Indian Journal of Science and Technology

Open Access Open Access  Restricted Access Subscription Access

Effect of Hollow Blades on Flow Improvement in Turbines and Large Scale Fans


Affiliations
1 Department of Mechanical Engineering, Universiti Tenaga Nasional, Kajang, Malaysia
2 Department of Engineering, Islamic Azad University, Najafabad Branch, Iran, Islamic Republic of
 

In this paper different computational fluid dynamics (CFD) methods have been defined and modern methods are developed and compared with conventional ones. Numerical methods are used to calculate volume flow rates of turbines and axial flow fans. Validation of results with experimental data is improved significantly by using hollow blades and this will result to increased efficiency of turbines and large scale fans.

Keywords

Computational Fluid Dynamics (CFD), Axial Flow Fans, Volume Flow Rate, Hollow Blade Turbine
User

  • Bleier F P (1998). Fan Handbook: selection, application, and design, McGraw-Hill, New York.

  • Borello D, Hanjalic K et al. (2007). Computation of tip-leakage flow in a linear compressor cascade with a second-moment turbulence closure, International Journal of Heat and Fluid Flow, vol 28(4), 587-601.

  • Chang C C et al., (2010). Air cooling for a large-scale motor, Applied Thermal Engineering, vol 30(11), 1360-1368.

  • Eberlinc M et al. (2009). Modification of axial fan flow by trailing edge self-induced blowing, Journal of Fluids Engineering, vol 131(11), 111104-1-111104-7.

  • Eberlinc M, B Širok et al. (2009). Experimental investigation of the interaction of two flows on the axial fan hollow blades by flow visualization and hot-wire anemometry, Experimental Thermal and Fluid Science, vol 33(5), 929-937.

  • Eberlinc M, Širok B et al. (2009). Patented hollow blades of the axial fan with trailing edge self-induced blowing, 0Benthem Science Publishers Recent Patents on Mechanical Engineering, vol 2(1), 1-7.

  • Eberlinc M et al. (2007). Axial turbine machine hollow blade with internal and external flow field, The Slovenian Intellectual Property Office, Patent No. P. 200700271.

  • Eberlinc M et al. (2008). Influence on the axial flow fan aerodynamic characteristic due to an introduction of internal secondary flow, ASME. Fluids Engineering Division Summer Conference, Jacksonville, Florida, USA.

  • Eberlinc M et al. (2009). Numerical and experimental investigation of axial fan with trailing edge self-induced blowing, Forschung im Ingenieurwesen, vol 73(3), 129-138.

  • Ferro L, Gato L et al. (2010). Design and experimental validation of the inlet guide vane system of a mini hydraulic bulb-turbine, Renewable Energy, vol 35(9), 1920-1928.

  • Garg V K (2002). Heat transfer research on gas turbine airfoils at NASA GRC, International Journal of Heat and Fluid Flow, vol 23(2), 109-136.

  • Lakshminarayana B (1996). Fluid dynamics and heat transfer of turbomachinery, Secondary Title, John Wiley, New York.

  • Liu S H, Huang R F (2010). Computational and experimental investigations of performance curve of an axial flow fan using downstream flow resistance method, Experimental Thermal and Fluid Science, vol 34(7), 827-837.

  • Meyer C j, and Kröger D G (2001). Numerical simulation of the flow field in the vicinity of an axial flow fan, International Journal for Numerical Methods in Fluids, vol 36(8), 947-969.

  • Murthy B et al. (2007). Hollow self-inducing impellers: Flow visualization and CFD simulation, Chemical Engineering Science, vol 62(14), 3839-3848.

  • Rhee S (2003). Analysis of a jet-controlled high-lift hydrofoil with a flap, Ocean Engineering, vol 30(16), 2117-2136.

  • Schlichting H, and K Gersten (2004). Boundary-layer theory, Springer.

  • Standard B (1997), Fans for general purpose. International Organization for Standardization: ISO 5801, Fans for General Purpose: Part 1: Performance Testing Using Standardized Airways.

  • Sutliff D L et al. (2002). Low-speed fan noise reduction with trailing edge blowing, International Journal of Aeroacoustics, vol 1(3), 275-305.

  • Wallis R (1983). Axial flow fans and ducts, Secondary Title, John Wiley & Sons, New York.

  • Woodward R P, Fite E B (2007). Noise benefits of rotor trailing edge blowing for a model turbofan, 45th Aerospace Sciences Meeting and Exhibit, AIAA.

  • Yakhot A et al. (1989). Renormalization group formulation of large-eddy simulations, Journal of Scientific Computing, vol 4(2), 139-158.

  • Yakhot V et al. (1992). Development of turbulence models for shear flows by a double expansion technique, Physics of Fluids A: Fluid Dynamics, vol 4(7), 1510-1520.

  • Yakhot V, and Orszag S A (1986). Renormalization group analysis of turbulence I. Basic theory, Journal of Scientific Computing, vol 1(1), 3-51.


Abstract Views: 486

PDF Views: 0




  • Effect of Hollow Blades on Flow Improvement in Turbines and Large Scale Fans

Abstract Views: 486  |  PDF Views: 0

Authors

Ali Najafzadeh
Department of Mechanical Engineering, Universiti Tenaga Nasional, Kajang, Malaysia
Ali Zare
Department of Mechanical Engineering, Universiti Tenaga Nasional, Kajang, Malaysia
Behzad Shahizare
Department of Mechanical Engineering, Universiti Tenaga Nasional, Kajang, Malaysia
S. Meysam Kosari Esfahan
Department of Engineering, Islamic Azad University, Najafabad Branch, Iran, Islamic Republic of
Iman Asadi
Department of Mechanical Engineering, Universiti Tenaga Nasional, Kajang, Malaysia
Naeim Ezzat Ahmadi
Department of Mechanical Engineering, Universiti Tenaga Nasional, Kajang, Malaysia

Abstract


In this paper different computational fluid dynamics (CFD) methods have been defined and modern methods are developed and compared with conventional ones. Numerical methods are used to calculate volume flow rates of turbines and axial flow fans. Validation of results with experimental data is improved significantly by using hollow blades and this will result to increased efficiency of turbines and large scale fans.

Keywords


Computational Fluid Dynamics (CFD), Axial Flow Fans, Volume Flow Rate, Hollow Blade Turbine

References





DOI: https://doi.org/10.17485/ijst%2F2013%2Fv6i5%2F33248