Patent ID: 8096770
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 and having 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; a trailing edge rib extending from said trailing edge toward said leading edge, said trailing edge rib forming a solid member between said pressure and suction sidewalls; a cooling fluid channel extending in the spanwise direction through said airfoil adjacent to said trailing edge rib; a plurality of fluid chambers formed in said trailing edge rib and extending chordwise between said cooling fluid channel and said trailing edge; a plurality of film cooling holes extending from said fluid chambers to said pressure and suction sidewalls; a plurality of trailing edge discharge holes extending from said fluid chambers to said trailing edge; and a metering hole associated with each of said fluid chambers, each said metering hole defining a flow restriction connecting said cooling fluid channel to a respective fluid chamber.