Patent ID: 8888455

Claim:
A blade for a gas turbine engine, comprising: an airfoil; an attachment affixed to a root portion of the airfoil and having an attachment opening with a defined perimeter therein; and a plug having a longitudinal axis disposed in the attachment opening, a combination of interference fit and centrifugal force retaining the plug in a fixed position in the attachment opening during operation of the engine, wherein the plug is configured to be retained in the attachment opening by an interference fit without the use of a material joining process, a flange extending radially outward from the longitudinal axis at one end of the plug to overlap a portion of the attachment about the entire perimeter of the attachment opening, wherein the flange is substantially parallel to a face of the attachment where the opening is formed; a back plate extending across the plug at an opposing end opposite from the flange; wherein the plug includes a flow control orifice configured to meter the flow of cooling air into the attachment; and wherein the flow control orifice is defined by a through hole formed in the back plate.