民用航空涡扇发动机性能试飞压力测试系统研究与实现

Turbofan Engines Performance Flight Test Pressure Measurement System Development

民用航空涡扇发动机性能试飞是发动机试飞科目中最重要的试飞项目,该试飞科目要测量的发动机参数非常多,测量精度要求高,尤其是压力测量。而发动机特殊的工况、外部环境条件以及发动机短舱内局限的安装空间,都对传感器、信号调理和数据采集提出了很高的要求。从系统软硬件组成,工作原理,接口设计等方面介绍了基于电子压力扫描系统的某民用涡扇发动机压力测试系统。该测试系统具有小型化、测试集成化、安装方便、测量准确、测试效率高、系统校准方便等特点,有效地实现了高精度大规模压力参数测量和采集,并且该系统引入了国际通用的拖锥装置,有效地保证了大气静压测量的准确性。

Aircraft Turbofan Engines Performance Flight Test is the most important flight test item, there are many parameters need to be measured, the accuracy requirements are very high, especially the pressure measurement. The working conditions of the engine, the ambient environment and the nacelle installation space, these all have high requirements for the sensors, signal conditioning and data acquisition equipments. This paper introduces the performance flight test pressure measurement system from the hardware, interface, and principle. This system realizes the high accuracy and a great numbers parameter measurement and data acquisition. This system have the trailing cone which guarantees the accuracy of the measurement.