Fan blade grounding tab

Patent metadata

Field	Value
Publication number	US-10107105-B2
Application number	US-201514735770-A
Country	US
Kind code	B2
Filing date	Jun 10, 2015
Priority date	Jun 11, 2014
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

An airfoil for a gas turbine engine is disclosed. The airfoil may include a leading edge, a sheath on the leading edge; and a grounding element connected to the sheath. The grounding element may have a radially extending tab, and may be configured for connection to a component of the gas turbine engine to form a ground path from the sheath to the component.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, comprising:
a first side and an opposite second side extending radially outward from a platform to a tip;
a leading edge;
a sheath on the leading edge;
a root extending radially inward from the platform, the grounding element being disposed on the platform and extending radially inward from the platform to the root, the tab projecting radially outward from the platform; and
a grounding element connected to the sheath, having a radially extending tab, and configured for connection to a component of the gas turbine engine to form a ground path from the sheath to the component.

2. The airfoil of claim 1 , further comprising a collar overlapping the sheath and the tab of the grounding element.

3. The airfoil of claim 2 , wherein the tab is preloaded toward the collar.

4. The airfoil of claim 1 , wherein the sheath overlaps the tab of the grounding element.

5. The airfoil of claim 1 , wherein the grounding element includes a platform cover disposed on a leading edge of the platform, and a strip extending from the platform cover to the root.

6. The airfoil of claim 1 , wherein the root includes a gradual bend from an under side of the platform to the root in order to enhance manufacturability of the strip.

7. The airfoil of claim 1 , wherein the strip extends along a length of a leading edge of the root.

8. The airfoil of claim 1 , wherein the platform cover and the strip comprise a multi-piece configuration.

9. The airfoil of claim 8 , wherein the platform cover includes a slot configured to receive an end of the strip.

10. The airfoil of claim 8 , wherein the platform of the airfoil includes a slot configured to receive an end of the strip.

11. The airfoil of claim 8 , wherein the grounding element further includes a dovetail cap extending from the strip and sized to cover a dovetail portion of a leading edge of the root.

12. The airfoil of claim 11 , wherein the dovetail portion of the leading edge of the root is shaped to fit within the dovetail cap.

13. The airfoil of claim 11 , wherein the platform cover, the strip, and the dovetail cap comprise a three-piece configuration.

14. The airfoil of claim 8 , wherein the strip includes a multi-piece configuration including a first piece extending from the leading edge of the platform to an under side of the platform, and a second piece extending from the under side of the platform to the root.

15. The airfoil of claim 14 , wherein the platform cover includes a multi-piece configuration including a first piece extending circumferentially from a first side of the platform proximate to a centerline of the platform, and a second piece extending circumferentially proximate the centerline of the platform to a second side of the platform.

16. An assembly for a gas turbine engine, comprising:
a fan section;
a compressor section downstream of the fan section;
a combustor section downstream of the compressor section; and
a turbine section downstream of the combustor section, at least one of the fan section, the compressor section, and the turbine section having an airfoil including:
a first side and an opposite second side extending radially outward from a platform to a tip;
a sheath disposed on a leading edge of the airfoil;
a root extending radially inward from the platform; and
a grounding element disposed on a platform of the airfoil and extending radially inward from the platform to the root of the airfoil, the grounding element including a tab projecting radially outward from the platform, the grounding element and the sheath being connected to form a ground path from the sheath to a rotor in the at least one of the fan section, the compressor section, and the turbine section.

17. The assembly of claim 16 , wherein a collar connects the grounding element to the sheath.

18. A method for increasing connectivity between a sheath and a grounding element of an airfoil, the airfoil having a first side and an opposite second side extending radially outward from a platform to a tip;
a root extending radially inward from the platform, the grounding element being disposed on the platform and extending radially inward from the platform to the root, the tab projecting radially outward from the platform, the method comprising:
connecting the sheath of the airfoil to a tab on the grounding element of the airfoil, the tab projecting radially outward from a platform of the airfoil to a predetermined height along a side of the airfoil.

19. The method of claim 18 , further comprising adhering the sheath on top of the tab.

Assignees

• United Technologies Corp

Inventors

• Wilber John E

Classifications

• F01D5/3007

  of axial insertion type · 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

• F02C3/04

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

• F01D5/28

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• F05D2240/303

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