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Engine test propellant supply low frequency ripple suppression method and system

A pulsation suppression and propellant technology, applied in jet engine testing, gas turbine engine testing, etc., can solve problems such as reducing engine stability, resonance, and heavy equipment weight, and achieve improved stability, reduced pulsation, and uniform injection devices Effect

Active Publication Date: 2018-08-10
XIAN AEROSPACE PROPULSION TESTING TECHN INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Pulsation interference reduces the stability of the engine, and when the frequency of the pulsation is similar to that of other parts of the supply system, resonance will occur, affecting the stability of the entire test system
The existing conventional method is to use an accumulator to adjust, this method is heavy in equipment weight and the adjustment effect is not ideal

Method used

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  • Engine test propellant supply low frequency ripple suppression method and system
  • Engine test propellant supply low frequency ripple suppression method and system
  • Engine test propellant supply low frequency ripple suppression method and system

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Embodiment Construction

[0063] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0064] The method of the present invention calculates parameters such as helium injection gas volume, gas distribution, and injected gas form of the propellant supply pipeline through simulation simulation, and the mixing of the simulated gas changes the natural frequency of the propellant supply system to adjust the self-pulsation of the propellant. Reduced coupling of the propellant supply system to the engine. Due to the cavitation margin of the engine turbo pump, it will not affect the work of the engine under the condition that the form gas volume is controllable. Through the application of this method, the pulsation of propellant supply is reduced, the stability of propellant supply is improved, and the stability of the entire engine pump system is further improved. This method was applied in engine tests.

[0065] Combining simulation ...

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Abstract

The invention relates to an engine test propellant supply low frequency ripple suppression method and system. Accurate helium injection is performed on the propellant supply pipeline, the inherent frequency of the propellant supply system is changed through gas mixing, and the ripple of the propellant can be adjusted through accurate control of the injection gas volume, the gas distribution and the injection gas form and the coupling situation of the propellant supply system and the engine can be reduced. With application of the method, the propellant supply ripple can be reduced, the propellant supply stability can be enhanced and thus the stability of the whole engine pump system can be enhanced. The method and the system are applied to the engine test.

Description

technical field [0001] The invention relates to a method and system for suppressing low-frequency pulsation of propellant supply for engine test. Background technique [0002] In the rocket engine test, due to the high-speed rotation of the turbo pump, there are relatively serious pressure and flow pulsations in the propellant supply pipeline. Pulsation interference reduces the stability of the engine, and when the frequency of the pulsation is similar to that of other parts of the supply system, resonance occurs, which affects the stability of the entire test system. The existing conventional method is to use an accumulator for adjustment, which is heavy in equipment weight and unsatisfactory in adjustment effect. Contents of the invention [0003] In order to reduce the pressure and flow pulsation of the propellant supply system, improve the stability of the propellant supply, and then improve the stability of the entire engine pump system, the present invention provide...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/14
CPCG01M15/14
Inventor 张志涛唐斌运罗帅帅曹庆红王文龙杨战伟付正
Owner XIAN AEROSPACE PROPULSION TESTING TECHN INST
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