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所属单位：能源与动力学院

发表刊物：AEROSPACE SCIENCE AND TECHNOLOGY

关键字：Air-breathing hypersonic propulsion system Turbine-based combined-cycle Inlet mode transition Wind tunnel test

摘要：Smooth transition from turbojet to ramjet mode is critical to turbine-based combined-cycle (TBCC) propulsion system. Wind tunnel tests and numerical simulation were conducted to investigate the method of smooth inlet mode transition, and acquire corresponding inlet flow details. Steady-state pressure distribution was recorded in the experiment to evaluate inlet performance. Combined experimental and numerical investigation results indicate that smooth inlet mode transition can be achieved by keeping the total throttle ratio of the TBCC inlet constant. When the total throttle ratio is equal to 56%, the Mach number and the flow ratio of aerodynamic interface plane (AIP) would be basically equal to 0.22 and 0.50, respectively. Meanwhile, the terminal shock wave is located near the throat of the inlet during the mode transition. This paper puts forward the method of smooth mode transition of tandem-type turbine-based combined-cycle inlet and provides the flow details during this process. (C) 2016 Elsevier Masson SAS. All rights reserved.

ISSN号：1270-9638

是否译文：否

发表时间：2017-01-01

合写作者：刘君,华正旭,陈文芳,葛宁

通讯作者：袁化成