涡轮冲压组合发动机涡轮基改型设计研究  

Modification design of the turbine engine for a TBCC

作　　者：何敏祥 韩冬 李传鹏[2] 王德庆 朱爱迪 文强 HE Min-xiang;HAN Dong;LI Chuan-peng;WANG De-qing;ZHU Ai-di;WEN Qiang(AECC Guiyang Engine Research Institute,Guiyang 550081,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国航发贵阳发动机设计研究所,贵阳550081 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《燃气涡轮试验与研究》2022年第1期23-28,35,共7页Gas Turbine Experiment and Research

基　　金：航空发动机与燃气轮机国家科技重大专项;马赫数X级串联式冲压组合发动机技术验证。

摘　　要：基于现有涡扇发动机,按涡轮冲压组合发动机技术验证要求,开展了基于成熟涡扇发动机改涡轮基的设计研究。根据涡轮基工作性能和技术要求,分析了改型设计的难点,并开展了涡轮基控制计划设计、高空大马赫数起动设计、超声速燃烧设计、低转速接通加力设计、全权限控制系统设计、燃滑油系统设计、高空封严设计和涡轮基与冲压级匹配设计。通过整机试验验证改型后发动机满足验证平台需求,并配装冲压组合发动机平台完成关键技术验证试验。对其他发动机的改型设计具备一定的工程参考价值。According to TBCC technology validation requirements,the turbine engine modification design was carried out based on a mature turbofan engine.The difficulties in the modification design were ana⁃lyzed,and control plan design,starting in high altitude and high Mach number,supersonic combustion de⁃sign,afterburner in low speed,full authority control system design,system of fuel and lubricating oil,high altitude sealing,and turbine engine and ramjet matching design were carried out.The engine tests showed that the optimized engine met the requirements of the platform,and key technology validation tests were completed on TBCC,which provide certain reference value in engineering for other engine modification de⁃sign.

关 键 词：航空发动机 涡轮冲压组合发动机 涡轮基 控制系统 高空大马赫数起动 改型设计 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]