基于GasTurb的涡扇发动机不同状态下总体特性研究  

Research on the Overall Characteristics of the Turbofan Engine Under Different Conditions Based on GasTurb

作　　者：赵振兴 薛园园 潘信予 赵运生 左松宸 ZHAO Zhenxing;XUE Yuanyuan;PAN Xinyu;ZHAO Yunsheng;ZUO Songchen(Taicang Techstone Aerospace Power Co.Ltd,Suzhou 215400,China;National Innovation Institute of Defense Technology,Academy of Military Sciences,Beijing 100071,China)

机构地区：[1]太仓点石航空动力有限公司,江苏苏州215400 [2]中国人民解放军军事科学院国防科技创新研究院,北京100071

出　　处：《飞机设计》2024年第6期18-24,共7页Aircraft Design

摘　　要：涡扇发动机因其具有高燃油经济性、低噪音及低维护成本等优点,广泛应用于航空交通领域。文中基于GasTurb软件对典型涡扇发动机不同状态进行了总体特性研究,分析了飞行马赫数、飞行高度、发动机涵道比、发动机燃烧室后温度等,对发动机推力性能、效率变化和压比情况的影响。结果显示:飞行高度越高、飞行马赫数越低,燃烧室后温度越高将导致燃烧室的温增比增大;增加飞行马赫数、降低飞行高度、提高发动机涵道比、提高燃烧室后温度对发动机总体性能有利。对于优化涡扇发动机的设计和应用具有重要的指导意义。The turbofan engine is widely used in the field of aviation transportation due to its advantages of high fuel economy,low noise,and low maintenance costs.Based on GasTurb software,this article conducts an overall characteristic study on different states of a typical turbofan engine,analyzing the effects of flight speed,f light altitude,engine bypass ratio,and temperature behind the engine combustion chamber on the engine thrust performance,efficiency changes,and pressure ratio.The results show that as flight altitude increases and flight speed decreases,the higher temperature behind the combustion chamber will lead to an increase in the temperature increase ratio of the combustion chamber.Increasing flight speed,reducing flight altitude,increasing the engine bypass ratio,and increasing the temperature behind the combustion chamber are all beneficial to the overall performance of the engine.These findings have important guiding significance for optimizing the design and application of turbofan engines.

关 键 词：GasTurb 气动性能 涡扇发动机 总体特性 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]