国外TBCC发动机进气道设计和试验研究综述  

Design and experimental development overview of foreign TBCC inlet technology

作　　者：李茜 桂丰 LI Qian;GUI Feng(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院

出　　处：《燃气涡轮试验与研究》2019年第3期58-62,共5页Gas Turbine Experiment and Research

摘　　要：跟踪研究了国外涡轮基组合循环(TBCC)发动机进气道技术的发展和应用现状,列举了典型的进气道设计方案,总结了TBCC发动机进气道的关键技术,如模态转换技术、不同工作模式匹配技术、流场控制技术以及一体化技术。TBCC发动机进气道需开展大量试验研究以突破技术瓶颈,国外针对性地开展了相关试验,并取得一定成果。二元可调进气道和三维内转式进气道,是TBCC发动机进气道的主要发展方向。The development and application of foreign turbine based combined cycle (TBCC) engine inlet technologies were studied.Several typical inlet concepts were discussed.On this basis,critical technologies of TBCC inlet were summarized as mode transition technology,different operation mode matching technolo gy,flow filed control technology and integration technology.It is necessary to carry out many tests to solve the technology challenges of TBCC inlet.Several tests have been carried out and obtained some achieve ments.Results show that two dimensional variable geometry inlets and three dimensional inward inlets are the main development directions of TBCC inlet.

关 键 词：航空发动机 TBCC 二元进气道 三维内转式进气道 模态转换 一体化技术 试验设备 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]