Numerical modelling of heat transfer distributions on jet impingement cooling plate

Nowadays, although the material technology quite reach the inlet temperature of the advanced gas turbine is higher than the withstand temperature of the flap material. Therefore, it is necessary to cool the turbine blades produced in absolute terms of the material technology. This much is important cooling has led to extensive research in gas turbine cooling technology producers, especially the blades. Internal cooling methods such as cooling via convection cooling and impingement, film cooling and external cooling methods such as transpiration cooling methods are mainly used to cool the gas turbine blades. In this study, University of Pittsburgh's Department of Mechanical Engineering the Thermochromic Liquid Crystals (TLC) thermal method was performed by Dr. Al-aqal [1] and use the experimental jet impingement models in his study; single rows with jet diameter (D) 9,52 mm, couple rows with jet diameter (D) 4,76 mm, triple rows with jet diameter (D) 3,18 mm. This each models tested for three different target plate distance (H) 12,7 mm, 19,05 mm and 25,4 mm with three different inlet velocities 22,2 m/s, 28,5 m/s and 42,8 m/s to investigate effects averaged local heat transfer with experimental method In this study, experimental models and boundary conditions used same for the numerical modeling study to investigate the heat transfer characteristics on surfaces. Calculation made by SST (Shear Stress Transport) k-ω turbulence model using commercial computational fluid dynamics program. Then the obtained numerical results are compared with experimental study results and CFD programs approach investigated. In Section 2, some research did about the subject such as boundary conditions, wall functions, turbulence modeling and essential data picked for the study. In Section 3, numerical models made according to literature and experimental work with necessary acceptances. Numerical analysis results and experimental results are compared in Section 4. Conclusions take part in Section 5.