主元分析在航空发动机关键系统状态识别中的应用

航空发动机是飞机的心脏,因此,对其状态识别进行研究,一直是业界研究并试图解决的热点问题之一。本文以某型真实发动机气路系统为具体研究对象,通过在专业试验平台对其各种运行状态进行试验,采集其大量试验数据,在对其深入分析的基础上,提出采用高压转子相对物理转速、发动机进口温度、发动机进口压力、压气机出口压力、25截面压气机进口温度、低压转子相对物理转速、低压涡轮后温度、低压涡轮后压力等8个主要参数进行状态识别的方法,首先对其进行标准化处理,再对其进行主元分析,采用主元贡献率法计算出主元个数,并据此构建状态识别模型,确定 统计量和SPE统计量。并以确定的 统计量和SPE统计量作为航空发动机气路系统状态健康与异常识别的标志,对航空发动机气路系统健康与否进行识别研究,研究结果表明,该方法可以很好识别出航空发动机气路系统的运行状态,对航空发动机实际运行及所处状态的识别具有重要的使用价值与工程指导意义。

The application of PCA on the status recognition of aero engine key system

The aviation engine is the heart of the airplane. Therefore, the research for its status recognition has been one of the hot issues which the industry studies attempts to solve. The paper take a real engine gas path system as the research object. The research collects a large number of test data through the test of the running condition in the professional test platform. And based on in-depth analysis for the large test data, the paper proposes to use the 8 main parameters for state recognition. The 8 main parameters contain the relative physical rotational speed of high pressure rotor, inlet temperature of aero engine, inlet pressure of aero engine, outlet pressure of compressor, 25 section of compressor inlet temperature, low pressure rotor speed, low relative temperature after turbine, low pressure turbine pressure etc. Firstly, the paper has been standardized treatment for these data. Second, the paper has been the principal component analysis, and this can calculate the number of principal components through the principal component contribution. Therefore, this can construct a state the recognition model, and can determine. Lastly, the paper takes the statistics of and statistics of SPE as the sign for the aero engine gas path system health status and anomaly recognition. So the paper uses the statistic of and statistic of SPE to finish the research of the aero engine gas path system health and no identification. The study result shows that the method can well identify the running state of the aero engine gas path system. And this method has important value and engineering guidance significance for the actual operation of the aero engine and the recognition of the state.