火箭推进2018，Vol.44Issue(2)：33-38,6.
涡轮叶型冷热态转换在液体火箭发动机中的应用
Application of cold and hot state conversion of turbine blade profile in liquid rocket engine
任众 1许开富 1韩飞1
作者信息
- 1. 西安航天动力研究所,陕西西安710100
- 折叠
摘要
Abstract
As a key part of closed cycle liquid rocket engine,the turbine blade is inevitably deformed under the effect of flow field and thermal field,which leads to low efficiency and bad performance.In the traditional design of the turbine,the influent of blade deformation was not under consideration.A deforma-tion compensation method(cold and hot state conversion)is proposed in this paper.The effect of turbine blade deformation on its aerodynamic performance was studied by means of fluid-themo-structure coupling method.It is found that the efficiency,mass flow and axial force of the deformed turbine blade have changed significantly.Therefore,an iterative method is used to conduct deformation compensation for the blade,that is,convert the cold blade profile from a hot blade profile in the aerodynamic design.The re-sults reveal that the aerodynamic performance can be controled precisely by using this mechod which can be carried out for engineering application.关键词
液体火箭发动机/涡轮叶片/变形影响分析/冷热态转换Key words
liquid rocket engine/turbine blade/deformation influence analysis/cold and hot state conversion分类
航空航天引用本文复制引用
任众,许开富,韩飞..涡轮叶型冷热态转换在液体火箭发动机中的应用[J].火箭推进,2018,44(2):33-38,6.
