FILM COOLING OF TURBINE BLADES OR VANES

摘要

The present invention relates to a turbine assembly (10) comprising at least an aerofoil (42) and/or the aerofoil (42) and an end wall (48). The aerofoil (42) and/or the end wall (48) (each) having at least an outer surface (16, 18) with at least a structure (24, 24') for directing a flow (22) of a cooling medium at the outer surface (16, 18). According the invention the structure (24, 24') at the outer surface (16, 18) of the aerofoil (42) has at least a first groove (26) and a second groove (28) extending in the outer surface (16, 18) basically from a leading edge (44) to a trailing edge (46) of the aerofoil (42) and being oriented in at least two different directions (30, 32) with a deflection angle (a) towards each other, with said deflection angle (a) having a component in a span wise direction (50) of the aerofoil (42). According the invention the structure (24, 24') at the outer surface (16, 18) of the end wall (48) has at least a first groove (26) and a second groove (28) extending basically in an axial direction (52) of the turbine assembly in the outer surface (16, 18), matching an outer profile (54) of the aerofoil (42) and being oriented in at least two different directions (30, 32) with a deflection angle (a) towards each other.