terminal 4 in the axial direction and prevents the copper terminal 4 from flying out.

[0027] Specifically, the tooling also includes: several second mounting through holes 35 through which locking screws 34 pass, the second mounting through holes 35 being opened on the first limiting component 31, the first limiting component 31 being installed between the second limiting component 32 and the test body 1; the locking bolts can simultaneously lock the first limiting component 31 and the second component.

[0028] In this embodiment, the tooling also includes: several limiting grooves 36, which are formed on the first limiting component 31 for the copper terminal 4 to pass through. The limiting grooves 36 restrict the copper terminal 4 downwards and limit its movement in the radial direction, preventing the copper terminal 4 from flying out.

[0029] In this embodiment, the positive pressure component includes: a threaded through hole 14, a valve, an air supply pipe, and an air pump; the threaded through hole 14 is formed on the test body 1 and communicates with the interior of the test body 1, the valve is set on the threaded through hole 14, and the two ends of the air supply pipe are respectively connected to the outlet of the valve and the air pump.

[0030] Those skilled in the art will understand that although preferred embodiments of the present invention have been described, those skilled in the art, once they learn the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of the present invention. Clearly, those skilled in the art can make various alterations and modifications to the present invention without departing from its spirit and scope. Thus, if these modifications and modifications of the present invention fall within the scope of the machine equivalents of the claims of the present invention, the present invention also intends to include these modifications and modifications.

Claims

1. A tooling for ensuring the airtightness of a stator housing component of a civil aircraft generator, characterized in that, include: Test body (1), hollow inside; The test connector (2) is detachably mounted on the test body (1), and the interior of the test connector (2) is hollow and connected to the interior of the test body (1); wherein, the copper terminal (4) is placed inside the test connector (2); The first sealing ring (21) is fitted onto the test connector (2) and is located between the test connector (2) and the test body (1); The second sealing ring (22) is fitted onto the copper terminal (4) and is located between the test connector (2) and the copper terminal (4); The first limiting component (31) is used to limit the radial movement of the copper terminal (4); The second limiting component (32) is used to limit the axial movement of the copper terminal (4); Positive pressure assembly for supplying positive pressure gas into the test body (1).

2. The airtightness tooling for the stator housing components of a civil aircraft generator according to claim 1, characterized in that, Several test holes (11) are provided on the test body (1) for the test connector (2) to be installed.

3. The airtightness tooling for the stator housing components of a civil aircraft generator according to claim 2, characterized in that, Both ends of the test hole (11) are chamfered with rounded corners (12).

4. The airtightness tooling for the stator housing components of a civil aircraft generator according to claim 1, characterized in that, The test body (1) is made of aluminum alloy.

5. The airtightness tooling for the stator housing components of a civil aircraft generator according to claim 1, characterized in that, Also includes: Several countersunk holes (13) are formed on the test body (1); Several first mounting through holes (33) are formed on the second limiting component (32); Several locking screws (34) can pass through the first mounting through hole (33) and be threadedly connected to the threaded countersunk hole (13).

6. The airtightness tooling for the stator housing components of a civil aircraft generator according to claim 5, characterized in that, Also includes: Several second mounting through holes (35) through which locking screws (34) pass, the second mounting through holes (35) are opened on the first limiting member (31), the first limiting member (31) is installed between the second limiting member (32) and the test body (1).

7. The airtightness tooling for the stator housing components of a civil aircraft generator according to claim 6, characterized in that, Also includes: Several limiting grooves (36) are provided on the first limiting component (31) for the copper terminal (4) to pass through.

8. The airtightness tooling for the stator housing components of a civil aircraft generator according to claim 1, characterized in that, The positive pressure assembly includes: a threaded through hole (14), a valve, an air supply pipe and an air pump; the threaded through hole (14) is opened on the test body (1) and connects to the interior of the test body (1), the valve is set on the threaded through hole (14), and the two ends of the air supply pipe are connected to the outlet of the valve and the air pump respectively.

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