一种TBCC进气道涡轮通道抽吸方案设计  

Bleed system design for the turbine duct of a TBCC inlet

作　　者：章欣涛 袁化成[1] 卢杰 王颖昕[3] 伊戈玲 ZHANG Xintao;YUAN Huacheng;LU Jie;WANG Yingxi;YI Geling(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AVIC Jiangxi Hongdu Aviation Industry Group Company Ltd,Nanchang 330024,China;China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]江苏省航空动力系统重点实验室,南京航空航天大学能源与动力学院,南京210016 [2]江西洪都航空工业集团,南昌330024 [3]中国运载火箭技术研究院研究发展中心,北京100076

出　　处：《固体火箭技术》2020年第2期250-258,共9页Journal of Solid Rocket Technology

基　　金：国家自然科学基金资助项目(11772155);中国航天科技集团公司航天科技创新基金资助项目;中国航发四川燃气涡轮研究院外委课题。

摘　　要：对一种组合发动机进气道模态转换设计马赫数下的流动进行了数值模拟,研究了涡轮通道不同区域抽吸对进气道气动性能的影响,对比了外压段不同区域及内压段不同区域抽吸对进气道性能的影响,通过设计不同抽吸方案对比了外压段抽吸及内压段抽吸对进气道气动性能的影响,根据分析结果确定了以外压段为主,内压段为辅的抽吸思路,并选取不同组合方式对比,确定了最优的抽吸方案,以此方案为基础研究了模态转换过程中抽吸对进气道的影响规律。结果表明:在进气道外压段、内压段单独抽吸均可不同程度地改善进气道的起动性能;内、外压区域同时抽吸,随抽吸流量率减小,总压恢复与流量系数乘积增大;涡轮通道抽吸对改善进气道模态转换结束状态起动性能的帮助不大。The 2?D flow field in an inlet of combined engine with suction at different positions was numerically analyzed.The flow characteristics in the low duct at different suction positions were compared and discussed.The effects of suction region at exter?nal compression and internal compression were studied.A comparison of suction at external compression and internal compression was conducted by designing different suction cases.According to the results,different cases for mode transition process were de?signed to screen the best suction method.The results show that the suction in internal and external compression section can improve the performances of the inlet to different extent.With the decrease of the suction flow coefficient in both suction area,the product of the total pressure recovery and the mass flow rate increased.The suction in turbine duct has no obvious impact on the start perform?ance of the ending condition in the mode transition.

关 键 词：涡轮基组合循环 进气道 进气道起动 抽吸 气动性能 数值仿真 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]