Testing device for throat liner of rocket engine nozzle
A rocket engine and testing device technology, which is applied in the direction of rocket engine devices, jet propulsion devices, machines/engines, etc., can solve the problem of high cost of nozzle throat lining ablation tests, large differences, and inability to ablate performance of different throat lining materials Assessment and other issues, to achieve low processing and assembly process costs, reduce test costs, and shorten the effect of test time
Inactive Publication Date: 2022-01-11
北京星河动力航天科技股份有限公司 +2
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Problems solved by technology
[0004] In view of the shortcomings of the existing methods, this application proposes a test device for the nozzle throat lining of a rocket engine, which is used to solve the problem that the nozzle throat lining ablation test environment in the prior art is quite different from the real working environment, and it is impossible to simultaneously test different types of The ablation performance assessment of the throat lining material under the same gas environment or the high cost of the nozzle throat lining ablation test
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[0058] The nozzle unit 200 includes: a nozzle housing 210 and a nozzle insulation layer 220 .
[0059] One end of the nozzle housing 210 is connected to the test engine unit 100 .
[0060] The nozzle heat insulating layer 220 is arranged on the inner wall of the nozzle housing 210, and encloses the gas channel 201; the nozzle heat insulating layer 220 has a limiting groove around itself, and the limiting groove forms a test station.
[0061] In this embodiment, the thermal insulation layer provided on the nozzle unit 200 can also prevent the nozzle casing 210 from being damaged by the high temperature when the gas in the solid rocket motor burns. The specific position of the position is beneficial to the assembly and fixing of the nozzle throat liner.
[0062] In some possible implementations, the test stations are distributed around the circumference of the gas channel 201 at intervals.
[0063] In this embodiment, the shape of the test stations is limited by the way that t...
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The embodiment of the application provides a testing device for a throat liner of a rocket engine nozzle. The testing device for the throat liner of the rocket engine nozzle comprises a test engine unit and a nozzle unit which are connected with each other. The test engine unit is provided with a combustion chamber. The nozzle unit is provided with a fuel gas channel and at least two test stations. One end of the fuel gas channel communicates with the combustion chamber of the test engine unit, and the other end of the fuel gas channel communicates with an external environment of the test engine unit. The test stations surround the circumferential direction of the fuel gas channel. The test stations are used for correspondingly bearing different types of split throat liner test pieces. The combustion chamber is used for generating the same real fuel gas environment for simulating a rocket engine and testing the different types of split throat liner test pieces. According to the embodiment of the application, different types of split throat liner test pieces can be ablated simultaneously in the same ablation test, the test cost is reduced, and the ablation performance assessment precision of the throat liner test pieces is improved.
Description
technical field [0001] The present application relates to the technical field of solid rocket motor testing, in particular, the present application relates to a testing device for a nozzle throat liner of a rocket motor. Background technique [0002] As a key component of the solid engine, the nozzle plays the role of controlling the pressure of the combustion chamber, maintaining the normal combustion of the charge, and accelerating the expansion of the gas to generate thrust. When the solid rocket motor is working, the erosion of internal high-temperature, high-speed, two-phase flow (containing condensed phase aluminum oxide particles) gas will increase the throat diameter of the throat and thin the throat lining structure. However, the increase of the throat diameter of the nozzle will affect the internal ballistic characteristics of the solid rocket motor. If the ablation is abnormal, it may cause serious consequences that the solid rocket motor cannot work normally; the...
Claims
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IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 刘百奇肖波张胜敏刘建设
Owner 北京星河动力航天科技股份有限公司