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Research Papers: Gas Turbines: Turbomachinery

Flowfield and Performance Analysis of a Three-Dimensional TBCC Exhaust Nozzle

[+] Author and Article Information
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

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

Xiao Wang

Shenyang Aircraft Design and Research Institute,
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

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

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 139(11), 112602 (Jul 19, 2017) (9 pages) Paper No: GTP-17-1006; doi: 10.1115/1.4037193 History: Received January 07, 2017; Revised June 28, 2017

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.

Copyright © 2017 by ASME
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References

Figures

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Fig. 1

Differential element for a quasi-two-dimensional flow

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Fig. 2

Ramjet nozzle design procedure by the MOC

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Fig. 3

Sketch of the conventional over–under TBCC exhaust system

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Fig. 4

Sketch of the new over–under TBCC exhaust system

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Fig. 5

Cross-sectional and rear views of the over–under TBCC exhaust nozzle model

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Fig. 6

Static pressure distribution along rotating ramp for different turbulence models at test point 5

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Fig. 7

Computational grid and boundary conditions

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Fig. 8

Static pressure distribution along rotating ramp for different grids at test point 5

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Fig. 9

Mach number distribution at the nozzle outlet for different grids at test point 5

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Fig. 10

Mach contour and pressure distribution of test point 1

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Fig. 11

Mach contour and pressure distribution of test point 2

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Fig. 12

Mach contour and pressure distribution of test point 5

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Fig. 13

Comparison of the schlieren image and the CFD result at test point 5

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Fig. 14

Comparisons of the schlieren images and the CFD results under the same NPRt of 8.5

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Fig. 15

Pressure distributions under the same NPRt of 8.5

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Fig. 16

Comparisons of the experimental data and CFD result at test point 6

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Fig. 17

Comparisons of the experimental data and CFD result at test point 7

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Fig. 18

Thrust coefficient over the flight envelop

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