|Table of Contents|

Numerical study on aerodynamic optimization of liquid rocket engine turbine(PDF)

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

Issue:
2020年05期
Page:
21-26
Research Field:
研究与设计
Publishing date:

Info

Title:
Numerical study on aerodynamic optimization of liquid rocket engine turbine
Author(s):
YU Qing1; ZHAO Hui2; YUAN Weiwei1; LI Aimin1; ZHANG Yatai1
(1.Xi’an Aerospace Propulsion Institute,Xi’an 710100,China; 2.The Equipment Project Management Center of the Rocket Army, Beijing 100085, China)
Keywords:
liquid rocket engine;  turbine;  area ratio;  aerodynamic optimization
PACS:
V434.211
DOI:
-
Abstract:
During the development of a liquid rocket engine, in order to completely mix and condense the gas driving the turbine in the oxygen pre-pressurized turbo pump with the liquid oxygen in the main circuit, it is necessary to improve the turbine performance as much as possible.In this paper, the parallel multi-objective aerodynamic optimization design software was used to optimize the cascade design of the oxygen pre-pressurized turbo pump with the adaptive multi-objective differential evolution algorithm as the optimization tool.The calculation results show that after the optimization design of the turbine, the internal flow loss is reduced and then the overall efficiency is increased by 3.739%.The maximum stress of the two stage blades of the turbine rotor is less than the yield strength of the material, which meets the strength requirements.The turbine cascade can be optimized by the parallel multi-objective aerodynamic optimization method, which reduces the gas ratio and is beneficial to the complete dissolution of gas in the oxygen pre-pressurized turbo pump of rocket engine.

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Last Update: 2020-10-20