A high-pressure steam turbine blade was investigated experimentally in a cascade windtunnel. The results of the experiment were used to calibrate a numerical CFD-optimisation process for an optimised compound lean turbine blade. The objective function used was global total pressure loss coefficient, the search algorithm was a self-programmed genetic algorithm. After initialisation the genetic algorithm suggested new compound lean configurations for calculation, then a commercial geometry- and mesh generator was used to construct and mesh the suggested configurations. Then the meshes were exported into a commercial CFD-solver. The optimisation calculated, after initialisation, more than 1200 compound lean configurations without any human interaction. A decrease in global total pressure loss of about 1.5% was achieved. Favourable effects on the flow angles, the downstream pressure distribution, the aerodynamic bladeload and the vortex systems could be observed and evalutated.