Patent ID: 7413409

Claim:
An airfoil for a gas turbine engine, comprising: opposed pressure and suction sidewalls extending between spaced-apart leading and trailing edges, a root, and a tip; a hollow plenum disposed between the sidewalls and having a profile bounded by opposed top and bottom edges and opposed forward and aft edges, the forward and aft edges being generally linear; the plenum having a chordwise first dimension at a radially outer end thereof, and a chordwise second dimension at a radially inner end thereof, the second dimension being substantially less than the first dimension; wherein the forward edge is disposed at a first angle to a radial direction, such that a radially inner end of the forward edge is aft of a radially outer end thereof; and the aft edge is disposed at a second angle to a radial direction, such that a radially inner end of the aft edge is forward of a radially outer end thereof.