摘要
建立一种用于估算涡扇发动机特性的工程分析模型,该模型以涡喷发动机推力估算模型与涡扇发动机效率分析方法为基础,引入高涵道比涡扇发动机的循环分析方法进行修正。利用该模型可以获取涡扇发动机的推力和油耗特性,进而考察总体循环参数对发动机性能的影响。通过与文献验证数据对比,判定了分析模型的精度。该模型只需要输入少量参数就可以快速完成计算过程,适合于飞机总体设计阶段,可以评估涡扇发动机参数对飞机性能的影响。
An engineering model for performance estimation of turbofan engine is developed.Based on the thrust estimation model of turbojet and the efficiency analysis method of turbofan,the model is modified by working cycle analysis for the high bypass ratio turbofan.Thrust and fuel consumption characteristics of turbofan engine could be estimated with the model,and the effect of cycle parameters on engine performance is analyzed.The precision of the model is validated by the experimental data from the references.The model can complete the calculation flow quickly with a small amount of input parameters,which can be used in the aircraft conceptual design to evaluate the effect of turbofan engine parameters on aircraft performance.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2016年第3期382-388,共7页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
客机
总体设计
涡扇发动机
工程分析模型
推力
油耗
civil aircraft
conceptual design
turbofan engine
engineering model
thrust
fuel consumption
