Gas turbine engine airfoil profile

Patent metadata

Field	Value
Publication number	US-10012086-B2
Application number	US-201415034429-A
Country	US
Kind code	B2
Filing date	Nov 4, 2014
Priority date	Nov 4, 2013
Publication date	Jul 3, 2018
Grant date	Jul 3, 2018

Abstract

An example airfoil includes an airfoil body with a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface extending in a radial direction from at least one platform. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to +0.050 inches (+1.27 mm).

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, comprising:
an airfoil body including a leading edge and a trailing edge joined by a pressure side and a suction side spaced apart from said pressure side to provide an external airfoil surface extending in a radial direction from at least one platform; and
wherein said external airfoil surface is formed in conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, said Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location, wherein said local axial chord corresponds to a width of the airfoil between said leading edge and said trailing edge at said span location and said Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to ±0.050 inches (±1.27 mm).

2. The airfoil as recited in claim 1 , wherein the airfoil is a stator vane in a high pressure section of said turbine section.

3. The airfoil as recited in claim 1 , wherein the span location corresponds to a distance from an engine central longitudinal axis.

4. The airfoil as recited in claim 3 , wherein said distance is measured with respect to a reference radius.

5. The airfoil as recited in claim 1 , wherein said airfoil body extends in said radial direction between an inner platform and an outer platform.

6. The airfoil as recited in claim 1 , wherein said tolerance is a manufacturing tolerance of ±0.050 inches (±1.27 mm).

7. The airfoil as recited in claim 1 , wherein said tolerance is a measurement tolerance of ±0.025 inches (±0.635 mm).

8. A gas turbine engine comprising:
a compressor section;
a combustor section fluidly connected to said compressor section;
a turbine section fluidly connected to said combustor section;
wherein said turbine section includes at least one airfoil, wherein said at least one airfoil includes an airfoil body having a leading edge and a trailing edge joined by a pressure side and a suction side that is spaced from said pressure side to provide an external airfoil surface extending in a radial direction from at least one platform; and
wherein said external airfoil surface is formed in conformance with multiple cross-sectional profiles of said at least one airfoil described by a set of Cartesian coordinates set forth in Table 1, said Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location, wherein said local axial chord corresponds to a width of the airfoil between said leading edge and said trailing edge at said span location and said Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to ±0.050 inches (±1.27 mm).

9. The gas turbine engine as recited in claim 8 , wherein said at least one airfoil includes thirty-two airfoils providing a first stage of stator vanes in a high pressure section of said turbine section.

10. The gas turbine engine as recited in claim 8 , wherein said span location corresponds to a distance from an engine central longitudinal axis.

11. The gas turbine engine as recited in claim 10 , wherein said distance is measured with respect to said reference radius.

12. The gas turbine engine as recited in claim 8 , wherein said airfoil body includes a root portion, a mid-span portion and a tip portion.

13. The gas turbine engine as recited in claim 8 , wherein said airfoil body extends in said radial direction between an inner platform and an outer platform.

14. The gas turbine engine as recited in claim 8 , wherein said tolerance is a manufacturing tolerance of ±0.050 inches (±1.27 mm).

15. The gas turbine engine as recited in claim 8 , wherein said tolerance is a measurement tolerance of ±0.025 inches (±0.635 mm).

Assignees

• United Technologies Corp

Inventors

• Pons David M
• Ramirez Loubriel

Classifications

• F01D9/041

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

• F05D2250/711

  convex · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title