Aero-engine turbine blade surface crystal temperature measurement correction method

The invention belongs to the technical field of aero-engine turbine blade surface crystal temperature measurement, and particularly relates to an aero-engine turbine blade surface crystal temperature measurement correction method, which comprises the steps of 1, acquiring a distance L from a crystal to the outer wall surface of a turbine blade; 2, the temperature tm of the position, L away from the outer wall face, in the turbine blade is measured, and the crystal measurement temperature tjt is taken; 3, calculating the heat flux q between the gas side and the cold air side of the turbine blade; 4, based on tm and q, the temperature tb of the outer wall face of the turbine blade is calculated; and 5, based on tb and q, calculating the temperature ttc of the outer wall surface of the turbine blade coating. 本申请属于航空发动机涡轮叶片表面晶体测温技术领域，具体涉及一种航空发动机涡轮叶片表面晶体测温修正方法，包括：步骤一、获取晶体到涡轮叶片外壁面的距离L；步骤二、将涡轮叶片内部距离外壁面L处的温度tm，取晶体测量温度tjt；步骤三、计算涡轮叶片燃气侧、冷气侧间的热通量q；步骤四、基于tm、q，计算涡轮叶片外壁面温度tb；步骤五、基于tb、q，计算涡轮叶片涂层外壁面温度ttc。