航空发动机涡轮机匣温度试验对比验证研究

涡轮机匣结构复杂且工作环境比较恶劣,直接利用发动机部件开展机匣表面换热规律研究难度极大.通过采用简化模型的基础研究结合某发动机部件试验验证的方式进行研究.在基础研究中,取涡轮机匣的1个周期性扇段作为研究对象,对机匣结构中的一些圆弧、倒角、倒圆等结构进行了简化,采用数值计算和瞬态液晶测试技术获得了涡轮机匣表面换热经验关系式；在验证试验中,针对某发动机部件,在压力和温度均接近发动机工况下进行试验,获得了涡轮机匣表面换热情况,并对基础研究获得的经验关系式进行了验证.研究结果表明:基础研究获得的换热经验关系式在发动机部件试验中同样适用.应用的研究方法可供类似研究借鉴.

Temperature Comparative Experiment on Aeroengine Turbine Casing

Due to the complicated structure and bad operation environment of turbine casing, the heat transfer law was hardly studied by engine components. Based on the simplified model combined with engine components the casing experimental verification, taking the turbine casing 1 periodic sector as the research object, Some arc, chamfer, fillet structure of was simplified, and the turbine casing surface heat transfer formula was presented by the numerical calculation and transient liquid crystal test technology. An engine components were tested, which pressure and temperature are close to the operation. The turbine casing surface heat transfer was obtained and the experience formula of basic research was also verified. The study results show that the heat transfer formula in the basic study is also applicable in the engine components test, and the application study method can provide reference to similar studying