Influence of compound angle on adiabatic film cooling effectiveness and heat transfer coefficient for a row of shaped film cooling holes

The measurement of adiabatic 1m cooling effectiveness data and heat transfer coef cient data for a row of fanshaped 1m cooling holes at different compound angles is presented in this paper. The measurements are performed at engine-like temperature ratios in a hot gas test facility on a at test plate. For the 1m cooling geometry, a row of ve laidback-fanshaped holes was used. The temperature distribution on the at plate is measured using infrared-thermography (IR). Steady state measure. ments are used to obtain the 1m cooling effectiveness. For the determination of the heat transfer coef cient ratio with and without 1m cooling on the test plate, a transient measurement technique is applied. Results for both the adiabatic 1m cooling effectiveness and the heat transfer coef cient ratio are given. The in uence of different blowing ratios on the injection with compound angles of 0, 30 and 45 will be discussed. From this study, the increasing compound angle showed only small effects on the pitch-wise lateral averaged adiabatic 1m cooling effectiveness but increased the heat transfer on the 1m cooled at plate with coolant injection.