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Research Papers: Gas Turbines: Turbomachinery

Flow Characteristics of Double Serpentine Convergent Nozzle With Different Inlet Configuration

[+] Author and Article Information
Sun Xiao-Lin

School of Power and Energy,
Collaborative Innovation Center for
Advanced Aero-Engine,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: 2014100446@mail.nwpu.edu.cn

Wang Zhan-Xue

Professor
School of Power and Energy,
Collaborative Innovation Center for
Advanced Aero-Engine,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: wangzx@nwpu.edu.cn

Zhou Li

Professor
School of Power and Energy,
Collaborative Innovation Center for
Advanced Aero-Engine,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: zhouli@nwpu.edu.cn

Shi Jing-Wei

School of Power and Energy,
Collaborative Innovation Center for
Advanced Aero-Engine,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: shijingwei@mail.nwpu.edu.cn

Cheng Wen

School of Power and Energy,
Collaborative Innovation Center for
Advanced Aero-Engine,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: chengwen0614@163.com

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 3, 2017; final manuscript received November 6, 2017; published online April 12, 2018. Assoc. Editor: Haixin Chen.

J. Eng. Gas Turbines Power 140(8), 082602 (Apr 12, 2018) (12 pages) Paper No: GTP-17-1259; doi: 10.1115/1.4038793 History: Received July 03, 2017; Revised November 06, 2017

Serpentine nozzles have been used in stealth fighters to increase their survivability. For real turbofan aero-engines, the existence of the double ducts (bypass and core flow), the tail cone, the struts, the lobed mixers, and the swirl flows from the engine turbine, could lead to complex flow features of serpentine nozzle. The aim of this paper is to ascertain the effect of different inlet configurations on the flow characteristics of a double serpentine convergent nozzle. The detailed flow features of the double serpentine convergent nozzle including/excluding the tail cone and the struts are investigated. The effects of inlet swirl angles and strut setting angles on the flow field and performance of the serpentine nozzle are also computed. The results show that the vortices, which inherently exist at the corners, are not affected by the existence of the bypass, the tail cone, and the struts. The existence of the tail cone and the struts leads to differences in the high-vorticity regions of the core flow. The static temperature contours are dependent on the distributions of the x-streamwise vorticity around the core flow. The high static temperature region is decreased with the increase of the inlet swirl angle and the setting angle of the struts. The performance loss of the serpentine nozzle is mostly caused by its inherent losses such as the friction loss and the shock loss. The performance of the serpentine nozzle is decreased as the inlet swirl angle and the setting angle of the struts increase.

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References

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Figures

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Fig. 1

The whole exhaust geometric model

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Fig. 2

Serpentine nozzle centerline and alterable sections

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Fig. 3

The primary geometric parameters of the whole exhaust

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Fig. 4

The double serpentine convergent nozzles with different inlet configurations

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Fig. 5

Experimental setup

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Fig. 6

Turbulent model validation by the experimental data: (a) static pressure distributions on upper wall and lower wall, (b) static pressure distributions on sidewall, (c) flux rates versus NPR, and (d) axial thrust versus NPR

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Fig. 7

Comparison between wall static pressure distributions for three grid sizes

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Fig. 8

Grids of the full computational domain and the grids on the nozzle and struts: (a) full computational domain grids, (b) grids on the nozzle, and (c) grids on the struts

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Fig. 9

The streamwise locations of the cross section of the serpentine nozzle

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Fig. 10

The comparisons of the symmetric wall surface pressure distributions for M1, M2, and M3 case

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Fig. 11

The comparisons of the symmetric plane Ma contours for M1, M2, and M3 case

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Fig. 12

Surface limiting streamlines on the tail cone

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Fig. 13

The comparisons of the x-streamwise vorticities on the flow cross section M0, M1, M2, and M3 case

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Fig. 14

The distributions of the static temperature on the cross section for M1, M2, and M3 case

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Fig. 15

The surface flows on the tail cone for these four cases based on M2 model

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Fig. 16

The comparisons of the symmetric plane Ma contours for these four cases based on M2 model

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Fig. 17

The comparisons of the x-streamwise vorticities on the flow cross section for these four cases based on M2 model

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Fig. 18

The distributions of the static temperature on the cross section for these four cases based on M2 model

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Fig. 19

Comparisons of performance parameters for these four cases based on M2 model: (a) the total pressure recovery coefficient and (b) the thrust coefficient

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Fig. 20

The surface flows on the tail cone for these four cases based on M3 model

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Fig. 21

The comparisons of the symmetric plane Ma contours for these four cases based on M3 model

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Fig. 23

The distributions of the static temperature on the cross section for these four cases based on M3 model

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Fig. 22

The comparisons of the x-streamwise vorticities on the flow cross section for these four cases based on M3 model

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Fig. 24

Comparisons of performance parameters for these four cases based on M3 model: (a) the total pressure recovery coefficient and (b) the thrust coefficient

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