hydrodynamic and thermal characteristics for eco-gas ... · zhihong gao, narzary, d. p. and je-chin...
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Hydrodynamic and Thermal Characteristics Study of Cooling Structure (IIC) for Eco-Gas Turbine Engine Blade
PROJECT LEADER Dr. Hamidon Bin Salleh
PROJECT MEMBER Prof. Dr. Vij ay R. Ragavan Prof. Dr. Funazaki Kenichi
AP Dr. Ahmad Jais Bin Alimin Suzairin Bin Md Seri
Mohd Faizal Bin Mohideen Batcha Siti Rohila Binti Atan
GERAN FRGS Vot 0724
UNIVERSITJ: TUN HUSSEIN ONN MALAYSIA
ABSTRACT
Higher inlet temperature of gas turbine increases the thermal performance, requiring
the operating temperature to be higher that the allowable blade material temperature.
Study on advance cooling technique is required to fulfil the increasing demand on
lugher performance turbine system. The present study deals with numerical
simulation on an advanced Integrated Impingement Cooling (IIC) system. The IIC
integrates the conventional film cooling (external cooling) with internal cooling,
which comprises of cool jet impingement on inner blade wall (the target plate) and
structural pins that act as fins. Overall cooling performance of four (4) newly
proposed IIC configurations including two (2) configurations by Funazaki and
Hamidon (2008) have been investigated through unsteady three-dimensional
numerical simulation of RANS with k-E turbulence model via commercial CFD
package, FLUENT. The numerical results show good agreement with experimental
data of Funazaki and Harnidon (2008). It is concluded that the inner pin
configuration does not affect the adiabatic cooling performance at the outer wall.
However the pin configuration does affect the internal cooling performance,
consequently the overall cooling performance. It is observed that STAGS offers the
best overall performance of the six configurations studied.
REFERENCES
Goldstein, R. J. Film Cooling. Advances in Heat Transfer. 1971. Vol. 7: 32 1-
379.
Sen, B., Schmidt, D. L. and Bogard, D. G. Film Cooling with Compound
Angle Holes: Heat Transfer. ASME Journal of Turbornachinely. 1996. Vol.
118: 800-806.
Schmidt, D. L., Sen, B. and Bogard, D. G. Film Cooling with Compound
Angle Holes: Adiabatic Effectiveness. ASME Journal of Turbomachinery.
1996. Vol. 118: 807-813.
Lutum, E., Wolfersdorf, J. V., Weigand, B. and Semmler, K. Film Cooling on a
Convex Surface with Zero Pressure Gradient Flow. International Journal of
Heat and Mass Transfer. 2000. Vol. 43: 2973-2987.
Lutum, E., Wolfersdorf, J. V., Weigand, B., Dittrnar, J. and Sernrnler, K. An
Experimental Investigation of Film Cooling on a Convex Surface Subjected to
Favourable Pressure Gradient Flow. International Journal of Heat and Mass
Transfer. 2001. Vol. 44: 939-951.
Yuen, C. H. N. and Martinez-Botas, R. F. Film Cooling Characteristics of a
Single Round Hole at Various Streamwise Angles in a Crossflow: Part I.
Effectiveness. International Journal of Heat and Muss Transfer. 2003. Vol. 46:
221-235.
Yuen, C. H. N. and Martinez-Botas, R. F. Film Cooling Characteristics of a
Single Round Hole at Various Streamwise Angles in a Crossflow: Part 11. Heat
Transfer Coefficients. International Journal of Heat and Mms Transfer. 2003.
VOI. 46: 237-249.
Maiteh, B. Y. and Jubran, B. A. Effects of Pressure Gradient on Film Cooling
Effectiveness from Two Rows of Simple and Compound Angle Holes in
Combination. Energy Conversion and Management. 2004. Vol. 45: 1457-1469.
Yuen, C. H. N. and Martinez-Botas, R. F. Film Cooling Characteristics of
Rows of Round Holes at Various Streamwise Angles in a Crossflow: Part I.
Effectiveness. International Journal ofHeat and Mass Transfer. 2005. Vol. 48:
4995-50 16.
Yuen, C. H. N. and Martinez-Botas, R. F. Film Cooling Characteristics of
Rows of Round Holes at Various Streamwise Angles in a Crossflow: Part 11.
Heat Transfer Coefficients. International Journal of Heat and Mass Transfer.
2005. Vol. 48: 5017-5035.
Abu Talib, A. R., Jaafar, A. A., Mokthar, A. S., Mohd Saiah, H. R., Abd.
Rahim, I. and Abd. Karirn, M. S. Effects of Blowing Ratio on the Heat
Transfer Coefficient Distribution Downstream of a Single Film Cooling Hole.
International Journal of Engineering and Technology. 2006. Vol. 3(1): 37-46.
Colban, W. and Thole, K. Influence of Hole Shape on The Performance of a
Turbine Vane Endwall Film-cooling Scheme. International Journal of Heat
and Fluid Flow. 2007. Vol. 28: 34 1-356.
Jaeyong Ahn, Schobeiri, M. T., Je-Chin Han and Hee-Koo Moon. Effects of
Rotation on Leading Edge Region Film Cooling of a Gas Turbine Blade with
Three Rows of Film Cooling Holes. International Journal of Heat and Mass
Transfer. 2007. Vol. 50: 15-25.
Li Guangchao, Zhu Huiren and Fan Huiming. Influence of Hole Shape on Film
Cooling Characteristics with C02 Injection. Chinese Journal of Aeronautics.
2008. Vol. 21: 393-401.
Zhihong Gao, Narzary, D. P. and Je-Chin Han, Film Cooling of a Gas Turbine
Blade Pressure Side or Suction Side with Axial Shaped Holes. International
Journal of Hear and Mass Transfer. 2008. Vol. 51 : 2139-2152.
Vipluv Aga, Rose, M. and Reza S. Abhari. Experimental Flow Structure
Investigation of Compound Angled Film Cooling. ASME Journal of
Turbomachinery. 2008, Vol. 130: 031005 1-8.
Wright, L. M., Blake, S. A. and Je-Chin Han. Film Cooling Effectiveness
Distributions on a Turbine Blade Cascade Platform with Stator-Rotor Purge
and Discrete Film Hole Flows. ASME Journal ofirurbomachinery. 2008. Vol.
130: 031015 1-10.
Zhi Tao, Xiaojun Yang, Shuiting Ding, Guogiang Xu, Hongwei Wu, Hongwu
Deng and Xiang Luo. Experimental Study of Rotation Effect on Film Cooling
over the Flat Wall with a Single Hole. Experimental Thermal and Fluid
Science. 2008. Vol. 32: 1081-1089.