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Calculation method of insulation power of high pressure hybrid gas turbine for liquid rocket engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2023年01期
Page:
65-71
Research Field:
目次
Publishing date:

Info

Title:
Calculation method of insulation power of high pressure hybrid gas turbine for liquid rocket engine
Author(s):
SU Zhan;  GAO Yushan;  QIN Yanping;  ZHANG Hang;  ZHANG Xiaoguang;  XING Lixiang
(Xian Aerospace Propulsion Institute, Xian 710100, China)
Keywords:
high pressure gas turbine adiabatic work cubic state equation mixed rule
PACS:
V430
DOI:
-
Abstract:
In the design of liquid rocket engine, the thermal insulation work of the turbine is an important design parameter that affects the engine thrust, and the accuracy of the calculation directly affects the efficiency of the turbine design.Under high pressure, the effect of real gas is prominent, which affects the accuracy of adiabatic work calculation and must be taken into account.This paper compares and analyzes the accuracy of three cubic equation[Soave-Redlich-Kwong(SRK),Peng-Robinson(PR),Redlich-Kwong- Peng-Robinson(RK-PR)] of state describing the thermodynamic properties of oxygen, methane and hydrogen.The results show that the accuracy of SRK equation is the best, the maximum error with NISTs data is less than 2.Besides, the high-pressure turbines gas is a multi-component mixture, and the calculation of the adiabatic work should consider the mixing rule.Assuming the expansion of the turbine is isentropic, the formulas of the ideal gas hypothesis and the turbine adiabatic work considering the equation under the mixing rule are derived respectively.And it is proved that the calculation s error of the ideal gas adiabatic work is much higher than the real gas.Finally, an algorithm for calculating the thermal insulation work of high-pressure turbo-engines is presented, which is calculating the approximate adiabatic work of high-pressure turbine by compressing factor, and the maximum error between the method and the theoretical method is less than 3.

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