Internally cooled airfoil for a gas turbine engine and method

• US 7,258,528 B2
• Filed: 12/02/2004
• Issued: 08/21/2007
• Est. Priority Date: 12/02/2004
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Trindade, Ricardo, Sreekanth, Sri, Djeridane, Toufik, Papple, Michael Leslie Clyde
• Primary Examiner(s): Edgar; Richard A.
• Application Number:
  US11/000,957
• Publication Number:
  US 20060120870A1
• Time in Patent Office: 992 Days
• Field of Search: 416/96.A, 416/224, 416/232, 416/233
• US Class Current: 416/96.00A
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An internally-cooled airfoil for a gas turbine engine, wherein the airfoil comprises at least one substantially chordwise-extending and internally-projecting stiffener located on an internal surface of one of the sidewalls and adjacent to the insert.

Claims

1. An internally-cooled airfoil for a gas turbine engine, the airfoil having at least one internal cooling passage generally located between opposite pressure and suction sidewalls and including an insert therein, the airfoil comprising at least one substantially chordwise-extending and internally-projecting stiffener located on an internal surface of one of the sidewalls and extending towards the insert, the stiffener having two opposite ends and a height less than a distance between the internal surface and the insert at the location of the stiffener such that the stiffener is free from contact with the insert, one end of the stiffener being integral with an adjacent structure extending inwardly from the internal surface and the other end of the stiffener being freestanding.

2. The airfoil as defined in claim 1, wherein the at least one stiffener comprises a plurality of stiffeners provided on both the pressure and suction sidewalls.

3. The airfoil as defined in claim 1, wherein the adjacent structure is a vertically-extending rib projecting from the pressure sidewall to the suction sidewall.

4. The airfoil as defined in claim 1, wherein the adjacent structure is a pedestal.

5. The airfoil as defined in claim 1, wherein the stiffener extends about half the distance between the internal surface and the insert at the location of the stiffener.

6. The airfoil as defined in claim 1, wherein the stiffener has a leading edge-to-trailing edge dimension greater than a root-to-tip dimension of the stiffener, as measured relative to a leading and trailing edge, root and tip of the airfoil.

7. The airfoil as defined in claim 1, further comprising at least two of said stiffners, and wherein the stiffeners are disposed on the internal surface of the sidewall spaced apart from one another and on opposite sides of the sidewall.

9. The airfoil core of claim 4, wherein the stiffener has a leading edge to trailing edge width relative to the airfoil which is greater than a root-to-tip height of the stiffener.

10. The airfoil core of claim 4, wherein the adjacent structure is at least one of a rib and a pedestal.

11. The airfoil core as defined in claim 4, further comprising at least two of said stiffeners, and wherein the stiffeners are disposed on the internal surface of said one of said internal surfaces spaced apart from one another and on opposite sides of an otherwise unsupported section of said one of said internal surfaces.

12. The airfoil core as defined in claim 4, wherein the stiffener extends about half the distance between said one of said internal surfaces and the insert at the location of the stiffener.

13. The airfoil core as defined in claim 4, wherein the adjacent structure is a vertically-extending rib projecting from said one of the internal surfaces of the airfoil core to another of the internal surfaces.

8. An airfoil core for use in a gas turbine engine, the airfoil core having internal surfaces and comprising:

at least one cooling air passage located inside the airfoil core and defined at least in part by the internal surfaces, the passage comprising a cavity for an insert; and

at least one stiffener extending from one of the internal surfaces of the airfoil core defining the cavity for the insert, the stiffener having a height less than a distance from said one of the internal surfaces to the insert when positioned in the cavity, the stiffener having two opposite ends, at least one of which is integrated with an adjacent structure extending from said one of the internal surfaces, the other end of the stiffener being freestanding.