Numerical simulation of the effect of tip clearance on axial flow compressor performance

Authors

1 Department of Aerospace Engineering, Malek-Ashtar University of Technology

2 Department of Aerospace Engineering, Malek-Ashtar University of Technology, Tehran

3 Department of Aerospace Engineering, Malek-Ashtar Univesity of Technology, Tehran

Abstract

In this paper, using numerical simulations of the Tip Clearance Size Effect of NASA Rotor 37 Blade on Axial Flow Compressor Performance and effective parameters, compressor performance and efficiency in the operating range of compressors are discussed. In this paper, In addition to the Standard design tip clearance the effect of increases and decreases the size of the tip clearance were also studied. For the numerical solution from steady state, compressibility and to simulate turbulent flow k-ε turbulence model was used. In order to validate Independence numerical mesh from the Grid Convergence Index criteria (GCI) was used. To validate numerical simulations performed in this study, the results of numerical solution were compared with experimental data. Results indicates well Tip Clearance Size Effect On efficiency, power and axial compressor overall performance.Reduce the maximum pressure in the proportion of 0.35%, 0.47% decline in yield and a 0.2% reduction in the power output of the compressor results tip clearance is 0.8.

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References

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Iranian Journal of Mechanical Engineering Transactions of ISME
Volume 19, Issue 2 - Serial Number 47
Fluid Mechanics and Heat Transfer
October 2016
Pages 96-122

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History

  • Receive Date: 27 November 2016
  • Revise Date: 28 January 2017
  • Accept Date: 03 October 2017

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