模拟Scramjet隔离段实际入口的直连试验设备设计试验验证  

Experimental Validation of Direct-Connect Wind-Tunnel Facility Design for Simulating Real Inflow in a Scramjet Isolator

作　　者：唐兰[1] 徐惊雷[1] 俞凯凯[1] 曹学斌[2] 满延进[2] TANG Lan XU Jing-lei YU Kai-kai CAO Xue-bin MAN Yan-jin(College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China Science and Technology on Scramjet Laboratory, Beijing Power Machinery Institute, Beijing 100074, China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]北京动力机械研究所高超声速冲压发动机技术重点实验室,北京100074

出　　处：《推进技术》2016年第10期1970-1976,共7页Journal of Propulsion Technology

基　　金：高超声速冲压发动机技术重点实验室开放基金(20120102007)

摘　　要：为了模拟进气道喉道非均匀流场对超燃冲压发动机隔离段流动特性的影响,针对典型超燃冲压发动机隔离段入口流场的马赫数分布要求,设计了隔离段直连试验设备。该设备整个通道采用扩张构型,在附面层发展段的下壁面采用加圆形凸台的方法加速附面层发展,并针对该设备进行了数值模拟和冷流试验。结果表明,该直连试验设备不仅能准确模拟隔离段实际入口流场(即入射激波和非对称附面层),模拟的主流区马赫数与目标值差值在0.02以内,还解决了传统的直连试验设备存在的启动问题。试验与数值模拟结果吻合较好,验证了该直连试验设备设计方法的可行性。In order to investigate the effects of nonuniform flow at inlet throat on the flow characteristics of isolators,a direct-connect wind-tunnel facility was designed according to the Ma distribution of typical scramjet isolator inlet. The direct-connect wind-tunnel facilities was divergent,and some cylindrical bumps were placed on the lower wall of boundary layer developed section to accelerate development of boundary layer. Finally,coldflow test and numerical simulation were conducted. The results show that this direct-connect wind-tunnel facility not only can simulate the real inflow（including the lip shock wave and asymmetric boundary layer） in a scramjet isolator,the difference of Mach number in main flow between simulation and target is within 0.02,but also can avoid the starting problem in the traditional direct-connect wind-tunnel facility. Results of cold-flow test and numerical simulation agree well with each other,which confirms that the design method of direct-connect windtunnel facility is fully verified.

关 键 词：超燃冲压发动机 隔离段直连试验 附面层 非均匀 激波 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]