Experimental Investigation of Flow Around a 3D Square Cylinder Using Five-hole Probe and Neural Networks Method

Document Type : Research Article

Authors

1 Mechanical Engineering Department, Iran University of Science & Technology, Tehran, Iran

2 Mechanical and Aerospace Engineering Department Science and Research Branch of the Islamic Azad University (SRBIAU), Tehran, Iran

Abstract

In the present research, axial compressor blade cascade was analyzed by using numerical and experimental methods. The model includes three rotor blades of an axial compressor having the same geometry and profile of NGTE 10C4/30C5 aligned parallel with a ratio of chord length to the blade pitch (rigidity) 0f 0.8-1.2. The experiments were done in a subsonic wind tunnel. Before the tests, some reforms in the output of the wind tunnel were designed to install a new test section, suitable for cascade testing. The necessary considerations are made to let a hot-wire probe to go through the wind tunnel’s wall move on the surface of the blades. The suction surfaces and pressure of the test blade have been equipped to the suitable tapping of the pressure to be connected through the connector hoses to the pressure transducers. Different situations between the blades were performed and at any stage of testing, the suction surface velocity and pressure profiles were measured in different longitudinal situations and distribution of surface pressure. Parallel with the experiments, the numerical analysis for different modes has been performed and the results were compared to experimental data. Combining the results of CFD and experimental measurements gives us a powerful tool for simulation, design and improvement.

References

[1] Howell, A. R. “Design of Axial Compressors”. Lectures on the Development of the British Gas Turbine Jet Unit Published in War Emergency Issue No. 12 of the Institution of Mechanical Engineers. A.S.M.E. Reprint, (1947): 452-462.
[2] Hayashibara, S., “Cascade flow Simulation and Measurement for the Study of Axial Compressor Loss Mechanism”, Wichita State University, 2003.
[3] Whitehead, D. S, “Force and Moment Coefficients for Vibrating Airfoils in Cascade”, University of Cambridge, 1962.
[4] Ardekani, M.A., “Low Speed Wind Tunnel , Design Principles & Application” . Khajenasir Uni. Tehran , Iran, 2010.
[5] Bruun, H.H., “Hot-Wire Anemometery Principles and signal analysis”,Oxford university press, (1996): 19-127.
[6] Collis, D.C. and Williams, M.J., “Two –dimensional convection from heated wire at low Reynold numbers”.,J.Fluid Mech, 6(1959): 357-384.
[7] Papadopoulos, G and M.V. Otugen “A Simple automated hotwire positioning technique for near-wall measurements”.Experiments in Fluids”, 15 (1993): 459-461.
[8] Athanasiadis, A.N., D.G. Koubogiannis and K.C. Giannakoglou “One- and two-equation turbulence models for the prediction of complex cascade flows using unstructured grids”, 2001.
[9] Kunz, R. F., B. Lakshminarayan, “Computation of Supersonic and Low Subsonic Cascade Flows Using An Explicit Navier-Stokes Technique amd The k-E Turbulence Model”, Department of Aerospace Engineering Pennsylvania State University,1992.
[10] Rodrick V.Chima, “Analysis of Inviscid and Viscouse Flows in Cascades with and Explicate Multiple-Grid Algorithm”, Lewis Research Center Cleveland, Ohio, 1984.
[11] Yaha, S. M.,“Turbines ,Compressors and Fans”,Tata MaGraw-Hill Publishing company Limited , 2002.
Amirkabir Journal of Mechanical Engineering
Volume 49, Issue 1
April 2017
Pages 3-10

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