一种复合冷却双层探针的设计与验证  

Design and verification of a double-layer probe with composite cooling

作　　者：杨华 陈鹏飞 杨斐 陈伟[2] 何培垒 YANG Hua;CHEN Pengfei;YANG Fei;CHEN Wei;HE Peilei(AECC Sichuan Gas Turbine Establishment,Mianyang 621010,China;Sichuan University,Chengdu 610065,China)

机构地区：[1]中国航发四川燃气涡轮研究院,四川绵阳621000 [2]四川大学,成都610065

出　　处：《燃气涡轮试验与研究》2023年第6期42-49,共8页Gas Turbine Experiment and Research

基　　金：国家财政稳定支持专项(GJCZ-0030-19)。

摘　　要：基于CCD相机的侵入式视觉成像温度场测量技术,设计了一种水和氮气复合冷却的双层探针。对探针外部气动特性和内部结构强度进行了仿真优化设计,验证了探针结构强度和冷却效果满足使用需求;同时,采用比色测温法,将喷流场图像转化为实时温度场,提出了基于温度场先验概率信息的尾喷口识别技术,剔除了环境光影响,提高了测量精度和显示效果。整机试验验证表明,所设计的探针能够监测发动机喷流场,实时高效地测量发动机尾焰温度,为航空发动机整机试验温度场测量提供了技术支持。Based on the invasive visual imaging temperature field measurement technology of CCD camera,a double-layer probe cooled by water and nitrogen was designed.The external aerodynamic characteristics and internal structural strength of the probe were simulated and optimized to verify the structural strength of the probe,and Colorimetric temperature measurement method was used to convert the image of jet field into a real-time temperature field.A nozzle recognition technique based on prior probability information of temperature field was proposed,which eliminated the influence of ambient light and improved the measurement accuracy and display effect.The whole engine test proved that this scheme could monitor the engine jet field and measure the engine tail flame temperature in real time and efficiently,which provided technical support for the temperature field measurement of the whole engine test.

关 键 词：航空发动机试验 温度场测量 结构仿真 比色测温法 图像处理 

分 类 号：V263.3[航空宇航科学与技术—航空宇航制造工程]