Turbine vane cooling arrangement

Patent metadata

Field	Value
Publication number	US-9803488-B2
Application number	US-201514590317-A
Country	US
Kind code	B2
Filing date	Jan 6, 2015
Priority date	Jan 29, 2014
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

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.

First claim

What is claimed is:

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.

Assignees

• United Technologies Corp

Inventors

• Riley Sarah
• Anderson Kristopher K

Classifications

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2260/202

  by film cooling · CPC title