采用拓展中心线、不同的流通截面面积变化规律和倒圆半径变化规律对内并联型TBCC（turbine based combined cycle engine）进气道涡轮通道扩张段进行了设计．通过数值模拟的手段，对涡轮通道扩张段设计参数的影响规律和涡轮模态下涡轮...采用拓展中心线、不同的流通截面面积变化规律和倒圆半径变化规律对内并联型TBCC（turbine based combined cycle engine）进气道涡轮通道扩张段进行了设计．通过数值模拟的手段，对涡轮通道扩张段设计参数的影响规律和涡轮模态下涡轮通道扩张段的气动特性进行了研究，并利用高速风洞试验结果对数值模拟方法进行了验证．研究结果表明：中心线控制点纵坐标在1．50～2．25、涡轮通道扩张段出口等直段长度与出口直径比值在0．3～0．7的范围内取值时，涡轮通道扩张段可获得较高的出口总压恢复系数和较小的出口总压畸变指数；采用前急后缓的流通截面面积和倒圆半径变化规律能使涡轮通道扩张段获得较小的出口总压畸变指数；随着飞行马赫数的增加，进气道和涡轮通道扩张段的流量系数先不断减小，在飞行马赫数为0．9附近达到最小，之后又逐渐增加，涡轮通道扩张段出口总压恢复系数不断升高，在飞行马赫数为0．7附近达到最大，之后又逐渐降低；涡轮模态下，涡轮通道扩张段出口总压畸变指数均小于0．5，能很好地满足涡轮发动机对进口流场的要求．展开更多
Airbreathing aero-engines are regarded as excellent propulsion devices from ground takeoff to hypersonic flight,and require control systems to ensure their efficient and safe operation.Therefore,the present paper aims...Airbreathing aero-engines are regarded as excellent propulsion devices from ground takeoff to hypersonic flight,and require control systems to ensure their efficient and safe operation.Therefore,the present paper aims to provide a summary report of recent research progress on airbreathing aero-engine control to help researchers working on this topic.First,five control problems of airbreathing aero-engines are classified:uncertainty problem,multiobjective and multivariable control,fault-tolerant control,distributed control system,and airframe/propulsion integrated control system.Subsequently,the research progress of aircraft gas turbine engine modelling,linear control,nonlinear control,and intelligent control is reviewed,and the advantages and disadvantages of various advanced control algorithms in aircraft gas turbine engines is discussed.Third,several typical hypersonic flight tests are investigated,and the modelling and control issues of dual-mode scramjet are examined.Fourth,modelling,mode transition control and thrust pinch control for turbine-based combined cycle engines are introduced.Followed,significant hypersonic airframe/propulsion integrated system control is analysed.Finally,the study provides specific control research topics that require attention on airbreathing aero-engines.展开更多
文摘采用拓展中心线、不同的流通截面面积变化规律和倒圆半径变化规律对内并联型TBCC（turbine based combined cycle engine）进气道涡轮通道扩张段进行了设计．通过数值模拟的手段，对涡轮通道扩张段设计参数的影响规律和涡轮模态下涡轮通道扩张段的气动特性进行了研究，并利用高速风洞试验结果对数值模拟方法进行了验证．研究结果表明：中心线控制点纵坐标在1．50～2．25、涡轮通道扩张段出口等直段长度与出口直径比值在0．3～0．7的范围内取值时，涡轮通道扩张段可获得较高的出口总压恢复系数和较小的出口总压畸变指数；采用前急后缓的流通截面面积和倒圆半径变化规律能使涡轮通道扩张段获得较小的出口总压畸变指数；随着飞行马赫数的增加，进气道和涡轮通道扩张段的流量系数先不断减小，在飞行马赫数为0．9附近达到最小，之后又逐渐增加，涡轮通道扩张段出口总压恢复系数不断升高，在飞行马赫数为0．7附近达到最大，之后又逐渐降低；涡轮模态下，涡轮通道扩张段出口总压畸变指数均小于0．5，能很好地满足涡轮发动机对进口流场的要求．
基金This research work is supported by the National Science and Technology Major Project(2017-V-0004-0054)the National Natural Science Foundation of China(Grant No.52125603)+1 种基金the National Natural Science Foundation of China(Grant No.11972139)the Fundamental Research Funds for the Central Universities(HIT.BRET.2021006 and FRFCU5710094620).
文摘Airbreathing aero-engines are regarded as excellent propulsion devices from ground takeoff to hypersonic flight,and require control systems to ensure their efficient and safe operation.Therefore,the present paper aims to provide a summary report of recent research progress on airbreathing aero-engine control to help researchers working on this topic.First,five control problems of airbreathing aero-engines are classified:uncertainty problem,multiobjective and multivariable control,fault-tolerant control,distributed control system,and airframe/propulsion integrated control system.Subsequently,the research progress of aircraft gas turbine engine modelling,linear control,nonlinear control,and intelligent control is reviewed,and the advantages and disadvantages of various advanced control algorithms in aircraft gas turbine engines is discussed.Third,several typical hypersonic flight tests are investigated,and the modelling and control issues of dual-mode scramjet are examined.Fourth,modelling,mode transition control and thrust pinch control for turbine-based combined cycle engines are introduced.Followed,significant hypersonic airframe/propulsion integrated system control is analysed.Finally,the study provides specific control research topics that require attention on airbreathing aero-engines.
