TURBINE AIRFOIL SEGMENT HAVING FILM COOLING HOLE ARRANGEMENT

• US 20160160654A1
• Filed: 11/30/2015
• Published: 06/09/2016
• Est. Priority Date: 12/08/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Ennacer, Mohammed, Bergman, Russell J., Moran, Jason B.
• Granted Patent: US 10,443,434 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2240/81 Cooled platforms
• 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

A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. At least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).

Claims

1. A turbine airfoil segment comprising:

inner and outer platforms that are joined by at least one airfoil, the at least one airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface, and at least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).

2. The turbine airfoil segment as recited in claim 1, wherein the external breakout points of the film cooling holes of the outer platform are located in substantial conformance with the Cartesian coordinates set forth in Table 1 and the external breakout points of the film cooling holes of the inner platform are located in substantial conformance with the Cartesian coordinates set forth in Table 2.

3. The turbine airfoil segment as recited in claim 2, wherein the film cooling holes are conical holes.

4. The turbine airfoil segment as recited in claim 1, wherein spacing between edges of adjacent cooling holes is at least 0.015 inch (0.38 mm).

5. The turbine airfoil segment as recited in claim 1, wherein the film cooling holes have a diameter of 0.010-0.035 inch (0.25-0.89 mm).

6. A gas turbine engine comprising:

a compressor section;

a combustor fluidly connected to the compressor section;

a turbine section fluidly connected to the combustor, the turbine section includes an array of turbine airfoil segments, each turbine airfoil segment comprising;

inner and outer platforms that are joined by at least one airfoil, the at least one airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface, and at least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).

7. The gas turbine engine as recited in claim 6, wherein the external breakout points of the film cooling holes of the outer platform are located in substantial conformance with the Cartesian coordinates set forth in Table 1 and the external breakout points of the film cooling holes of the inner platform are located in substantial conformance with the Cartesian coordinates set forth in Table 2.

8. The gas turbine engine as recited in claim 7, wherein the film cooling holes are conical holes.

9. The gas turbine engine as recited in claim 6, wherein spacing between edges of adjacent cooling holes is at least 0.015 inch (0.38 mm).

10. The gas turbine engine as recited in claim 6, wherein the film cooling holes have a diameter of 0.010-0.035 inch (0.25-0.89 mm).