Measurements of the overall heat transfer coefficient within an impingement/effusion cooled wall are presented. The FLUENT CFD computer code has been applied to the internal aerodynamics to demonstrate the importance of the internal recirculation in the impingement gap. This generates a convective heat transfer to the impingement jet and measurements of this heat transfer plate coefficient are presented that show it to be approximately a half of the impingement/effusion heat transfer coefficient. The influence of the relative pressure loss or X/D between the impingement and effusion was investigated, for an effusion X/D of 4.67 and a Z of 8 mm, and shown to be only significant at high G where a reduction in h of 20% occurred. Increasing the number of holes, N, in the impingement/effusion array at a constant Z of 8 mm reduced h by 20%, mainly due to the higher Z/D for the smaller holes at high N. Reduced numbers of impingement holes relative to the effusion holes, in a ratio of 1 to 4, were shown to have a small influence on h with a maximum reduction in h of 20% at high G and a negligible effect at low G.

Measurements of the overall heat transfer coefficient within an impingement/effusion cooled wall are presented. The FLUENT CFD computer code has been applied to the internal aerodynamics to demonstrate the importance of internal recirculation in the impingement gap. This generates a convective heat transfer to the impingement jet. Measurements of this heat transfer plate coefficient are presented that show it to be approximately half of the impingement/effusion heat transfer coefficient. The influence of the relative pressure loss or X/D between the impingement and effusion walls was investigated, for an effusion X/D of 4.67 and a Z of 8 mm, and shown to be only significant at high G where a reduction in h of 20 percent occurred. Increasing the number of holes N in the impingement/effusion array at a constant Z of 8 mm reduced h by 20 percent, mainly due to the higher Z/D for the smaller holes at high N. Reduced numbers of impingement holes relative to the effusion holes, in a ratio of 1 to 4, were shown to have a small influence on h with a maximum reduction in h of 20 percent at high G and a negligible effect at low G.

The current experimental study is made to investigate the heat transfer characteristics and pressure losses for both impingement and impingement/effusion cooling systems. The experiments are carried out on a metal test plate. The numerical work is made to analyze the flow behavior in the test section. The benefit of introducing the present experimental method is the capability of investigating and analyzing the performance of both impingement and impingement/effusion cooling systems by the same test rig. The impinging jet device configurations are designed as inline round multihole arrays with jet to jet spacing of 4 jet hole diameter. The effusion holes configurations are inline round multi-hole arrays. Staggered arrangement between jet and effusion holes is maintained. The Jet Reynolds numbers (Re j ) of 5000 to 15000 and jet height to diameter ratio ( H D ⁄ ) of 1.5, 2.0, and 3.0 are maintained. For impingement/effusion case, the best wall cooling effectiveness is obtained at (H D ⁄ = 2), and maximum increment in the wall cooling effectiveness over that of impingement case is 23% at (Re j = 5000), 16 % at (Re j = 7500), and 14% at (Re j = 15000). Jet spacing in impingement case and blowing ratio in impingement/effusion case show an evident effect on the discharge coefficients.

The current experimental study focuses on the heat transfer characteristics and pressure losses for impingement system which is used in cooling the liner of gas turbine combustor. Recent experiment method of conductive heat transfer technique with resistive film in the back side target plate is introduced. The present experimental model measured both the heat transfer coefficient for inner target surface and the wall cooling effectiveness for outer target surface. To physically explain the phenomena associated with interaction flow area, a computational fluid dynamic code (Fluent 14) is employed. The continuity, momentum and energy equations are computationally solved to analyze the flow field in the jet impingement area. The tests models of the impingement plate are made from round jet holes of inline and staggered arrays arrangement with jet to jet spacing of four-hole diameter. Jet Reynolds numbers of 4200 to 15000 and jet height to diameter ratio of 1.5, 2.0, and 3.0 are maintained. The inline array, as expected enhanced the wall cooling effectiveness over that of the staggered array by 10.3% and both jet spacing and Reynolds number have an evident effect on the discharge coefficient. Empirical correlations are obtained for both arrays arrangement to predict the area-averaged Nusselt number as a function of jet governing parameters.