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End face sealing test device for liquid rocket engine turbine pump under low-temperature and high-speed

A liquid rocket, end-face sealing technology, applied in rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problem of no end-face sealing test device, etc., and achieve the effect of strong functionality, good test results, and improved stability.

Active Publication Date: 2018-10-26
BEIJING AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, there is no end face sealing test device suitable for low temperature and high speed conditions

Method used

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  • End face sealing test device for liquid rocket engine turbine pump under low-temperature and high-speed

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Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0024] In order to carry out the low-temperature high-speed sampling test and running-in test of the end face seal of the turbo pump of the liquid rocket engine, and to detect the sealing performance between the static ring assembly and the moving ring of the turbo pump, a test device is designed in the present invention, and the device needs to meet the low temperature of -196 ℃ And the working conditions at 40000r / min speed, and no shrinkage deformation under low temperature environment, at the same time to ensure the dynamic stability of the stepped spindle and the requirements of low-speed dynamic balance and weight removal.

[0025] Assemble the end face seal products (engine static ring assembly and engine dynamic ring) into the test device of the present invention, simulate the working environment of the engine turbo pump, evaluate the sealing performance and structural rationality of the seal assembly products, and quantitatively detect the seal assembly products. It ca...

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Abstract

The invention discloses an end face sealing test device for a liquid rocket engine turbine pump under a low-temperature and a high-speed. The device is applied to a sampling test of an end face sealing assembly of a rocket engine of a liquid hydrogen liquid oxygen propellant, in a running-in test and a research performance test, an end face sealing assembly product ( such as an engine static ringassembly and an engine moving ring ) is assembled in the test device of the invention, a working environment of the engine turbine pump is simulated, the sealing performance and the structural rationality of the sealing assembly product are checked, and the sealing performance of the sealing assembly product can be quantitatively detected. According to the device, the test device does not contractand deform under a low-temperature environment, and runs stably at a high speed, the device provides an important basis for improving various problems in the design of the end face sealing assembly product.

Description

technical field [0001] The invention relates to a low-temperature and high-speed end face seal test device for a liquid rocket engine turbo pump, which is applied to the sampling test, running-in test and research test of a rocket engine end face seal assembly of liquid hydrogen and liquid oxygen propellants, and belongs to the liquid rocket engine turbo pump Seal the application area with a face. Background technique [0002] The turbo pump is an important component of the liquid rocket engine, and the end face seal is the key part of the turbo pump. The reliability of the end face seal is the basis of the reliability of the engine. Under the condition of low temperature and high rotation speed, the sealing performance of the face seal is related to factors such as pressure, rotation speed, rigidity of the static ring bellows and the compression amount of the static ring. The end face seal test device is to simulate the working environment of the engine turbo pump: includi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 董丽双钱云方何伟锋秦雷连军伟孟博丁张栋刘国龙李佳
Owner BEIJING AEROSPACE PROPULSION INST
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