一种航空发动机涡轮导向器叶片热冲击试验系统设计  

Design of Thermal Shock Test System for Aeroengine Turbine Guide Vane

作　　者：徐健[1] 霍施宇[1] 燕群[1] Xu Jian;Huo Shiyu;Yan Qun(Aviation Science and Technology Key Laboratory of Aviation Acoustics and Vibration,AVIC Aircraft Strength Research Institute,Xi′an 710065,Shaanxi,China)

机构地区：[1]中国飞机强度研究所,航空声学与振动航空科技重点实验室,陕西西安710065

出　　处：《工程与试验》2023年第1期66-68,共3页Engineering and Test

基　　金：专项科研项目(WDZC-2019-04)。

摘　　要：航空发动机涡轮导向器叶片是发动机热端部件受热最严重的构件之一,在研发设计过程中,需要开展大量的热冲击试验。本文利用丙烷-氧气燃烧产物参数和航空煤油燃烧产物参数较为接近的特点,研发了一套考虑叶片内部主动气流冷却的涡轮导向器叶片热冲击试验系统,能够低成本并且较为真实地还原涡轮导向器叶片外部加热内部冷却的受热特征。Aeroengine turbine guide vane is one of the most severely heated components of engine hot components.In the process of R&D and design,a large number of thermal shock tests need to be carried out.In this paper,based on the characteristics that the parameters of propane oxygen combustion product are close to aviation kerosene,a set of thermal shock test system for turbine guide vane considering active airflow cooling inside the vane is developed,which can simulate the heating characteristics of turbine guide vane with external heating and internal cooling at a lower cost and more realistically.

关 键 词：涡轮 导向器叶片 热冲击试验系统 内部冷却 

分 类 号：V216.8[航空宇航科学与技术—航空宇航推进理论与工程]