Turbine blade with reverse cooling air film hole direction

• US 7,712,316 B2
• Filed: 01/09/2007
• Issued: 05/11/2010
• Est. Priority Date: 01/09/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Spangler, Brandon W.
• Primary Examiner(s): Cuff; Michael
• Assistant Examiner(s): Wongwian; Phutthiwat
• Application Number:
  US11/651,226
• Publication Number:
  US 20080163604A1
• Time in Patent Office: 1,218 Days
• Field of Search: 60754-757, 608/06, 415/115, 415/116, 416/97.A, 416/97.R, 416/96.R
• US Class Current: 60/806
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F05D 2250/52 Outlet

Abstract

A gas turbine engine includes turbine blades having film cooling holes at an outer face of an airfoil wherein the film cooling holes are designed to be better filled with air. In a disclosed embodiment, the film cooling holes include a meter section extending along a direction having a main component extending from a blade tip to a blade root. In addition, a diffused section communicates with the meter section at a face of the airfoil. The diffused section is spaced toward the blade tip from the meter section. In this manner, centrifugal force ensures the diffused section is also filled with air.

Claims

1. A turbine blade comprising:

a root, and an airfoil extending away from the root to a tip;

a plurality of film cooling holes on an outer face of the airfoil, said airfoil having at least one internal cooling passage for receiving air from a source, and delivering air to said film cooling holes, and said plurality of film holes being formed in an array, with there being film holes spaced at different locations in a direction between a trailing edge and a leading edge of the airfoil, and also at different locations between the root and the tip of the airfoil; and

said film cooling holes receiving air from said cooling passage through meter sections extending with a component in a direction from the tip towards the root, said meter sections extend at a first angle, with an extension of said meter section extending through to an outer wall of said airfoil, said meter sections communicating directly with said cooling passage and a diffused section of an outer end of said film cooling holes extending towards said tip from the meter section, said diffused section is formed at a different angle having a lesser component in the direction from said tip toward said root than said meter extending at.

2. The turbine blade as set fourth in claim 1, wherein said diffused section is formed along an angle having a lesser component in the direction from said tip toward said root than said meter section.

3. The turbine blade as set forth in claim 1, wherein said meter section extends from said cooling passage initially at said direction.

4. The turbine blade as set forth in claim 3, wherein said meter section extends along a single angle from said cooling passage to said outer wall of said outer face of the airfoil.

5. The turbine blade as set forth in claim 1, wherein said away of cooling holes is formed on a pressure side of said airfoil.

9. The turbine blade as set forth in claim 5, wherein said meter sections each extend along a single angle from said cooling passage to said outer wall of said outer face of the airfoil.

6. A turbine blade comprising:

a root, and an airfoil extending away from the root toward a tip;

a plurality of film cooling holes on an outer face of said airfoil, said airfoil having at least one internal cooling passage for receiving air from a source, and delivering air to said film cooling holes, and said plurality of film holes being formed in an array, with there being film holes spaced at different locations in a direction between a trailing edge and a leading edge of the airfoil, and also at different locations between the root and the tip of the airfoil; and

said film cooling holes receiving air from said internal cooling passage through meter sections that extend with a component in a direction from said tip toward said root at a first angle, and a diffused section of an outer end of said film cooling holes communicates with said meter section, said diffused section extending towards said tip from said meter section and at a different angle than said meter section.

7. The turbine blade as set forth in claim 6, wherein said diffused section is formed along an angle having a lesser component in the direction from said tip toward said root than said meter section.

8. The turbine blade as set forth in claim 6, wherein said meter section extends from said cooling passage initially at said direction.

10. The turbine blade as set forth in claim 6, wherein said away of cooling holes is formed on a pressure side of said airfoil.