Patent ID: 9394798
Filing Date: 2016-07-19
CPC Classification: F01D,F05D,Y02T

Claim Text:
1. An airfoil for a gas turbine engine, comprising: a body comprising a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge of the airfoil, and a suction side wall extending between the leading edge and the trailing edge of the airfoil, wherein the body defines an interior cavity; and an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber, wherein the interior wall defines a first cooling hole with a first base portion and a first locally extended portion completely surrounding the first cooling hole and a second cooling hole being adjacent to the first cooling hole in a radial row of cooling holes in the interior wall, the second cooling hole having a second base portion and a second locally extended portion completely surrounding the second cooling hole, the first and second cooling holes configured to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge, wherein the first and second locally extended portions are separated at a respective distance from each of the pressure and suction side walls and are separated from one another.