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Effects of back pressure fluctuation on pseudo-shock waves in a rectangular duct

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Abstract

Pseudo-shock waves in a scramjet isolator are worth studying. These waves are generally subjected to back pressure fluctuation induced by combustion. The characteristics and unsteadiness mechanism of pseudo-shock waves are investigated using a numerical method. A second nozzle with a movable pintle is utilized to simulate the back pressure fluctuation of a combustion chamber in the numerical model. A 2D numerical method with the kω-shear stress transport turbulence model is adopted to investigate the behavior of pseudo-shock waves. Validation of the numerical model is performed by comparing its results with existing experimental results. The accuracy of the numerical model is proven. The present study aims to investigate the unsteady characteristics of pseudo-shock waves in a scramjet isolator. As indicated by the results, the amplitude of pseudo-shock wave motion can be reduced by increasing the exciting frequency of back pressure fluctuation. The influence mechanism of exciting frequency is the phase difference caused by time delay.

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Abbreviations

A s :

Amplitude of shock train leading edge oscillation

A th :

Throat area of the first nozzle

A* :

Throat area of the second nozzle

C :

Sound speed

f b :

Exciting frequency of fluctuating back pressure

H th :

Throat height of the first nozzle

H* :

Throat height of the second nozzle

L :

Length of the entire test section

L 1 :

Length of the first section

L 2 :

Length of the second section

L 3 :

Length of the third section

P :

Static pressure

P i,0 :

Stagnation pressure at the inlet

t :

Time

T :

Duration of one period

U :

Speed of subsonic flow where disturbances propagate

V :

Propagation velocity of pressure disturbances

x:

Coordinate along the x-axis

Xs :

Coordinate of shock train leading edge along the x-axis

α 1 :

Half divergence angle of the first section

α 2 :

Half divergence angle of the second section

α 3 :

Half divergence angle of the third section

STLE:

Shock train leading edge

TR:

Throat area ratio

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Acknowledgments

This work was supported by the National Natural Science Foundation of China (Grant Nos. U1713211 and 61673300) and the Natural Science Foundation of Shanghai (18DZ1200804).

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Authors and Affiliations

  1. Department of Control Science and Engineering, Tongji University, Shanghai, China

    Ruoyu Deng & Qijun Chen

  2. Department of Mechanical Engineering, Andong National University, Andong, 760-749, Korea

    Heuy Dong Kim

Authors
  1. Ruoyu Deng
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  2. Heuy Dong Kim
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  3. Qijun Chen
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Corresponding author

Correspondence to Ruoyu Deng.

Additional information

Ruoyu Deng obtained his M.S. in Mechanical Engineering from Zhejiang Sci-Tech University, China in 2013. He obtained his Ph.D. in Mechanical Engineering from Andong National University, Korea in 2017. Dr. Deng is currently a postdoctoral student in Tongji University, China. His research interests include thrust vector control, ramjets and scramjets, fluid power, and mechatronic systems.

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Deng, R., Kim, H.D. & Chen, Q. Effects of back pressure fluctuation on pseudo-shock waves in a rectangular duct. J Mech Sci Technol 34, 4649–4655 (2020). https://doi.org/10.1007/s12206-020-1023-5

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  • DOI: https://doi.org/10.1007/s12206-020-1023-5

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