轴驱动升力风扇发动机稳态性能仿真模型研究  

Steady performance mathematical model of a turbofan engine with the shaft-driven lift-fan

作　　者：杨磊 杨大军 姜楠 白磊 YANG Lei;YANG Da-jun;JIANG Nan;BAI Lei(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China;Aero Engine Corporation of China,Beijing 100097,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500 [2]中国航空发动机集团有限公司,北京100097

出　　处：《燃气涡轮试验与研究》2018年第3期1-4,共4页Gas Turbine Experiment and Research

基　　金：航空科学基金(2014ZB24008)

摘　　要：以常规混排涡扇发动机性能模型为基础,结合升力系统工作原理,并以推力比为控制目标,建立了轴驱动升力风扇发动机稳态性能仿真数学模型。根据此模型编制了轴驱动升力风扇发动机整机稳态性能计算软件,并以轴驱动升力风扇发动机的三种工作状态为例进行了计算分析。结果表明,该模型软件逻辑正确,计算精度满足后续研究需要,为轴驱动升力风扇发动机性能分析及控制规律研究提供了必要的技术基础。Based on a conventional turbofan steady performance mathematical model, and combined withthe working principle of the lifting system, steady performance mathematical model of a turbofan enginewith the shaft-driven lift-fan was built with thrust ratio as a control target. According to this model, steadyperformance simulation software was compiled and calculation analysis was carried out on three typicalworking conditions. The calculation findings suggest that the procedure of the software is logically accurate,and the precision of the calculation will satisfy the further research. It provides the foundation for the perfor-mance analysis and control law design of shaft-driven lift-fan turbofan.

关 键 词：航空发动机 升力系统 垂直起降 数学模型 F-35B F135-PW-600 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]