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所属单位：能源与动力学院
发表刊物：Int. Space Planes Hypersonics Technol. Conf.
摘要：TBCC (Turbine Based Combined Cycle) concept engine is becoming one of the most prominent domains of the future reusable hypersonic vehicle and is attracting more and more attention in recent years for its higher specific and fine realizability. In this paper, a new scheme of rotating around the rear shaft is adopted to achieve the requirement of adjusting the throat area ratio while the TBCC propulsion system working in turbo or transition mode. Experimental investigation is conducted to understand the performance and flow structures of the over-under TBCC exhaust system under different working conditions. During the experiments, the model is instrumented to carry out static pressure measurement. In addition, schlieren technology is used to visualize the detailed flow structures in the nozzle. The schlieren images demonstrate that flow structure in transition mode is complex, and the interaction of the two flowpaths is obvious, the experimental results indicate that the turbojet flow influences the flowfield downstream the ramjet outlet rather than that of internal flowfield of ramjet, and the ramjet flow will have a great impact on the internal flowfield of the turbojet nozzle, which should be taken into consideration in the design process of the TBCC nozzle. © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
是否译文：否
发表时间：2017-01-01
合写作者：许保成,牛彦沣,陈匡世,Wang, Xiao,Zhu, Wei
通讯作者：徐惊雷