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发动机性能飞行试验中,关键因素之一是确定发动机进口空气流量。考虑到发动机空中性能确定是一个非常复杂的过程,在飞行试验中,应准备多种方案互为备份,以防止某一特定方案由于若干测量参数失效而无法使用。所以,本文参考和改进了应用于国外某大涵道比发动机的高压涡轮导向器喉道截面流量函数计算法,根据地面台架校准试验,获取基于小涵道比涡扇发动机的高压涡轮导向器喉道无量纲组合参数,将其应用到飞行试验中,利用能量守恒和流量守恒,即可得到发动机进口空气流量。计算结果显示,与Gasturb软件计算结果吻合度高。最后,进行了参数敏感性分析,确定出试验中测量需求精度高的参数,这对小涵道比发动机试飞以及性能确定有很重要的意义。
Engine Performance Flight tests, one of the key factors is to determine the engine inlet air flow. Taking into account the determination of engine air performance is a very complex process in which flight tests should be prepared in such a way that multiple solutions are backed up each other to prevent a particular solution from being unavailable due to failure of several measurement parameters. Therefore, this paper references and improves the throat cross-section flow function calculation method of high-pressure turbine governor applied to a large bypass ratio engine in foreign countries. According to the ground bench calibration test, the high-pressure turbine guider based on small bypass ratio turbofan engine Throat dimensionless combination of parameters, its application to the flight test, the use of conservation of energy and flow conservation, you can get the engine inlet air flow. The calculation results show that the calculated results are in good agreement with Gasturb software. Finally, the parameter sensitivity analysis was carried out to determine the parameters of high precision measurement requirements in the experiment, which is of great significance to the flight test and performance determination of the small bypass ratio engine.