摘要
闭式循环液体火箭发动机涡轮叶片载荷大,温度分布复杂,叶片变形对气动参数影响显著。在以往的液体火箭发动机涡轮设计中,一般将设计出的叶片直接进行加工,而不考虑工作变形的影响。提出了一种叶片冷热态转换的方法,并以某发动机主涡轮为研究对象,首先通过气热固耦合仿真对比叶片变形对气动性能的影响,变形后的涡轮效率、流量、轴向力等参数均发生了显著变化,然后通过修正迭代对该叶片进行变形补偿,将热态工作叶片转化为冷态加工叶片。结果表明,该方法可以使叶型的气动参数得到精确控制,可开展工程应用。
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.
作者
任众
许开富
韩飞
REN Zhong;XU Kaifu;HAN Fei(Xi＇ an Aerospace Propulsion Institute, Xi＇ an 710100, China)
出处
《火箭推进》
CAS
2018年第2期33-38,共6页
Journal of Rocket Propulsion
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
liquid rocket engine
turbine blade
deformation influence analysis
cold and hot state conversion
