Patent ID: 9017026
Filing Date: 2015-04-28
Classification: F01D,F05D,Y02T

Abstract:
1. A gas turbine engine turbine airfoil comprising: widthwise spaced apart pressure and suction sidewalls extending outwardly along a span from an airfoil base to an airfoil tip; the pressure and suction sidewalls extending chordwise between opposite leading and trailing edges; a spanwise row of spanwise spaced apart trailing edge cooling holes encased in the airfoil between the pressure and suction sidewalls and ending at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge; each of the cooling holes including a spanwise diverging section leading into the trailing edge cooling slot; and a plug disposed in each of the cooling holes and the plug extending downstream through at least a portion of the diverging section, the plug further comprising a plug dome rising up from a plug base of the plug and the plug base extending along a suction sidewall surface of the suction sidewall, the plug being spanwise centered in the hole and including widthwise and spanwise rounded upstream and downstream dome ends.