Steady-state stress relaxation analysis of turbine blade cooling designs

Abstract

An analytical evaluation was made of five turbine blade cooling configurations for advanced airbreathing engines on the basis of the time to a local creep strain of 1 per cent for cast IN 100.The longest life w a s shown by the transpiration design (neglecting oxidation problems) followed by the multiple small hole design.Curves were established to predict the multiple small hole blade life under various combinations of turbine inlet and coolant temperatures and coolant to total gas flow ratios.