桨扇发动机推进效率分析方法研究  

Research on analysis method of propulsive efficiency of prop-fan engine

作　　者：黄兴 李伟 杨宇飞 郑华雷 HUANG Xing;LI Wei;YANG Yufei;ZHENG Hualei(General Research Department on Future Propulsion Technology,AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China)

机构地区：[1]中国航发湖南动力机械研究所未来动力总体研究部,株洲412002

出　　处：《航空工程进展》2024年第4期50-55,共6页Advances in Aeronautical Science and Engineering

基　　金：两机国家重大专项。

摘　　要：评估涡扇、涡桨、桨扇发动机的推进效率对中高飞行马赫数下桨扇发动机具有重要意义。基于分开排气涡扇发动机模式,采用能量—动量方法推导、建立推进效率分析的数学模型,形成涡桨、涡扇及桨扇发动机统一的推进效率分析方法;选取不同外涵风扇压比、等效涵道比及不同飞行马赫数开展计算。结果表明:在中低飞行马赫数下涡桨发动机推进效率较高,在中高飞行马赫数下桨扇发动机推进效率较高,在高亚声速飞行马赫数下涡扇发动机推进效率较高,印证了现有的涡桨、桨扇及涡扇发动机优势推进效率的飞行马赫数区间分布规律,为涡扇、涡桨、桨扇发动机推进效率研究分析提供了方法。It is of great significant for prop-fan engine under medium to high Mach number to evaluate the propulsive efficiency of turbofan,turboprop and prop-fan engines.The mathematical model for propulsive efficiency analysis is established by using energy-momentum method based on the model of separate exhaust turbofan engines,and a unified propulsive efficiency analysis method is formed for turbofan,prop-fan and propeller fan engines.Different external fan pressure ratios,equivalent bypass ratios and different flight Mach number are selected for calculation.The results show that the propulsion efficiency of turboprop engine is higher at medium to low flight Mach number,the propulsion efficiency of prop-fan engine is higher at medium to high flight Mach number,and the propulsion efficiency of turbofan engine is higher at high subsonic flight Mach number.The existing flight Mach number interval distribution law of the superior propulsion efficiency of turboprop,prop-fan and turbofan engines is conformed.The study can provide a method for the research and analysis of the propulsion efficiency of turbofan,turboprop and prop-fan engines.

关 键 词：桨扇发动机 涵道比 推进效率 数学模型 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]