Calculation of the flow around a high-pressure turbine blade with cooling-jet injection from slots at the leading edge

A fully vectorised, basically three-dimensional finite-volume multi-block m ethod for flows with complex boundaries is applied in a stripped-down two-d imensional version for the investigation of the flow field in the leading-e dge region of a high-pressure turbine blade with slot cooling-jet injection . The calculation results are compared with experiments and the numerical r esults of other investigators. The present method yields excellent agreemen t with the experiments for the isentropic Mach number distributions on the blade surface. All numerical results for the velocity field were found to b e in very good agreement with each other and with experiments on the suctio n side, while the agreement is not as good on the pressure side.