摘要
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。
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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第8期1773-1777,共5页
Journal of Aerospace Power
关键词
高涵道比涡扇发动机
飞行性能预估
试车数据分析
非设计点敏感性分析
设计点性能
high bypass ratio turbofan ground test data analysis
design point performance engine
flight performance prediction non-design point sensitivity analysis
