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Liquid rocket engine thermal test parameter setting method considering real gas effect

A real gas and liquid rocket technology, used in jet engine testing, gas turbine engine testing, etc., can solve problems such as insufficient consideration of the impact, and achieve the effect of accurate thermal test parameters and reduced test risks.

Active Publication Date: 2021-03-23
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology

The existing liquid rocket engine thermal test parameter setting method does not fully consider the influence of real gas effects on the liquid rocket engine thermal test parameters

Method used

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  • Liquid rocket engine thermal test parameter setting method considering real gas effect
  • Liquid rocket engine thermal test parameter setting method considering real gas effect
  • Liquid rocket engine thermal test parameter setting method considering real gas effect

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Embodiment Construction

[0037] The present invention is further described in detail below by way of examples.

[0038] For the high-pressure turbine, the theoretical adiabatic work deviation of the turbine based on the ideal gas reaches 10%-20%. This will lead to the deviation of the turbine power, which in turn will lead to the deviation of the static parameter balance of the liquid rocket engine, which will cause the excessive deviation of the turbo pump speed and the turbine outlet temperature, resulting in the excessive deviation between the experimental data and the theoretical setting working condition parameters.

[0039] For this reason, the following embodiments fully consider the influence of the real gas effect on the turbine power, and the calculation of the turbine power based on the ideal gas is corrected.

[0040] Turbine power calculation method 1:

[0041] Based on the turbine power of the ideal gas, the influence of the real gas effect on the adiabatic work of the turbine is consid...

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Abstract

The invention provides a liquid rocket engine thermal test parameter setting method considering a real gas effect, and aims to avoid deviation of turbine power calculation. According to the method, onthe basis of turbine power of ideal gas, the influence of a real gas effect on turbine adiabatic work is considered, and the turbine power of the ideal gas is corrected through linear weighting of agas compression factor, wherein the gas compression factor is solved based on an RKS state equation; and based on the turbine power obtained through calculation, other thermal test parameters are calculated according to flow, pressure and power balance. According to the invention, the influence of the real gas effect on the turbine power is fully considered, and the set engine joint test and hot test working condition parameters are more accurate, so that the test risk can be reduced.

Description

technical field [0001] The invention relates to a method for setting thermal test parameters of a liquid rocket engine, in particular to engineering calculation of efficient turbine power under high temperature and high pressure. Background technique [0002] The high-thrust liquid oxygen kerosene engine is one of the reasonable power choices for my country's future deep space exploration, manned moon landing and large-scale space activities. Before the gas generator / turbine pump is connected, it is necessary to determine the test conditions parameters, that is, to set the thermal test parameters of the liquid rocket engine, including turbine power, turbo pump speed, gas generator temperature, etc. Among them, it is first necessary to accurately set the turbine power, and then calculate other thermal test parameters according to the flow, pressure, and power balance. [0003] As the thrust and performance of the liquid oxygen kerosene engine increase, the pressure and tempe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/14
CPCG01M15/14
Inventor 秦艳平马冬英蒲星星邢理想王海燕李鹏飞张晟
Owner XIAN AEROSPACE PROPULSION INST
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