涡喷发动机全三维流-热-固耦合建模方法  

Modeling of turbojet engines based on three-dimensional fluid-thermal-structural coupling method

作　　者：魏杰[1] 温孟阳 杨合理 王旭 郑新前[1] WEI Jie;WEN Mengyang;YANG Heli;WANG Xu;ZHENG Xinqian(School of Vehicle and Mobility,Tsinghua University,Beijing 100084,China;Institute for Aero Engine,Tsinghua University,Beijing 100084,China;Guangxi Hawk Power Technology Company Limited,Guilin Guangxi 541003,China)

机构地区：[1]清华大学车辆与运载学院,北京100084 [2]清华大学航空发动机研究院,北京100084 [3]广西虹鹰动力科技有限公司,广西桂林541003

出　　处：《航空动力学报》2025年第2期72-80,共9页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅱ-0004-0016,J2019-Ⅰ-0021-0020)。

摘　　要：建立了单通道流-热和全通道热-固的耦合建模方法,对某涡喷发动机进行了全三维流-热-固耦合分析,并与不考虑耦合的方法进行了对比,在温度、应力和变形等方面均有较大差异。流-热耦合的压气机转子叶片温度较不耦合偏低15 K,三级扩压器温度较不耦合偏低10~20 K。热-固耦合的压气机转子最大等效应力比不耦合小31 MPa(4.7%),径向变形比不耦合大0.02 mm(11.1%)。流-热-固耦合预测的设计点涡轮叶尖间隙变化0.54 mm。该方法实现了整机温度场、应力场、变形场的分析,综合评估了部件的强度和变形,为部件优化提供了数据支撑。A single-passage fluid-thermal and full-passage thermo-structural coupling modeling method was established,and three-dimensional fluid-thermal-structural coupling analysis of a turbojet engine was carried out.Compared with the method without coupling,there were great differences in temperature,stress,and deformation.The temperature of the compressor impeller of the fluid-thermal coupling method was 15 K lower than that of the uncoupled,and the temperature of the three-stage diffuser was 10—20 K lower than that of the uncoupled.The maximum equivalent stress of the compressor impeller of the thermal-structural coupling method was 31 MPa(4.7%)smaller than that of the uncoupled,and the radial deformation of the compressor impeller was 0.02 mm(11.1%)larger than that of the uncoupled.The tip clearance variation of the turbine at the design point predicted by the fluid-thermalstructural coupling analysis was 0.54 mm.This method realized the analysis of the temperature field,stress field,and deformation field of the whole engine,comprehensively evaluated the strength and deformation of components,and provided data support for component optimization.

关 键 词：涡喷发动机 全三维数值仿真 流-热-固耦合 间隙预测 结构分析 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]