Airfoil for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016258296-A1
Application number	US-201514635243-A
Country	US
Kind code	A1
Filing date	Mar 2, 2015
Priority date	Mar 2, 2015
Publication date	Sep 8, 2016
Grant date	—

Abstract

A component for a gas turbine engine includes an airfoil that has a first end. A first platform is located at the first end of the airfoil. A compound fillet includes a first fillet portion tangent to the first platform and an airfoil offset. A second fillet portion is tangent to a surface of the airfoil and the first fillet portion.

First claim

What is claimed is:

1 . A component for a gas turbine engine comprising:
an airfoil having a first end; a first platform located at the first end of the airfoil; and a compound fillet including a first fillet portion tangent to the first platform and an airfoil offset and a second fillet portion tangent to a surface of the airfoil and the first fillet portion.

2 . The component of claim 1 , wherein the airfoil offset is a surface extending generally parallel to the airfoil.

3 . The component of claim 1 , wherein the first fillet portion has a first radius and the second fillet portion has a second radius that is greater than the first radius.

4 . The component of claim 1 , wherein the first fillet portion includes a radius of approximately 0.125 inches, the second fillet portion includes a radius of approximately 0.700 inches, and the airfoil offset is spaced from the airfoil approximately 0.022 inches.

5 . The component of claim 1 , further comprising a single fillet located at an intersection of the first end and the first platform and spaced from the compound fillet.

6 . The component of claim 5 , further comprising a transition fillet located at the intersection of the first end and the first platform axially between the compound fillet and the single fillet.

7 . The component of claim 5 , wherein the compound fillet extends from approximately 23% to 32% of the axial chord length from the leading edge of the airfoil on a pressure side of the airfoil around the leading edge of the airfoil and to approximately 15% to 25% of the axial chord length from the leading edge on a suction side of the airfoil.

8 . The component of claim 7 , wherein the compound fillet extends from approximately 28% of the axial chord length from the leading edge on the pressure side around the leading edge of the airfoil and to approximately 20% of the axial chord length from the leading edge on the suction side.

9 . The component of claim 7 , wherein the single fillet extend from approximately 48% of the axial chord length from the leading edge on the pressure side around the trailing edge of the airfoil to approximately 50% of the axial chord length from the leading edge on the suction side.

10 . The component of claim 1 , wherein the airfoil is a vane and includes a second platform located at a second end of the airfoil and a second compound fillet located at an intersection of the second end and the second platform.

11 . The component of claim 1 , wherein the first fillet portion is tangent to a radially outer surface of the first platform.

12 . A gas turbine engine comprising:
an airfoil located in one of a compressor section or a turbine section; a first platform attached to the airfoil; a compound fillet including a first fillet portion tangent to the first platform and an airfoil offset and a second fillet portion tangent to a surface of the airfoil and the first fillet portion.

13 . The gas turbine engine of claim 12 , wherein the airfoil offset is a surface extending generally parallel to the airfoil.

14 . The gas turbine engine of claim 12 , wherein the first fillet portion has a first radius and the second fillet portion has a second radius that is greater than the first radius.

15 . The gas turbine engine of claim 12 , further comprising a single fillet located at an intersection of the airfoil and the first platform and spaced from the compound fillet.

16 . The gas turbine engine of claim 12 , wherein the airfoil is a vane and includes a second platform attached to the airfoil and a second compound fillet located at an intersection of the airfoil and the second platform.

17 . A method of forming an airfoil comprising:
locating a platform relative to an airfoil; forming a first fillet portion tangent to the platform and an airfoil offset; and forming a second fillet portion tangent to the first fillet portion and a surface of the airfoil.

18 . The method of claim 17 , wherein the airfoil offset is a surface extending generally parallel to the airfoil.

19 . The method of claim 17 , wherein the first fillet portion has a first radius and the second fillet portion has a second radius that is greater than the first radius.

20 . The method of claim 17 , further comprising a single fillet located at an intersection of the airfoil and the first platform and spaced from the compound fillet.

Assignees

• United Technologies Corp

Inventors

• Bergman Russell J
• Parkin Jess J

Classifications

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2230/50

  Building or constructing in particular ways · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F05D2220/32

  in gas turbines · CPC title