Asian Journal of Scientific Research1992-14542077-2076Asian Network for Scientific Information10.3923/ajsr.2013.467.477H. Al-KayiemHussain K. Al-taieArkan DongWee Tiat 3201363Enhancement of gas turbine performance can be achieved by increasing the working
fluid temperature. On other hand, the level and variation in the temperature
within the blade material which causes thermal stresses, must be limited to
achieve reasonable durability goals. Therefore, there is a critical need to
cool the blades for safe operation by internal air flow passages. In this study,
CFD technique was employed to investigate the temperature distribution in at
different operational conditions. The blade was digitized to get the exact dimensions
in the form of AutoCad drawing which was then exported to GAMBIT for discretization
and to FLUENT for simulation. Flowing into a rectangular 9x18 mm channel, 400
K compressed air is used to cool the blade while the blade is spinning in hot
gas of 1700 K. The temperature distribution was compared with the results previously
obtained by using analytical-finite difference coupled method. The results show
that the temperature difference is less than 5% at the root of the blade and
15.9% at the channel of height 157.7 mm. Further simulation and analysis of
a ribbed channel with rib angle, α = 60° and rib blockage ratio, e/Dh
= 0.078 have been carried out and compared with previous analytical results.
Ribbed channel was compared with smooth channel cooling. The results showed
that there is a decrease in the blade material temperature which improves the
efficiency by 8.68% when using two-opposite rib walls on the 18 mm wide side
of the channel.]]>Bounegta, B., R. Dizene, M. Abdelkarim and M.A. Maazouzi,201010182188Dahlquist, A.,20082008Gao, X. and B. Sunden,200137315320Donald, W.M.,20082008Han, J.C., S. Dutta and S. Ekkad,2000Pages: 662.Pages: 662.Han, J.C.,200410443457Al-Kayiem, H.H. and A.H. Ghanizadeh,20111117331740Incropera, F.,20075th Edn.,