×

Gas turbine airfoil

  • US 8,231,349 B2
  • Filed: 03/20/2009
  • Issued: 07/31/2012
  • Est. Priority Date: 03/31/2008
  • Status: Expired due to Fees
First Claim
Patent Images

1. A gas turbine engine component comprising:

  • a root and a tip separated along a longitudinal axis;

    an airfoil portion having a leading edge, a trailing edge, an external suction side wall, and an external pressure side wall, the external walls extending between said leading edge and said trailing edge, said external walls enclosing a central cavity for the passage of cooling air between the root and the tip;

    at least one longitudinally extending first web connecting said suction side wall with said pressure side wall, said at least one first web partitioning said cavity into a leading edge region and a trailing edge region and defining a leading edge chamber in the leading edge region;

    a second longitudinally extending web connecting said at least one first web with the suction side wall and defining a first entry chamber on the suction side of the second web and a second entry chamber for cooling air in the trailing edge region;

    wherein said at least one first web comprises at least one cross-over hole between the first entry chamber and the leading edge chamber, and wherein the second web is devoid of openings;

    wherein the at least one cross-over hole in the at least one first web between the first entry chamber and the leading edge chamber comprises a longitudinally extending row of holes, and wherein the cross-sectional area of the holes of said row is larger in a region of the tip than in a region of the root.

View all claims
  • 3 Assignments
Timeline View
Assignment View
    ×
    ×