Liquid rocket engine turbine pump rotor low-temperature displacement measuring device

A turbo pump rotor, liquid rocket technology, applied in rocket engine devices, measuring devices, engine testing and other directions, to achieve the effect of ensuring low temperature sealing, high safety and reliability, and reducing temperature drift performance

Active Publication Date: 2022-03-18
BEIJING AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in the prior art, there is no related device that can monitor the axial displacement and radial displacement of the rotor system in real time in a low temperature environment, and it is impossible to perform fault detection and early warning of the real-time operation of the rotor system based on the above principles

Method used

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  • Liquid rocket engine turbine pump rotor low-temperature displacement measuring device
  • Liquid rocket engine turbine pump rotor low-temperature displacement measuring device
  • Liquid rocket engine turbine pump rotor low-temperature displacement measuring device

Examples

Experimental program
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Embodiment 1

[0049] The installation diagram and sensor plan of the axial displacement sensor are as follows: figure 1 As shown, 6 in the figure represents the turbo pump rotor in the turbo pump rotor assembly or other moving parts that are relatively stationary with the turbo pump rotor. During the operation of the turbo pump, there will be an axial displacement relative to a stationary part 7 inside the turbo pump. 61 represents the measured surface, 10 is the axial displacement sensor, the type of sensor is an eddy current displacement sensor, and its plan view is as follows figure 1 As shown in (b), the internal axial space of the turbo pump is usually small, so the shape of the axial displacement sensor is generally designed as a prolate cuboid shape, the length can be controlled at 20mm, and the width is about 10mm, in which the circular area is where the sensor probes 102 are distributed. area, the sensor is fixed on the stationary part 7 by passing through two sensor installation t...

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Abstract

The invention discloses a liquid rocket engine turbine pump rotor low-temperature displacement measuring device which comprises an axial displacement sensor, a radial displacement sensor and a sensor base assembly, the axial displacement sensor and the radial displacement sensor are installed in a turbine pump, and the sensor base assembly is provided with multiple seals. The low-temperature sealing performance of the turbine pump can be guaranteed while the wire is led out, the axial displacement and the radial displacement of the rotor assembly of the oxyhydrogen turbine pump in the low-temperature environment running process can be monitored in real time, the axial displacement and the axis track of the rotor are obtained on the basis, a criterion is provided for the working health state of the turbine pump, and the reliability of the turbine pump is improved. The system is especially suitable for on-line monitoring and fault early warning when an engine test and flight mission execution are carried out.

Description

technical field [0001] The invention belongs to the technical field of liquid rocket engines, and in particular relates to a low-temperature displacement measuring device for a turbine pump rotor of a liquid rocket engine. Background technique [0002] With the increasing demand of people to explore the vast universe, the number of manned spaceflight projects, the construction of space stations, and the launch missions such as landing on Mars and deep space exploration are increasing, and there are higher standards and higher standards for the safety and reliability of launch vehicles. Stringent requirements. For this reason, the world's aerospace industry has also ushered in a new era of digital development. In the construction of digital aerospace, real-time measurement of the actual working status of each important component in the system is an essential and important link. Based on the actual working parameters of the current components, it can judge and warn whether t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F02K9/46F04D15/00G01M15/02G01M15/14G01B7/02G01K7/16
CPCF02K9/96F02K9/46F04D15/0088F04D15/0077G01M15/02G01M15/14G01B7/02G01K7/16
Inventor 周丹洋徐世洋沈文金黄克松李小芬陈钊金志磊林奇燕闻林元安阳杨文静
Owner BEIJING AEROSPACE PROPULSION INST
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