超声速高温燃气温度探针速度误差标定试验研究  

Calibration test of supersonic high temperature gas temperature probe velocity error

作　　者：林音 唐永涛 钟欣 LIN Yin;TANG Yongtao;ZHONG Xin(AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China)

机构地区：[1]中国航发四川燃气涡轮研究院,四川绵阳621000

出　　处：《燃气涡轮试验与研究》2023年第6期50-54,共5页Gas Turbine Experiment and Research

摘　　要：针对航空发动机喷管出口温度场测试问题,研制了大跨度多测点超声速高温燃气温度探针。在亚跨超声速风洞上开展了速度误差标定试验,获得了屏蔽式温度探针和裸露式温度探针在马赫数0.3~2.0范围内的恢复系数以及速度误差。标定试验结果表明,屏蔽式温度探针的恢复系数很高,速度误差很小;裸露式温度探针速度误差略大,需要进行修正计算。基于标定试验结果,给出了裸露式温度探针速度误差修正计算方法。In order to solve the problem of temperature field measurement at the outlet of aero-engine nozzle,a long-span,multi-point supersonic and high temperature probe was developed.The velocity error calibration test was carried out on a subsonic transonic wind tunnel.Recovery coefficient and velocity error of shielded temperature probe and bare temperature probe in the range of Mach number 0.3~2.0 was obtained.The calibration test results show that the shielded temperature probe has high recovery coefficient and small velocity error.The velocity error of the bare temperature probe is slightly larger,so the correction calculation is necessary.Based on the calibration test results,the correction calculation method of velocity error of bare temperature probe was presented.

关 键 词：航空发动机 喷管 超声速 温度探针 速度误差 恢复系数 标定试验 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]