高空模拟状态下长焦距低压涡轮转子叶片温度场测试

Low Pressure Turbine Rotor Blades Temperature Field Measurement at Simulated Altitude ConditionsUsing Long Working Distance Pyrometer

中文关键词:  低压涡轮转子叶片  温度场  温度测试  高空模拟条件  航空发动机

英文关键词:low pressure turbine rotor blades  temperature field  temperature measurement  simulated altitude condition  aeroengine

中文摘要:

      为验证发动机叶片冷却设计效果，提高发动机寿命及可靠性，开展了高空模拟状态下低压涡轮转子叶片表面温度场测 试技术研究。基于辐射测温原理，设计了一种长焦距、可变测量角度的光学高温计探头，并在此基础上进行了测试改装方案设计、 冷却气源系统设计、光学高温计标定及涡轮叶片发射率测量，在不改变发动机结构的情况下成功实现了高空模拟环境下发动机中 间状态低压涡轮转子叶片表面温度测试，获取了低压涡轮转子叶片尾缘及叶背的温度场分布数据。结果表明：涡轮叶片尾缘温度 高于叶背温度；最高温度位于尾缘中间偏上位置；同一截面位置每个叶片温度无明显差异；随着距离发动机轴线半径逐渐减小，涡 轮叶片各截面径向平均温度逐渐降低。

英文摘要:

      In order to verify the cooling effect of an engine blade design, and improve the engine life and reliability, research was conducted on the surface temperature field measurement technology of low-pressure turbine rotor blades at simulated altitude conditions. Based on the principle of radiation temperature measurement, a long focal length optical pyrometer probe featuring variable measurement angles was designed. On this basis, the instrument installation scheme design, cooling air source system design, optical pyrometer calibra? tion, and turbine blade emissivity measurement were carried out. Surface temperature measurements of the low-pressure turbine rotor blades were accomplished without engine modification.when the engine was operating at intermediate state under simulated altitude condi? tions, surface temperature distributions of the trailing edge and concave side of the low pressure turbine rotor blades were acquired. The results indicate that the blade trailing edge temperature is higher than that of the blade convex side area; The highest temperature is located a bit above the mid-height of the trailing edge; There is no significant difference in temperature for each blade at the same cross-section height; As the cross-section height decreases, the cross-section average temperature gradually decreases.