A high temperature and high pressure gas environment measurement installation structure
A technology of environmental measurement and installation structure, which is applied in the direction of measuring devices, machine/structural component testing, engine testing, etc., to achieve reasonable design effects
Active Publication Date: 2018-05-18
BEIJING AEROSPACE PROPULSION INST
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[0004] The purpose of the present invention is to provide a high temperature and high pressure gas environment measurement installation structure, which aims to solve the problem of measurement installation under high temperature and high pressure gas environment conditions
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[0017] A high-temperature and high-pressure gas environment measurement installation structure according to the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.
[0018] A high-temperature and high-pressure gas environment measurement installation structure according to the present invention, the high-temperature and high-pressure gas environment measurement installation structure includes a quartz glass observation window and a tungsten-infiltrated copper installation ring; the quartz glass observation window is mainly composed of an observation section wall, an observation window It consists of an adapter seat and an observation window.
[0019] Such as figure 1 As shown, the quartz glass observation window includes a cylindrical observation section wall 3, the observation window adapter seat 2 is fixed outside the observation section wall 3, and the observation window 1 is fixed on the observ...
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The invention provides a high-temperature and high-pressure gas environment measurement installation structure. The high-temperature and high-pressure gas environment measurement installation structure includes a quartz glass observation window and a tungsten-infiltrated copper installation ring; the quartz glass observation window includes a cylindrical observation section wall , the observation window adapter seat is fixed outside the wall of the observation section, and the observation window is fixed on the observation window adapter seat; a flexible graphite gasket is arranged at the connection between the observation section wall and the observation window adapter seat; the tungsten copper-infiltrated installation ring includes a cylinder Shaped tungsten infiltrated copper inner wall, fix the metal outer wall outside the tungsten copper infiltrated inner wall, set the igniter adapter seat at the upper end of the central through hole of the metal outer wall, and set the measuring nozzle at the lower end of the central through hole of the metal outer wall. The invention can satisfy the installation of large-diameter structures such as igniters and high-frequency pulsation pressure sensors, and is suitable for the alternating test environment of the hydrogen-oxygen engine from low-temperature precooling to high-temperature operation, and solves the difficulty in installing the grooved regenerative cooling combustion chamber wall The problem.
Description
technical field [0001] The invention relates to a measurement installation structure, in particular to a measurement installation structure suitable for high temperature (1000K-3600K) high pressure (above 10MPa) gas environment. Background technique [0002] In engineering tests, a safe and reliable measurement structure is an important factor affecting the success of the test. The high temperature and high pressure gas environment puts forward higher requirements for the sealing and installation of the measurement structure. [0003] In the current liquid rocket engine combustion test, for a gas environment with a gas temperature of less than 1000K and a working pressure of less than 10MPa, the combustion chamber wall usually adopts a thick-walled superalloy structure to achieve thermal protection. For a gas environment with a gas temperature of 1000K-3600K and a working pressure of 10MPa or more, the combustion chamber wall usually adopts a grooved regenerative cooling st...
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IPC IPC(8): G01M15/02
Inventor 赵世红丁兆波张晋博王仙许晓勇田原刘红珍姬威信潘刚王召刘中祥陶瑞峰郑孟伟
Owner BEIJING AEROSPACE PROPULSION INST