Patent ID: 8096771
Filing Date: 2012-01-17
Classification: F01D,F05D

Abstract:
1. A gas turbine engine hollow turbine airfoil comprising: an outer wall surrounding a hollow interior; said outer wall extending radially outwardly in a spanwise direction from an airfoil platform to an airfoil tip, said outer wall including chordwise spaced apart leading and trailing edges, and widthwise spaced apart pressure and suction sidewalls extending chordwise between said leading edge and said trailing edge; said trailing edge comprising a cutback trailing edge including a pressure sidewall lip and a suction sidewall lip, and defining a breakout distance between said pressure sidewall lip and said suction sidewall lip; said airfoil hollow interior comprising a cooling fluid channel extending in the spanwise direction through said airfoil adjacent to said trailing edge; a plurality of exit ports defined adjacent to said pressure sidewall lip, between said pressure sidewall and said suction sidewall; a plurality of flow dividers defining exit passages communicating between said cooling fluid channel and said exit ports; said flow dividers extending through said breakout distance to said suction sidewall lip to define breakout slots comprising continuations of said exit passages; said exit passages comprising a metering section and an interior diffusion section, said metering section extending from said cooling fluid channel to said interior diffusion section and defining a flow area; and said interior diffusion section comprising a spanwise dimension and a widthwise dimension perpendicular to said spanwise dimension, wherein said spanwise dimension continuously increases in a chordwise direction from said metering section to said exit ports, and said widthwise dimension continuously decreases in said chordwise direction from said metering section to said exit ports.