基于地面试车数据的高涵道比涡扇发动机飞行性能预估方法

为了预估高涵道比涡扇发动机飞行性能,使用GasTurb 11软件的试车数据分析功能计算出了某高涵道比涡扇发动机地面试车点与设计点各部件效率和流路损失的偏差.通过非设计点敏感性分析确定设计点与地面试车点的效率与损失偏差的相关性,最后预估得到高涵道比涡扇发动机的飞行性能.对某高涵道比涡扇发动机飞行性能预估研究表明:该方法切实可行,其中地面试车数据分析、地面和设计点偏差关系图、以及非设计敏感性分析是预估高涵道比涡扇发动机飞行性能的3个关键环节。

Method of flight performance prediction of high bypass ratio turbofan engine based on ground test data

In order to predict the flight performance of a high bypass ratio turbofan engine. Errors of component efficiencies and pressure losses of a high bypass ratio turbofan engine at ground test point and design point were estimated by using GasTurb 11 software. And then the relationships of the errors between design point and ground test point were determined through the non-design point sensitivity analysis method. In terms of the above relationships determined, the flight performance of the high bypass ratio turbofan engine can be predicted at last. Prediction of the flight performance of a high bypass ratio engine shows that the method is feasible, analysis of ground test data, relationships of delta value of ground point and design point and the non-design point sensitivity analysis are three key links in predicting the flight performance of high bypass ratio turbofan engines.