摘要
为了提高小型涡喷发动机的综合性能,用全三维气动设计方法对其压气机和涡轮进行了重新设计,使压气机和涡轮的性能得到较大幅度的改善。压气机的增压比、绝热效率和空气流量分别提高15.1%,3.8%,3.9%,气动稳定性边界向左上方大幅度扩大。三级轴流压气机的级平均增压比从原来的1.56提高到1.64,涡轮的绝热效率提高了1.5%。发动机整机性能试验表明,在最大转速下发动机的最大推力增加幅度达16.58%,燃油消耗率最大降低幅度达21%。
In order to improve the performance of a small turbo-jet engine,a three-stage axial compressor and a single stage axial turbine of the engine were redesigned with 3D aerodynamic method.The aerodynamic performances of both compressor and turbine were substantially improved.The pressure ratio,adiabatic efficiency and mass flow of the compressor were increased,respectively,by 15.1%,3.8%,3.9%.The surge borderline was moved toward up and left in a great pace.The mean pressure ratio of three stage axial compressor was increased from 1.56 to 1.64.The adiabatic efficiency of the turbine was increased by 1.5%.The experiment data of the engine show that the thrust of the engine was increased by 16.58%,and specific fuel consumption was decreased by 21% at the maximum speed of the engine.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2013年第3期326-331,共6页
Journal of Propulsion Technology
关键词
涡轮喷气发动机
性能
改进
Turbojet engine
Performance
Improvement
