高速涡轮发动机技术途径浅析  

Study on the Technical Approach of High-speed Turbine Engine

作　　者：郭帅帆 韩佳 孔祥雪 GUO Shuai-fan;HAN Jia;KONG Xiang-xue(AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《价值工程》2021年第19期133-136,共4页Value Engineering

摘　　要：高速涡轮发动机是航空动力发展的重要方向。本文从性能角度出发,结合高速涡轮发动机宽包线、高温度特征,指出其性能重点在流量,难点在温度,需要基于进气预冷和低压比设计途径,发展射流预冷、换热预冷和变循环、高流通等关键技术,为后续研究提供参考。For the development of aero-engines,high-speed turbine engine technology is very important.From the perspective of performance,this paper combines the characteristics of wider envelope and higher temperature,points out that the key to engine performance lies in mass flow rate,and the difficult point lies in temperature.Based on the technical approach of intake precooling and low pressure ratio design,key technologies such as mass injecting precooling,heat transfer precooling,variable cycle and high circulation are proposed.

关 键 词：高速涡轮发动机 进气预冷 低压比设计 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]