Testing device for testing service life of aviation combined sealing ring

Abstract

The utility model belongs to the field of aviation tests, and relates to a test device for testing the service life of an aviation combined sealing ring, which comprises an upper end cover and a lower end cover, and the upper end cover is arranged above the lower end cover; the upper end cover comprises a connecting plate, a connecting column and a connecting piece, the first face of the connecting plate is connected with the side face of the lower end cover, the first end of the connecting column is connected with the middle of the second face of the connecting plate, and the connecting piece is arranged at the second end of the connecting column. Protruding structures are arranged on the side walls of the connecting pieces, and inclined faces are arranged at the ends, away from the connecting columns, of the connecting pieces. According to the utility model, through the cooperation of the upper end cover and the lower end cover, the preparation time required by testing is shortened under the condition that the testing condition required by the sealing ring is met, and the testing efficiency is further improved.

Description

Technical Field

[0001] The utility model belongs to the field of aviation tests, and particularly relates to a test device for testing the service life of an aviation combined sealing ring. Background Art

[0002] The sealing ring plays a crucial role in the aviation system, such as preventing liquid and gas leakage and maintaining system stability. Especially in the hydraulic, fuel, engine, and environmental control systems of an aircraft, the sealing performance of these parts is directly related to the flight safety of the aircraft.

[0003] Since aircraft need to operate in complex environments such as extreme high pressure, high temperature, low temperature, and strong vibration for a long time, the materials and designs of the sealing rings must have extremely high durability and stability.

[0004] Through the test device, engineers can simulate these extreme working conditions in the laboratory environment, conduct fatigue tests on the sealing rings in terms of high pressure, temperature, vibration, etc., collect data in real time, and analyze the performance changes of the sealing rings, so as to evaluate their service life and reliability during long-term use. This kind of test can not only predict the performance of the sealing rings under actual flight conditions, help optimize the design, and improve their durability, but also ensure that the key systems of the aircraft will not malfunction due to the failure of the sealing rings during long-term operation, greatly improving flight safety and the reliability of the equipment.

[0005] However, the current test devices are relatively complex and the operation process is too cumbersome, increasing the preparation time required for the test. Content of the Utility Model

[0006] Aiming at the deficiencies of the prior art, the utility model provides a test device for testing the service life of an aviation combined sealing ring. By setting an upper end cover and a lower end cover, test conditions are provided for the test of the sealing ring, realizing the test of the sealing ring to be tested. The overall structure is simple, the operation is convenient, and the overall test time is shortened.

[0007] To achieve the above object, the utility model discloses the following technical solutions:

[0008] A test device for testing the service life of an aviation combined sealing ring, which includes an upper end cover and a lower end cover, and the upper end cover is arranged above the lower end cover;

[0009] The upper end cover includes a connecting plate, a connecting column, and a connecting piece. The first surface of the connecting plate is connected to the side surface of the lower end cover, the first end of the connecting column is connected to the middle of the second surface of the connecting plate, and the connecting piece is arranged at the second end of the connecting column;

[0010] A protruding structure is arranged on the side wall of the connecting piece, and an inclined surface is arranged at one end of the connecting piece far away from the connecting column;

[0011] A plurality of annular grooves are formed on the inner side wall of the connecting plate;

[0012] A cylindrical protrusion that is connected in cooperation with the inside of the connecting plate is provided at the central position of the lower end cover;

[0013] The sealing ring to be tested is sleeved on the cylindrical protrusion.

[0014] Preferably, the upper end cover is connected to the lower end cover by bolts.

[0015] Preferably, a plurality of first threaded holes are formed on the connecting plate, and a plurality of second threaded holes that cooperate with the first threaded holes are formed on the lower end cover.

[0016] Preferably, the connecting plate, the connecting column and the connecting member are all of an integral hollow structure.

[0017] Preferably, it further includes an air source, a pressure gauge and a high-temperature aging box. After the upper end cover and the lower end cover are connected, they are installed inside the high-temperature aging box. The air source is sleeved and connected to the connecting member of the upper end cover through an air source pipeline, and the pressure gauge is arranged on the air source pipeline.

[0018] Preferably, an air source switch is further arranged on the air source pipeline.

[0019] Preferably, the air source pipeline is in a communicating state with the inside of the upper end cover.

[0020] Optionally, a chamfer is arranged in the annular groove.

[0021] Compared with the prior art, the present utility model has the following beneficial effects:

[0022] The present utility model realizes the test of the sealing ring through the cooperation of the cylindrical protrusion of the lower end cover and the connecting plate of the upper end cover. Moreover, the operation of this device is simple. When replacing the sealing ring to be tested, it is only necessary to separate the lower end cover from the upper end cover, and then the replacement of the sealing ring to be tested on the cylindrical protrusion can be realized, which reduces the operation time and simplifies the operation process, so that more sealing rings can be effectively tested in the same time.

[0023] The present utility model is provided with a protrusion structure on the connecting member of the upper end cover, which can make the connection between the air source pipeline and the connecting member more firm and reliable. At the same time, a slope is also arranged on the connecting member, and the slope can assist in the connection of the air source pipeline, thereby reducing the operation difficulty of the connection and shortening the preparation time required for the experiment. Description of the Drawings

[0024] Figure 1 It is a schematic structural diagram of the combined upper end cover and lower end cover of the present utility model;

[0025] Figure 2 This is a semi-transparent schematic diagram after the upper end cover and the lower end cover of the present utility model are combined;

[0026] Figure 3 This is a schematic structural diagram of the upper end cover of the present utility model;

[0027] Figure 4 This is a schematic structural diagram of the lower end cover of the present utility model;

[0028] Figure 5 This is a connection diagram for the combined seal ring test of the present utility model.

[0029] Some of the attached drawings are described as follows:

[0030] 1. Upper end cover; 2. Lower end cover; 3. Bolt; 4. Air source; 5. Pressure gauge; 6. High-temperature aging box; 7. Connection plate; 8. Connection column; 9. Connector; 10. Protrusion structure; 11. Inclined surface; 12. Annular groove; 13. Seal ring to be tested; 14. Cylindrical protrusion; 15. First threaded hole; 16. Second threaded hole; 17. Air source switch. Detailed implementation manners

[0031] The following will describe in detail the exemplary embodiments, features and aspects of the present utility model with reference to the attached drawings. The same reference numerals in the drawings denote elements having the same or similar functions. Although various aspects of the embodiments are shown in the drawings, the drawings do not have to be drawn to scale unless otherwise specified.

[0032] The present utility model provides a test device for the life test of an aviation combined seal ring, as Figures 1-4 shown, which includes an upper end cover 1, a lower end cover 2, an air source 4, a pressure gauge 5 and a high-temperature aging box 6, and the upper end cover 1 is arranged above the lower end cover 2.

[0033] The upper end cover 1 includes a connection plate 7, a connection column 8 and a connector 9. The first surface of the connection plate 7 is connected to the side surface of the lower end cover 2, the first end of the connection column 8 is connected to the middle of the second surface of the connection plate 7, and the connector 9 is arranged on the second end of the connection column 8.

[0034] A protrusion structure 10 is arranged on the side wall of the connector 9, and an inclined surface 11 is arranged at one end of the connector 9 away from the connection column 8.

[0035] A plurality of annular grooves 12 are formed on the inner side wall of the connection plate 7.

[0036] A cylindrical protrusion 14 that is in fit connection with the inside of the connection plate 7 is arranged at the central position of the lower end cover 2.

[0037] The seal ring 13 to be tested is sleeved on the cylindrical protrusion 14.

[0038] The upper end cover 1 is connected to the lower end cover 2 by bolts 3.

[0039] A plurality of first threaded holes 15 are provided on the connecting plate 7, and a plurality of second threaded holes 16 that cooperate with the first threaded holes 15 are provided on the lower end cover 2.

[0040] The connecting plate 7, the connecting column 8, and the connecting member 9 are all of an integral hollow structure. The connecting member 9 can be connected to an external air pump to pressurize the interior of the upper end cover 1. The interior is designed with a gas medium and can withstand high-pressure gas to simulate the actual working state and actual working medium conditions of the combined sealing ring.

[0041] After the upper end cover 1 and the lower end cover 2 are connected, they are installed inside the high-temperature aging box 6. The gas source 4 is sleeved and connected to the connecting member 9 of the upper end cover 1 through a gas source pipeline, and the pressure gauge 5 is arranged on the crude oil pipeline.

[0042] A gas source switch 17 is also provided on the gas source pipeline to control the connection or disconnection between the gas source pipeline and the upper end cover.

[0043] The gas source pipeline is in a communicating state with the interior of the upper end cover 1.

[0044] A chamfer is provided in the annular groove 12 to reduce damage to the sealing ring 13 to be tested.

[0045] The roughness of the contact surface where the connecting plate 7 is connected to the lower end cover 2 is designed to be 1.6, meeting the actual installation interface of the product to be tested. The external roughness is 3.2 to save processing costs, and the general tolerance is designed in accordance with HB5800-1999.

[0046] After the upper end cover 1 and the lower end cover 2 are connected, the air pump is then connected to the upper end cover 1. Finally, the connected assembly is placed in water for a sealing test to test its sealing performance. If bubbles appear, it is considered that the combined sealing ring has failed, that is, the combined sealing ring has reached the service life.

[0047] The combined sealing ring test tooling of the present utility model can withstand the use environment of high temperature outside and high pressure inside. Its test connection diagram is as Figure 5 shown.

[0048] The embodiments described above are only descriptions of the preferred embodiments of the present utility model, and do not limit the scope of the present utility model. Without departing from the design spirit of the present utility model, various deformations and improvements made by those of ordinary skill in the art to the technical solutions of the present utility model shall all fall within the protection scope determined by the claims of the present utility model.

Claims

1. An experimental device for the life test of an aviation combined sealing ring, characterized in that: It includes an upper end cover and a lower end cover, and the upper end cover is arranged above the lower end cover; The upper end cover includes a connecting plate, a connecting column and a connecting piece. The first surface of the connecting plate is connected to the side surface of the lower end cover. The first end of the connecting column is connected to the middle of the second surface of the connecting plate. The connecting piece is arranged at the second end of the connecting column; A convex structure is arranged on the side wall of the connecting piece, and an inclined surface is arranged at one end of the connecting piece away from the connecting column; A plurality of annular grooves are formed on the inner side wall of the connecting plate; A cylindrical protrusion that is connected in cooperation with the inside of the connecting plate is arranged at the central position of the lower end cover; The sealing ring to be tested is sleeved on the cylindrical protrusion; 2. The test device for the life test of the aviation combined sealing ring according to claim 1, characterized in that: The upper end cover is connected to the lower end cover by bolts; 3. The test device for the life test of the aviation combined sealing ring according to claim 2, characterized in that: A plurality of first threaded holes are formed in the connecting plate, and a plurality of second threaded holes that are matched with the first threaded holes are formed in the lower end cover; 4. The test device for the life test of the aviation combined sealing ring according to claim 1, characterized in that: The connecting plate, the connecting column and the connecting piece are all of an integral hollow structure; 5. The test device for the life test of the aviation combined sealing ring according to claim 4, characterized in that: It further includes a gas source, a pressure gauge and a high-temperature aging box. After the upper end cover and the lower end cover are connected, they are installed inside the high-temperature aging box. The gas source is sleeved and connected to the connecting piece of the upper end cover through a gas source pipeline, and the pressure gauge is arranged on the gas source pipeline; 6. The test device for the life test of the aviation combined sealing ring according to claim 5, characterized in that: A gas source switch is further arranged on the gas source pipeline; 7. The test device for the life test of the aviation combined sealing ring according to claim 5, characterized in that: The gas source pipeline is in a communicating state with the inside of the upper end cover; 8. The test device for the life test of the aviation combined sealing ring according to claim 1, characterized in that: A chamfer is arranged in the annular groove;

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