Turbine vane cooling arrangement

• US 9,803,488 B2
• Filed: 01/06/2015
• Issued: 10/31/2017
• Est. Priority Date: 01/29/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Riley, Sarah, Anderson, Kristopher K.
• Primary Examiner(s): Wiehe, Nathaniel
• Assistant Examiner(s): Peters, Brian O
• Application Number:
  US14/590,317
• Publication Number:
  US 20150211376A1
• Time in Patent Office: 1,029 Days
• CPC Class Codes: F01D 25/12 Cooling
• 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: 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 vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

Claims

1. A vane comprising:

a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of said airfoils, wherein each of said plurality of film cooling holes break through said exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1, wherein each of said geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane; and

wherein said Cartesian coordinate values of Table 1 are expressed in inches.

2. The vane as recited in claim 1, wherein said reference point includes a pin hole of said platform.

3. The vane as recited in claim 1, wherein said plurality of film cooling holes are spaced along a span of said airfoil body in multiple collinearly aligned rows.

4. The vane as recited in claim 1, wherein said plurality of film cooling holes are disposed on a pressure side, a suction side and a leading edge of said airfoil body.

5. The vane as recited in claim 1, wherein a first portion of said plurality of film cooling holes from a point of said airfoil body toward an outer platform are angled toward said outer platform and a second portion of said plurality of film cooling holes from said point toward an inner platform are angled inwardly toward said inner platform.

6. The vane as recited in claim 1, wherein the airfoils extend between inner and outer platforms, the inner and outer platforms include another plurality of film cooling holes that extend through an exterior surface of said platforms, wherein each of said other plurality of film cooling holes break through said exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 2, wherein each of said geometric coordinates is measured from the reference point;

and wherein said Cartesian coordinate values of Table 2 are expressed in inches.

7. A vane comprising:

a pair of airfoils extending between inner and outer platforms, the inner and outer platforms include a plurality of film cooling holes that extend through an exterior surface of said platforms, wherein each of said plurality of film cooling holes break through said exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 2, wherein each of said geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane; and

wherein said Cartesian coordinate values of Table 2 are expressed in inches.

8. The vane as recited in claim 7, wherein said reference point includes a pin hole of said platform.