Unsteady flow characteristic analysis of turbine based combined cycle (TBCC) inlet mode transition

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• 作者：Jun Liu^a ; ^b ; Huacheng Yuan^a ; ^{yuanhuacheng@nuaa.edu.cn" class="auth_mail" title="E-mail the corresponding author} ; Guo Rongwei^a
• 关键词：Airbreathing hypersonic vehicle ; Turbine based combined cycle (TBCC) ; Inlet mode transition ; Unsteady numerical simulation ; Shock oscillation
• 刊名：Propulsion and Power Research
• 出版年：2015
• 出版时间：September 2015
• 年：2015
• 卷：4
• 期：3
• 页码：141-149
• 全文大小：4453 K

文摘

A turbine based combined cycle (TBCC) propulsion system uses a turbine-based engine to accelerate the vehicle from takeoff to the mode transition flight condition, at which point, the propulsion system performs a “mode transition” from the turbine to ramjet engine. Smooth inlet mode transition is accomplished when flow is diverted from one flowpath to the other, without experiencing unstart or buzz. The smooth inlet mode transition is a complex unsteady process and it is one of the enabling technologies for combined cycle engine to become a functional reality. In order to unveil the unsteady process of inlet mode transition, the research of over/under TBCC inlet mode transition was conducted through a numerical simulation. It shows that during the mode transition the terminal shock oscillates in the inlet. During the process of inlet mode transition mass flow rate and Mach number of turbojet flowpath reduce with oscillation. While in ramjet flowpath the flow field is non-uniform at the beginning of inlet mode transition. The speed of mode transition and the operation states of the turbojet and ramjet engines will affect the motion of terminal shock. The result obtained in present paper can help us realize the unsteady flow characteristic during the mode transition and provide some suggestions for TBCC inlet mode transition based on the smooth transition of thrust.