摘要
为了研究涡轮基组合循环发动机的安装性能,基于美国Georgia大学工程技术研究中心提出的HSF高速飞行器,选择并联式涡扇-冲压组合发动机方案作为研究对象。采用数值模拟方法,研究了并联式涡扇-冲压组合发动机的工作模式转换点的确定方法,以及模式转换过程中气动参数变化和几何调节规律,建立了适用于并联式涡轮基组合发动机的进排气系统安装损失计算模型及安装性能计算模型。研究表明,通过几何和发动机供油规律调节,可保证在推力连续的准则下完成工作模式转换,发动机的安装性能满足飞行器的要求。
To investigate the installed performance of turbine based combined cycle engines,based on Hypersonic Strike Fighter proposed by Georgia Institute of Technology,parallel configuration was selected as a turbofan-ram combined engine.The work process and the determination of transition mode point of turbo-ramjet were described.The installed loss computational model and installed performance computational model were established.The installed performance characteristics of turbo-ramjet were simulated by numerical method.The investigation indicates that the engine installed performance can meet the requirement of aircraft.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2011年第3期312-317,322,共7页
Journal of Propulsion Technology
关键词
涡轮冲压组合发动机
模式转换
安装性能
数值仿真
Turbo-ramjet combined cycle engine
Mode transition
Installed performance
Numerical simulation
