摘要
为了解某型发动机整机运行状态下低压涡轮工作叶片的温度分布情况,使用红外测试系统测量了该发动机整机状态低压涡轮工作叶片前缘及盆侧的温度场。试验前对该发动机进行了测试改装,设计了用于实现叶片定位的转速信号分析仪,以及用于提供高压气源的气体增压系统。试验共测得多个状态下发动机涡轮叶片的表面温度分布数据。结果表明:涡轮叶片前缘和叶盆中间位置的温度较高;相同位置下每片叶片的温度有轻微差异;叶片的最高温度位置位于测试区域的下方,与仿真计算结果相吻合。采用红外测温技术可以得到清晰的涡轮叶片表面温度分布云图,结合示温漆标记技术,可用于定位温度最高的叶片和叶片温度最高的位置。
To know the temperature distribution of the low pressure turbine blade under the real engine working condition. Using the infrared pyrometer system, the temperature distribution of the leading edge of the engine low pressure turbine blade was measured. The instrument modification of the engine began before the experiment; the instrument to identify the blade position using the engine speed signal was designed, at the same time a set of gas pressurization system was designed to provide a high pressure air source. The temperature distribution of the turbine blade was obtained under multiple engine working condition. The data shows that the leading edge and basin of blade temperature are higher than other area; the distributions of blades temperature are different at the same position; the maximum temperature of the blade is located at the bottom of the test area, which is consistent with the simulation results. The temperature distribution of blade can be obtained, using the infrared technology combined with the thermal index paint, the maximum temperature blade and the maximum temperature position of blade can be found.
出处
《航空发动机》
北大核心
2018年第1期75-78,共4页
Aeroengine
基金
航空动力基础研究项目资助
关键词
航空发动机
涡轮叶片
红外测温
温度场测量
Infrared radiation pyrometer
Aeroengine
Turbine blade
Measurement of temperature profile
