Airfoil cooling arrangement

• US 9,109,453 B2
• Filed: 08/15/2012
• Issued: 08/18/2015
• Est. Priority Date: 07/02/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Spangler, Brandon W., Bergman, Russell J.
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): Flores, Juan G
• Application Number:
  US13/585,982
• Publication Number:
  US 20150192021A1
• Time in Patent Office: 1,098 Days
• US Class Current: 1/1
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F05D 2240/121 related to the leading edge of a stator vane
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An airfoil includes a leading edge, a trailing edge, a pressure side surface extending from the leading edge to the trailing edge, a suction side surface extending from the leading edge to the trailing edge and generally opposite the pressure side surface and a plurality of cooling holes. The cooling holes are positioned on the airfoil in accordance with X, Y and Z Cartesian coordinate values set forth in an accompanying Table.

Claims

1. An airfoil comprising:

a leading edge;

a trailing edge;

a pressure side surface extending from the leading edge to the trailing edge;

a suction side surface extending from the leading edge to the trailing edge and generally opposite the pressure side surface;

a plurality of cooling holes positioned on the airfoil in accordance with X, Y and Z Cartesian coordinate values set forth in Table I.

2. The airfoil of claim 1, wherein the plurality of cooling holes includes both circular and conical holes.

3. The airfoil of claim 2, wherein the conical holes have a maximum diameter at an outer surface of the airfoil.

4. The airfoil of claim 1, wherein the airfoil is a component of a vane and extends between an inner diameter platform and an outer diameter platform.

5. The airfoil of claim 4, wherein the airfoil is located in a high pressure turbine section of a gas turbine engine.

6. The airfoil of claim 5, wherein the vane is a first stage turbine vane.

7. A gas turbine engine comprising:

a plurality of vanes, each vane extending from an inner platform to an outer platform and comprising;

an airfoil having leading and trailing edges and pressure and suction side surfaces; and

a plurality of cooling holes located on the airfoil, wherein the plurality of cooling holes are positioned on the airfoil in accordance with X, Y and Z Cartesian coordinate values set forth in Table I.

8. The gas turbine engine of claim 7, wherein the plurality of vanes are located in a high pressure turbine section of the gas turbine engine.

9. The gas turbine engine of claim 8, wherein the plurality of vanes are first stage turbine vanes.

10. The gas turbine engine of claim 7, wherein the plurality of cooling holes includes both circular and conical holes.

11. The gas turbine engine of claim 10, wherein the conical holes have a maximum diameter at an outer surface of the airfoil.