一种内转式TBCC进气道气动设计及分析  

Areodynamic Design and Analysis of a TBCC Inlet Based on Inward-turning Inlet

作　　者：何墨凡 李宪开[1] 尹超 徐倩楠 袁化成[3] HE Mofan;LI Xiankai;YIN Chao;XU Qiannan;YUAN Huacheng(Yangzhou Academy of Collaboration&Innovation Co.,Ltd.,Yangzhou 225002,China;Sichuan Gas Turbine Establishment,Mianyang 621700,China;Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]沈阳飞机设计研究所扬州协同创新研究院,江苏扬州225002 [2]四川燃气涡轮研究院,四川绵阳621700 [3]南京航空航天大学,江苏南京210016

出　　处：《飞机设计》2021年第4期56-64,73,共10页Aircraft Design

摘　　要：提出了一种基于内转式进气道利用二元楔板转动的TBCC进气道可调设计方法及方案,进气道采用平动式模态转换装置,并对其不同来流马赫数及模态转换过程的气动特性开展了三维数值模拟分析,同时探究了进气道方转圆扩张段典型参数对进气道性能影响。结果显示:给出的可调进气道变几何方案解决了高马赫数气动性能与低马赫数起动性能的兼容问题,平动式模态转换装置保证了涡轮通道与冲压通道流量的线性过渡,方转圆段面积变化规律对本文进气道性能影响较小,中心线变化规律对进气道性能影响较大,其中对出口畸变影响显著。该方案有很好的工程实现性,本研究可为此类内转式TBCC可调进气道研制提供参考。An adjustable TBCC inlet based on the inward-turning inlet with the use of the dual wedge rotation was proposed.The inlet was equipped with the translational mode conversion device.The 3d numerical simulation analysis of the aerodynamic characteristics of different inlet Mach Numbers and mode conversion process was carried out,and explores the inlet side turn round expansion period of typical parameters influence on the inlet performance.The results show that the adjustable inlet variable geometry scheme can solve the compatibility problem between high Mach number aerodynamic performance and low Mach number starting performance.Translational mode conversion device to ensure the turbine passage and stamping linear transition of channel flow,side turn round section area of change law of inlet performance is affected in this paper,the center line of the change rule of greater influence on the inlet performance,which significantly influence on export of distor tion. The scheme has good engineering realization. This study can provide reference for the development of such inward-turning adjustable inlet.

关 键 词：TBCC进气道 内转式进气道 模态转换 数值模拟 

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]