Conference paper ASME GT2009-59626, Orlando, USA
G. Kröger, C. Cornelius, E. Nicke
Year of publication: 2009
In the high pressure stages of gas turbine compressors a rather large radial tip clearance must be kept because of thermal and mechanical stress. To minimize the clearance losses a new axisymmetric and waved endwall contouring is developed. For the design an automated optimization method including 3D-CFD is used. The efficiency of the high pressure stage was significantly improved without modifying the stage pressure ratio. In this paper the aerodynamic effects induced by the axisymmetric endwall contouring are presented and discussed.