三维并联式TBCC发动机排气系统设计与实验  

Design approach and experiment of three-dimensional over/under TBCC exhaust system

作　　者：花文达 徐惊雷 HUA Wenda;XU Jinglei(Jiangsu Province Key Laboratory of Aerospace Power College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing System,210016,China)

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016

出　　处：《航空动力学报》2018年第9期2268-2277,共10页Journal of Aerospace Power

基　　金：基础科研重点项目(XX20132002);四川燃气涡轮研究院项目(XX-2006-14)

摘　　要：为实现三维并联式TBCC排气系统的设计,利用基于二维最大推力理论的密切法设计了圆转矩变截面非对称冲压发动机喷管,并在冲压发动机喷管上壁面为三维曲面的条件下,利用转动加滑动共用面的调节方式实现了涡喷发动机喷管的内型面设计及其喉道面积的调节,从而完成了排气系统设计。随后对设计结果进行了冷流实验验证。结果表明,这种排气系统设计方法具有可行性。在冲压单独工作状态,壁面压力分布的数值计算与实验结果吻合较好,相对方均根偏差低于10.8%;在涡喷单独工作状态及共同工作状态,上壁面压力在激波附面层干扰区域内偏差较大,最大相对偏差可达30.6%。但壁面压力分布的数值计算与实验结果的整体变化趋势一致。To design a three-dimensional turbine based combined cycle（TBCC）exhaust system,a design approach was presented.It employed osculating method based on flowfield of nozzle with optimum thrust to design a three-dimensional section controllable dissymmetric ramjet nozzle.And on the basis of curved ramjet flowpath,a new scheme of rotating and sliding the shared surface was proposed to regulate the throat area of the turbojet nozzle.Cold flow experiments and numerical simulations were conducted at typical test points.The comparison proved that the design approach of TBCC exhaust system is practicable.Under the ramjet mode,the comparison of static pressure distributions showed agreement and the relative root mean square error was less than 10.8%.Under the other modes,obvious deviations appeared in the area where the shock wave interacted with the boundary layer,the maximum relative error was 30.6%.However,the variation tendencies of the static pressuredistributions were consistent.

关 键 词：涡轮基组合循环(TBCC) 三维排气系统 喷管设计 喉道调节 冷流实验 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]