Airfoil with break-way, free-floating damper member

Patent metadata

Field	Value
Publication number	US-9249668-B2
Application number	US-201213454183-A
Country	US
Kind code	B2
Filing date	Apr 24, 2012
Priority date	Apr 24, 2012
Publication date	Feb 2, 2016
Grant date	Feb 2, 2016

Abstract

An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

First claim

What is claimed is:

1. An airfoil comprising:
an airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining a cavity in the airfoil body; and
a damper member enclosed in the cavity, the damper member being free-floating within the cavity, wherein the damper member includes a vestigial joint structure and the airfoil body includes a corresponding vestigial joint structure.

2. The airfoil as recited in claim 1 , wherein the damper member is elongated.

3. The airfoil as recited in claim 1 , wherein the damper member has a geometric cross-sectional shape.

4. The airfoil as recited in claim 1 , wherein the damper member includes a fractured surface at one end thereof.

5. The airfoil as recited in claim 1 , wherein the damper member includes a terminal end and a narrow protuberance at the terminal end.

6. An airfoil comprising:
an airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining a cavity in the airfoil body; and
a damper member enclosed in the cavity, the damper member being connected to the body in a break-away joint, wherein the minimum cross-sectional area of the break-away joint is less than a critical cross-sectional area needed to support the mass of the damper member during rotation of the airfoil body.

7. The airfoil as recited in claim 6 , wherein the break-away joint has a minimum cross-sectional area and the damper member has a minimum cross-sectional area, and the minimum cross-sectional area of the break-away joint is less than a minimum cross-sectional area of the damper member.

8. The airfoil as recited in claim 6 , wherein the break-away joint is located at a terminal end of the damper member.

9. The airfoil as recited in claim 6 , wherein the break-away joint is an exclusive connection between the damper member and the airfoil body.

10. The airfoil as recited in claim 6 , wherein the damper member is free of any contact with the airfoil body, exclusive of the break-away joint.

11. A turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, the turbine section being coupled to drive the compressor section and the fan, and
at least one of the fan, the compressor section and the turbine section including an airfoil having an airfoil body including a body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining a cavity in the body and a damper member enclosed in the cavity, the damper member being free-floating within the cavity, wherein the damper member includes a vestigial joint structure and the airfoil body includes a corresponding vestigial joint structure.

12. The turbine engine as recited in claim 11 , wherein the vestigial structure of the damper member includes a fractured surface at one end thereof.

13. The turbine engine as recited in claim 11 , wherein the damper member is elongated.

14. The turbine engine as recited in claim 11 , wherein the damper member has a geometric cross-sectional shape.

15. A method for processing an airfoil, the method comprising:
depositing multiple layers of a powdered metal onto one another;
joining the layers to one another with reference to data relating to a particular cross-section of an airfoil; and
producing the airfoil with a body including an airfoil body including a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall, the first side wall and the second side wall joining the leading edge and the trailing edge and at least partially defining a cavity in the airfoil body, and a damper member enclosed in the cavity, the damper member being connected to the body in a break-away joint, wherein the minimum cross-sectional area of the break-away joint is less than a critical cross-sectional area needed to support the mass of the damper member during rotation of the airfoil body.

16. The airfoil as recited in claim 1 , wherein the vestigial structure of the damper member and the corresponding vestigial structure of the airfoil body each include a fractured surface.

17. The airfoil as recited in claim 16 , wherein the vestigial structure of the damper member is a narrow protuberance located at a terminal end of the damper member.

18. The airfoil as recited in claim 16 , wherein the vestigial structure of the damper member is located at a radially inboard end of the damper member.

19. The airfoil as recited in claim 16 , wherein the fractured surfaces have topological features that are characteristic of a ductile break, a brittle break, or combination thereof.

Assignees

• Fisk Benjamin T
• Propheter-Hinckley Tracy A
• Dolansky Gregory M
• Houston David P
• Tracy Anita L
• United Technologies Corp

Inventors

• Fisk Benjamin T
• Propheter-Hinckley Tracy A
• Dolansky Gregory M
• Houston David P
• Tracy Anita L

Classifications

• F01D5/16 Primary

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