Compound fillet for a gas turbine airfoil

Patent metadata

Field	Value
Publication number	US-9920633-B2
Application number	US-201514635243-A
Country	US
Kind code	B2
Filing date	Mar 2, 2015
Priority date	Mar 2, 2015
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

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;
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; and
a single fillet region having a single fillet separated from the compound fillet by a transition fillet region having a transition fillet, wherein the single fillet includes a radius larger than the radius of the first fillet portion and smaller than a radius of the second 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 , wherein the single fillet is located at an intersection of the first end and the first platform and spaced from the compound fillet.

6. The component of claim 5 , wherein the transition fillet is 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 23% to 32% of an 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 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 28% of the axial chord length from the leading edge on the pressure side around the leading edge of the airfoil and to 20% of the axial chord length from the leading edge on the suction side.

9. The component of claim 7 , wherein the single fillet extends from 48% of the axial chord length from the leading edge on the pressure side around the trailing edge of the airfoil to 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; and
a single fillet region having a single fillet separated from the compound fillet by a transition fillet region having a transition fillet, wherein the single fillet includes a radius larger than the radius of the first fillet portion and smaller than a radius of the second 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 , wherein the single fillet region is 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 compound fillet with a first fillet portion tangent to the platform and an airfoil offset and a second fillet portion tangent to the first fillet portion and a surface of the airfoil; and
forming a single fillet region having a single fillet separated from the compound fillet by a transition fillet region having a transition fillet, wherein the single fillet includes includes a radius larger than the radius of the first fillet portion and smaller than the radius of the second fillet portion.

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 , wherein the single fillet is 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

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2240/121

  related to the leading edge of a stator vane · 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

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title