A special seal test device for aircraft electric centrifugal pump

Abstract

The present invention discloses a special sealing test device for an aircraft electric centrifugal pump, which belongs to the field of aviation manufacturing technology. The sealing test device of the present invention places the pump body into a sealed container, does not block the outlet, but checks the sealing of the joint by reversely pressurizing the inside of the pump body through the outlet. The sealing test device is designed as an upper cover in the form of a movable mounting plate, and the lower surface of the test box mounting cover is first mounted with the flange of the upper end cover of the bell jar, and then the test box mounting cover is mounted with the sealing test box, which not only meets the installation test requirements of the aircraft electric centrifugal pump, but can also be extended to the sealing test of other similar products by replacing the test box mounting cover; and the design of the sealing bolt assembly solves the problem that ordinary bolt connections cannot ensure the sealing at the screw.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation manufacturing and relates to a special sealing test device for an aircraft electric centrifugal pump. Background Art

[0002] According to the technical requirements for aircraft overhaul, after the electric centrifugal pump is repaired, it needs to be installed in a bell-shaped cover and then inspected for sealing. The document stipulates: Pass 0.069MPa air pressure into the product, maintain for 3 minutes, and check the air tightness of each joint of the electric centrifugal pump. The conventional sealing test requires blocking the outlet of the product, leaving only one inlet connected to the test bench for pressurization. This kind of sealing test method is suitable for sealing inspection of products with regular structures and easy inlets and outlets to be blocked. It is not suitable for products with complex shapes, irregular inlets and outlets, and difficult to block. The electric centrifugal pump involved in the present invention has an irregular shape, and there are oil suction ports, oil outlets, oil discharge ports, etc. on the pump body, and a filter screen is also installed on the oil suction port. The commonly used plugs, plug caps or sealing rubber plugs cannot block the oil suction port and oil outlet of the pump body. Therefore, it is necessary to design a special sealing test device to check the sealing of the joints of the electric centrifugal pump without blocking the pressure relief point of the pump body. At the same time, the bell cover is a cast aluminum part. Except for the upper end flange installed with the aircraft, which has been machined and can be used as the connection surface with the sealing test device, the other surfaces cannot be used as installation surfaces to connect with the sealing test device to ensure sealing. When designing special tooling, it is necessary to verify the installation sealing method of the test pump. Summary of the invention

[0003] The present invention comprehensively considers that the installation joints of various components of the electric centrifugal pump are all on the upper end cover, and the installation joints of the electric centrifugal pump and the bell jar are also on the upper end cover. In combination with the volume size and test pressure of the electric centrifugal pump, a sealed test box is designed, and the test pump is installed in the sealed test box. Without blocking the pressure relief points of the test pump, air pressure is added to the sealed test box, so that the air pressure enters the pump body in the reverse direction through the pressure relief points to check the sealing of the joints of the upper end cover; at the same time, a detachable test box installation cover is designed, and the lower surface of the test box installation cover is first connected to the upper end cover flange machined by the bell jar, the test pump is fixed, and then installed with the sealed test box flange, and finally air pressure is added to the test box through the air inlet nozzle on the test box installation cover.

[0004] The technical solution of the present invention is:

[0005] A special sealing test device for an aircraft electric centrifugal pump comprises a sealing test box 1, a test box installation cover 2, a sealing bolt assembly 3, a fixing bolt 4, an air inlet nozzle 5, a sealing rubber ring and a caster 9.

[0006] The sealing test box 1 is a cylindrical structure and is the main body of the device. Its function is to place the tested pump during the test and to form a sealed pressure space when pressurized, and to reversely pressurize each oil outlet end of the tested pump.

[0007] The test box installation cover 2 is not only a mounting base for the electric centrifugal pump, but also an upper cover plate of the sealed test box. The electric centrifugal pump is connected to the lower surface of the test box installation cover 2 through the flange on the upper end face of the bell jar. A sealing gasket A8 is installed between the two and fixedly connected with a sealing bolt assembly 3. The sealing gasket A8 and the sealing bolt assembly 3 ensure the sealing of the connection. The outer edge of the test box installation cover 2 is connected to the flange of the sealed test box 1 through a fixing bolt 4. A sealing rubber ring B7 is installed in the sealing groove of the test box installation cover 2 to ensure the sealing of the connection between the test box installation cover and the sealed test box. The test box installation cover 2 is provided with an air inlet nozzle 5, which is connected to the air source to pressurize the test box; a sealing rubber ring A6 is used between the air inlet nozzle 5 and the test box installation cover 2 to ensure the sealing.

[0008] The casters 9 are installed at the bottom of the sealing test box 1 to facilitate the movement of the sealing test device.

[0009] Furthermore, the structural shape and size of the test box installation cover 2 are completely designed according to the shape and installation size of the upper end surface of the bell-shaped cover of the electric centrifugal pump.

[0010] Furthermore, the mounting holes of the flange on the upper end face of the bell-shaped cover of the electric centrifugal pump and the mounting holes of the test box mounting cover are both through holes. The sealing of the joints cannot be guaranteed after being connected with ordinary bolts. Therefore, a sealing bolt assembly 3 is used, including a sealing bolt 11, a rubber pad support 12 and a sealing rubber pad B13; the sealing rubber pad B13 is supported by the rubber pad support 12 and tightened on the test box mounting cover to ensure the sealing of the bolted joint.

[0011] Beneficial effects of the present invention:

[0012] 1) In general, the sealing test is performed by blocking the outlet of the product and applying pressure to the inside of the product to check the sealing condition of the joint of the product. The sealing test device of the present invention places the pump body in a sealed container, does not block the outlet, but applies pressure to the inside of the pump body in the reverse direction through the outlet to check the sealing condition of the joint;

[0013] 2) The sealing test device is designed as an upper cover in the form of a movable mounting plate. The lower surface of the test box installation cover is first installed with the flange of the upper end cover of the bell jar, and then the test box installation cover is installed with the sealing test box. This not only meets the installation test requirements of the aircraft electric centrifugal pump, but can also be extended to the sealing test of other similar products by replacing the test box installation cover;

[0014] 3) The design of the sealing bolt assembly solves the problem that ordinary bolt connections cannot ensure the sealing of the screw;

[0015] 4) The caster installation facilitates the use of the sealing test device. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of the present invention.

[0017] Figure 2 This is a schematic diagram of the installation test of an electric centrifugal pump.

[0018] Figure 3 Schematic diagram of a sealed test box, where (a) is the main view and (b) is the side view.

[0019] Figure 4 This is a schematic diagram of installing the cover of the test chamber.

[0020] Figure 5 Schematic diagram of the sealing bolt assembly.

[0021] In the figure: 1 sealing test box; 2 test box installation cover; 3 sealing bolt assembly; 4 fixing bolt; 5 air inlet nozzle; 6 sealing rubber ring A; 7 sealing rubber ring B; 8 sealing rubber pad A; 9 casters; 10 electric centrifugal pump; 11 sealing bolt; 12 rubber pad support; 13 sealing rubber pad B. DETAILED DESCRIPTION

[0022] The specific implementation of the present invention is further explained below in conjunction with the examples and drawings, but is not intended to limit the present invention.

[0023] like Figure 1 As shown, a special sealing test device for an aircraft electric centrifugal pump includes a sealing test box 1, a test box installation cover 2, a sealing bolt assembly 3, a fixing bolt 4, an air intake nozzle 5, a sealing rubber ring and a caster 9.

[0024] like Figure 3 As shown, the sealing test box 1 is a cylindrical structure, and its function is to place the tested pump during the test and form a sealed pressure space when pressurized to reversely pressurize each oil outlet end of the tested pump.

[0025] like Figure 4As shown, the test box installation cover 2 is installed on the flange of the upper end face of the bell-shaped cover of the electric centrifugal pump, and a sealing rubber gasket A8 is installed between the two, and they are fixedly connected by 10 sealing bolt assemblies 3; the sealing bolt assembly 3 includes a sealing bolt 11, a rubber gasket support 12 and a sealing rubber gasket B13; the rubber gasket support 12 is used to support the sealing rubber gasket B13 and tighten it on the test box installation cover to ensure the sealing of the bolt connection. The outer edge of the test box installation cover 2 is connected to the flange of the sealed test box 1 through the fixing bolts 4; a sealing rubber ring B7 is installed in the sealing groove of the test box installation cover 2 to ensure the sealing of the connection between the test box installation cover and the sealed test box. The test box installation cover 2 is provided with an air inlet nozzle 5, which is connected to the air source to pressurize the test box; a sealing rubber ring A6 is used between the air inlet nozzle 5 and the test box installation cover 2 to ensure the sealing.

[0026] Three casters 9 are installed at the bottom of the sealing test box 1 to facilitate the movement of the sealing test device.

Claims

1. A special seal test device for an aircraft electric centrifugal pump, characterized in that: The sealing test device comprises a sealing test box (1), a test box installation cover (2), a sealing bolt assembly (3), an air inlet nozzle (5) and casters (9); The sealing test box (1) is a cylindrical structure, used to place the tested pump during the test, and to form a sealed pressure space when pressurized, and to reversely pressurize each oil outlet end of the tested pump; The test box installation cover (2) can be disassembled and installed on the flange plate on the upper end face of the bell-shaped cover of the electric centrifugal pump, and a sealing rubber gasket A (8) is installed between the two, and the sealing bolt assembly (3) is used to fix the connection; the outer edge of the test box installation cover (2) is connected to the flange plate of the sealing test box (1); the test box installation cover (2) is provided with an air inlet nozzle (5), which is connected to the air source to pressurize the test box; The casters (9) are installed at the bottom of the sealing test box (1) to facilitate the movement of the sealing test device; The structural shape and size of the test box installation cover (2) are designed according to the shape and installation size of the upper end surface of the bell-shaped cover of the electric centrifugal pump; the sealing bolt assembly (3) comprises a sealing bolt (11), a rubber pad support (12) and a sealing rubber pad B (13), and the sealing rubber pad B (13) is supported by the rubber pad support (12) and tightened on the test box installation cover to ensure the sealing of the bolt connection.

2. A special seal test device for an aircraft electric centrifugal pump according to claim 1, characterized in that: A sealing rubber ring B (7) is installed in the sealing groove of the test box installation cover (2) to ensure the sealing of the connection between the test box installation cover and the sealed test box; a sealing rubber ring A (6) is used to ensure the sealing between the air inlet nozzle (5) and the test box installation cover (2).

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