A low-temperature high-speed end-face sealing test device for a liquid rocket engine turbo pump

A liquid rocket and end face sealing technology, which is applied in the direction of rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problems of no end face sealing test device, etc., achieve strong functionality, good performance, and ensure coaxiality accuracy Effect

Active Publication Date: 2019-12-20
BEIJING AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
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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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  • A low-temperature high-speed end-face sealing test device for a liquid rocket engine turbo pump

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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 liquid rocket engine turbo pump, and to detect the sealing performance between the static ring assembly and the moving ring of the turbo pump, the present invention designs a test device, which needs to meet the low temperature of -196 °C And the working conditions at 40000r / min speed, and no shrinkage deformation in low temperature environment, at the same time to ensure the dynamic stability of the stepped spindle and the requirements of low-speed dynamic balance to remove weight.

[0025] The end face sealing products (engine static ring assembly and engine moving ring) are assembled into the test device of the present invention, the working environment of the engine turbo pump is simulated, the sealing performance and structural rationality of the sealing assembly products are assessed, and the sealing assembly products can be quantitatively detected The...

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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 sealing test device for a liquid rocket engine turbo pump, which is applied to the sampling test, run-in test and research test of the rocket engine end face seal assembly of liquid hydrogen and liquid oxygen propellants, and belongs to the liquid rocket engine turbo pump Use the face seal application area. Background technique [0002] The turbo pump is an important component of the liquid rocket engine, and the end seal is a key part of the turbo pump. The reliability of the end seal is the basis for the reliability of the engine. Under the condition of low temperature and high speed, the sealing performance of the end face seal is related to factors such as pressure, speed, stiffness of the static ring bellows, and compression of the static ring. The end face seal test device is to simulate the working environment of the engine turbo pump: including pressure, temperature and flow to...

Claims

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Application Information

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Patent Type & Authority Patents(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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