AIRFOIL INCLUDING MEMBER CONNECTED BY ARTICULATED JOINT

• US 20130276456A1
• Filed: 04/24/2012
• Published: 10/24/2013
• Est. Priority Date: 04/24/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Propheter-Hinckley, Tracy A., Tracy, Anita L.
• Granted Patent: US 9,175,570 B2
• Time in Patent Office: Days
• US Class Current: 60/805
• CPC Class Codes: B22F 10/28 Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• CPC Class Codes: B22F 5/04 of turbine blades
• CPC Class Codes: B22F 7/08 with one or more parts not made from powder B22F7/062 takes precedence
• CPC Class Codes: F01D 5/22 Blade-to-blade connections, e.g. for damping vibrations
• CPC Class Codes: F01D 5/26 Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
• CPC Class Codes: Y02P 10/25 Process efficiency
• CPC Class Codes: Y10T 29/49316 Impeller making

Abstract

An airfoil includes a body that has a platform, an airfoil extending outwardly from a side of the platform and a root extending outwardly from another side of the platform. A member is connected in an articulated joint to the body.

Claims

1. An airfoil comprising:

a body including a platform, an airfoil extending outwardly from a side of the platform and a root extending outwardly from another side of the platform; and

a member connected in an articulated joint to the body.

2. The airfoil as recited in claim 1, wherein the member includes a body extending adjacent the platform.

3. The airfoil as recited in claim 1, wherein the articulated joint includes a socket and a socket member movably interlocked with the socket.

4. The airfoil as recited in claim 3, wherein the socket is fixed on the root.

5. The airfoil as recited in claim 3, wherein the body defines a longitudinal axis and the socket is longitudinally elongated relative to the longitudinal axis.

6. The airfoil as recited in claim 3, wherein the body defines a longitudinal axis and the socket member is longitudinally elongated relative to the longitudinal axis.

7. The airfoil as recited in claim 3, wherein the member is a damper member including a damper body extending adjacent the platform, and the socket includes socket sidewalls that define an opening through which the damper body of the damper member extends.

8. The airfoil as recited in claim 7, wherein the opening is smaller than the socket member such that the socket member cannot fit through the opening.

9. The airfoil as recited in claim 3, wherein the articulated joint includes an open gap between the socket and the socket member.

10. The airfoil as recited in claim 3, wherein the socket member is irremovably interlocked with the socket such that the socket member cannot be removed from the socket non-destructively.

11. The airfoil as recited in claim 3, wherein the socket is a slot and the socket member is a button having a shank and enlarged head on the shank.

12. The airfoil as recited in claim 1, wherein the member is a damper member including a damper body extending adjacent the platform, and the body defines a longitudinal axis and the damper body of the damper member includes an inclined bearing surface relative to the longitudinal axis.

13. The airfoil as recited in claim 1, further including a first buttress wall extending outwardly from the platform to the root and a second buttress wall extending outwardly from the platform to the root, the first buttress wall being spaced apart from the second buttress wall and the member being connected in a first articulated joint to the first buttress wall and in a second articulated joint to the second buttress wall.

14. The airfoil as recited in claim 1, wherein the member includes a body extending adjacent the platform, the body including a seal surface abutting the platform.

15. The airfoil as recited in claim 14, wherein the body has a uniform through-thickness.

16. A turbine engine comprising:

optionally, a fan;

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 a body including a platform, an airfoil extending outwardly from a side of the platform and a root extending outwardly from another side of the platform, and a member connected in an articulated joint to the body.

17. 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 a platform, an airfoil extending outwardly from a side of the platform and a root extending outwardly from another side of the platform, and a member connected in an articulated joint to the body.

18. A method for processing an airfoil, the method comprising:

providing an airfoil that includes a body having a platform, an airfoil extending outwardly from a side of the platform and a root extending outwardly from another side of the platform;

providing a damper member including a damper body; and

forming an articulated joint to connect the body and a damper member together such that the damper body extends adjacent the platform.

19. The method as recited in claim 18, wherein the forming includes depositing multiple layers of a powdered metal onto one another and joining the layers to one another with reference to data relating to a particular cross-section of the articulated joint.

20. The method as recited in claim 18, further including destructively removing at least a portion of a prior articulated joint of the airfoil and, in place of the prior articulated joint, forming the articulated joint.