旅客机／涡扇发动机设计参数一体化选择研究  

INVESTIGATION OF INTEGRATED SELECTION FOR PASSENGER PLANE/TURBOFAN ENGINES DESIGN PARAMETERS

作　　者：胡军[1] 张津[1] 

机构地区：[1]北京航空航天大学动力系

出　　处：《北京航空航天大学学报》1996年第2期183-188,共6页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：依据旅客机的典型飞行剖面、适航性以及国际民航组织的规范，建立了旅客机／涡轮风扇发动机设计参数一体化选择的计算方法和程序．此方法按照旅客机的商载、航程等营运需求，以满足飞行任务条件下经济性最好为目标，优选飞机的起飞推重比、翼载以及发动机循环参数等．对选出的旅客机／发动机方案，可对其航线飞行性能进行模拟，计算轮挡燃油、轮挡时间以及一发失效的升限．本方法和程序可用于民用涡轮风扇发动机的方案设计和性能分析，也可作为航空公司选购飞机和发动机时的一种分析评价工具．on the basis of typical passenger plane flight profiles. airworthiness and the regulationsof ICAO, a method and program were developed for the integrated selection of the passengerplane/turbofan engine design parameters in the paper. The optimization of airplane thrust-toweight ratio, wing load and engine cycle parameters can be performed to aim at the best economics in consideration of the requirements of payload. range and flight mission etc. For candidate airplane/engine concepts. the engine performance and weight. and airplane performance on airlines such as block fuel, block time and ceiling when one engine failure can besimulated. They will be used to concept desigh and performance analysis of civil turbofan engines. They are also useful assessment tools for airlines to choose and purchase passengerplane and their engines.

关 键 词：透平风扇发动机 旅客机 一体化设计 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]