液氧/煤油发动机试验扩压器热力耦合特性分析  

Analysis on thermal mechanical coupling characteristics of diffuser in test of liquid oxygen/kerosene rocket engine

作　　者：秦永涛[1] 唐斌运[1] 沈继彬[1] 李波[1] 

机构地区：[1]西安航天动力试验技术研究所,陕西西安710100

出　　处：《火箭推进》2016年第1期71-76,共6页Journal of Rocket Propulsion

摘　　要：针对液氧/煤油发动机试验台现有高模试验扩压器存在的局部焊缝开裂问题,基于燃气扩压器的热力耦合环境,采用雷诺平均方程和sst k-ε湍流模型,对扩压器内部的压力场、速度场和温度场进行分析,根据燃气冷却换热对扩压器内部温度梯度进行研究;用有限元法对扩压器冷却结构进行热应力分析,结合扩压器加工结构特点,确定局部焊缝开裂内外因根源;最后通过试验过程的扩压器应变测量,验证了该方法有效性,为解决扩压器焊缝开裂问题和现有扩压器改进设计提供了分析方法和理论指导。For solving the part weld crazing problem of diffuser in high-altitude simulation test in a liquid oxygen/kerosene rocket engine, Reynolds mean equation and sst k-ε turbulence model were used to analyze the inner temperature field, pressure field and velocity field in the diffuser under the thermal mechanical coupling environment of diffuser. The inner temperature gradient of the diffuser was researched according to the gas cooling and heat transfer. A thermal stress analysis for the cooling structure of the diffuser is conducted with finite element method to confirm the internal and external cause of part weld crazing in consideration of the structural characteristics of the diffuser.The validity and accuracy of the method were proved by strain measurement of the diffuser in the process of a liquid oxygen/kerosene rocket engine test, which provided an analysis method and theoretical guidance for solving the weld crazing problem of the diffuser and modifying the design of the available diffuser

关 键 词：扩压器 发动机试验 热力耦合 热应力分析 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]