内并联式TBCC进气道分流板流固耦合分析  

Fluid-Structure Interaction Analysis of Shunting Plate in Over/Under TBCC Inlet

作　　者：许多[1,2] 顾瑞[1] 徐惊雷[1] 伏宇[2] 范志鹏[1] 

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]中国燃气涡轮研究院,四川成都610000

出　　处：《飞机设计》2013年第4期59-63,共5页Aircraft Design

摘　　要：TBCC内并联式进气道有共用的气流捕获进口和内压缩段,气流经过内压缩段后,再分为2路,分别流向涡轮发动机压气机和冲压发动机燃烧室,本文以内并联式TBCC进气道分流板为研究对象,研究在进口马赫数为2.5,分流板分别在0°和-3°位置时的流固耦合动态特性。为了简化计算模型,本文分流板的模型为实体模型,材料选定为45钢,不考虑重力和壁面传热的影响。仿真结果表明:(1)分流板呈现超声速颤振现象;(2)分流板位置为-3°的最大应力值较0°位置时增加了18.6倍,参考点Tip-Point y方向的最大位移增加了18.94倍。流固耦合分析可以更加真实的研究TBCC进气道分流板实际工作中的动态响应现象,为工程设计提供一定的技术参考。The airflow captured import and the internal compression section are shared in Over/ Under TBCC inlet. While going through the internal compression section, airflow divided into two part respectively, one part flowing into turbine engine compressor and the other part flowing into cramjet combustion chamber. This article takes the shunting plate in Over/Under TBCC Inlet as a research object. Researching the character of Fluid-Structure Interaction in the object while the inlet roach number is 2.5 and the position angle is 0°and -3°separately. Ignoring the effect of gravity and wall heat transfer and defining the material is 45# steel, In order to simplify the calculation model. Simulation result shows that： 1. The shunting plate present supersonic flutter phenomenon. 2. The Max-shear stress increase 18.6 times and the y direction Max-displacement increase 18.94 times, while the position of the shunting plate changing from -3°to 0°. Fluid-Structure Interaction analysis can be more real research the dynamic response phenomenon of the shunting plate. It may provide technical reference for the engineering design.

关 键 词：内并联式TBCC进气道 流固耦合 超声速颤振 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]