Compared to other engines, turbine-based combined cycle (TBCC) engine is one of the most suitable propulsion systems for hypersonic vehicle. Because of its fine reusability, wide flight envelope, and safety margins, TBCC engine is becoming a more and more important hotspot of research. In this paper, a three-dimensional (3D) over–under TBCC exhaust system is designed, simulated, and the results are discussed, wherein the ramjet flowpath is designed by the quasi-two-dimensional method of characteristics (MOC). A new scheme of rotating around the rear shaft is proposed to regulate the throat area of turbine flowpath. Cold flow experiments are conducted to gain a thorough and fundamental understanding of TBCC exhaust system at on and off-design conditions. To characterize the flow regimes, static pressure taps and schlieren apparatus are employed to obtain the wall pressure distributions and flowfield structures during the experiments. Detailed flow features, as well as the thrust performance, are simulated by the computational fluid dynamics (CFD) method. Both the numerical and experimental results show that the TBCC exhaust nozzle in this study can provide sufficient thrust during the whole flight envelop despite a little deterioration at the beginning of the mode transition. The research provides a new and effective scheme for the exhaust system of TBCC engine.
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November 2017
Research-Article
Flowfield and Performance Analysis of a Three-Dimensional TBCC Exhaust Nozzle
Baocheng Xu,
Baocheng Xu
Jiangsu Province Key Laboratory of
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: alvin_xubc@163.com
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: alvin_xubc@163.com
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Jinglei Xu,
Jinglei Xu
Professor
Jiangsu Province Key Laboratory of
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: xujl@nuaa.edu.cn
Jiangsu Province Key Laboratory of
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: xujl@nuaa.edu.cn
Search for other works by this author on:
Xiao Wang,
Xiao Wang
Shenyang Aircraft Design and Research Institute,
Aviation Industry Corporation of China (AVIC),
Shenyang 110035, Liaoning, China
e-mail: alenwx@126.com
Aviation Industry Corporation of China (AVIC),
Shenyang 110035, Liaoning, China
e-mail: alenwx@126.com
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Wei Zhu,
Wei Zhu
Shenyang Aircraft Design and Research Institute,
Aviation Industry Corporation of China (AVIC),
Shenyang 110035, Liaoning, China
e-mail: zwwder@163.com
Aviation Industry Corporation of China (AVIC),
Shenyang 110035, Liaoning, China
e-mail: zwwder@163.com
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Yanfeng Niu
Yanfeng Niu
Jiangsu Province Key Laboratory of
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: yanfengniu@163.com
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: yanfengniu@163.com
Search for other works by this author on:
Baocheng Xu
Jiangsu Province Key Laboratory of
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: alvin_xubc@163.com
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: alvin_xubc@163.com
Jinglei Xu
Professor
Jiangsu Province Key Laboratory of
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: xujl@nuaa.edu.cn
Jiangsu Province Key Laboratory of
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: xujl@nuaa.edu.cn
Xiao Wang
Shenyang Aircraft Design and Research Institute,
Aviation Industry Corporation of China (AVIC),
Shenyang 110035, Liaoning, China
e-mail: alenwx@126.com
Aviation Industry Corporation of China (AVIC),
Shenyang 110035, Liaoning, China
e-mail: alenwx@126.com
Wei Zhu
Shenyang Aircraft Design and Research Institute,
Aviation Industry Corporation of China (AVIC),
Shenyang 110035, Liaoning, China
e-mail: zwwder@163.com
Aviation Industry Corporation of China (AVIC),
Shenyang 110035, Liaoning, China
e-mail: zwwder@163.com
Yanfeng Niu
Jiangsu Province Key Laboratory of
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: yanfengniu@163.com
Aerospace Power System,
College of Energy and Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, Jiangsu, China
e-mail: yanfengniu@163.com
1Corresponding author.
Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received January 7, 2017; final manuscript received June 28, 2017; published online July 19, 2017. Assoc. Editor: Haixin Chen.
J. Eng. Gas Turbines Power. Nov 2017, 139(11): 112602 (9 pages)
Published Online: July 19, 2017
Article history
Received:
January 7, 2017
Revised:
June 28, 2017
Citation
Xu, B., Xu, J., Wang, X., Zhu, W., and Niu, Y. (July 19, 2017). "Flowfield and Performance Analysis of a Three-Dimensional TBCC Exhaust Nozzle." ASME. J. Eng. Gas Turbines Power. November 2017; 139(11): 112602. https://doi.org/10.1115/1.4037193
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