Ductile alloys for sealing modular component interfaces

Patent metadata

Field	Value
Publication number	US-9726028-B2
Application number	US-201113171699-A
Country	US
Kind code	B2
Filing date	Jun 29, 2011
Priority date	Jun 29, 2011
Publication date	Aug 8, 2017
Grant date	Aug 8, 2017

Abstract

A vane assembly ( 10 ) having: an airfoil ( 12 ) and a shroud ( 14 ) held together without metallurgical bonding there between; a channel ( 22 ) disposed circumferentially about the airfoil ( 12 ), between the airfoil ( 12 ) and the shroud ( 14 ); and a seal ( 20 ) disposed in the channel ( 22 ), wherein during operation of a turbine engine having the vane assembly ( 10 ) the seal ( 20 ) has a sufficient ductility such that a force generated on the seal ( 20 ) resulting from relative movement of the airfoil ( 12 ) and the shroud ( 14 ) is sufficient to plastically deform the seal ( 20 ).

First claim

The invention claimed is:

1. A vane assembly comprising:
an airfoil and a shroud held together without metallurgical bonding there between;
a channel disposed circumferentially about the airfoil, between the airfoil and the shroud;
a seal disposed in the channel, wherein during operation of a turbine engine comprising the vane assembly the seal comprises a sufficient ductility such that a force generated on the seal resulting from relative movement of the airfoil and the shroud is sufficient to plastically deform the seal; and
wherein the shroud is monolithic, the vane assembly further comprising interlocking features of the airfoil and the shroud that hold the airfoil and the shroud together.

2. The vane assembly of claim 1 , wherein the airfoil and the shroud comprise sufficient structural integrity to operate without the seal.

3. The vane assembly of claim 1 , wherein the relative movement causes seal material to move from an area of decreased channel volume to an area of increased channel volume.

4. The vane assembly of claim 1 , wherein the channel is formed in only one of the airfoil or the shroud.

5. The vane assembly of claim 1 , wherein the channel comprises a groove in the airfoil and an associated groove in the shroud.

6. The vane assembly of claim 1 , wherein the channel spans less than an entire perimeter of the airfoil.

7. The vane assembly of claim 6 , wherein an ungrooved area of the airfoil between ends of the channel is disposed on a suction side of the airfoil.

8. The vane assembly of claim 1 , wherein the seal comprises a seal material comprising a Young's modulus of no more than approximately 220 GPa (20 million psi) at 800° C.

9. The vane assembly of claim 1 , wherein the seal comprises a seal material comprising a creep rate of no less than 0.001 s−1 at a temperature of 800° C. with an applied stress of 500 MPa.

10. The vane assembly of claim 1 , wherein the seal comprises a seal material comprising a melting temperature not greater than twice an operating temperature of the seal.

11. The vane assembly of claim 10 , wherein the seal operating temperature is 500° C.±100° C.

12. The vane assembly of claim 1 , wherein the seal comprises aluminum, aluminum alloys, tin, tin alloys, pure nickel, bronze, or brass.

Assignees

• Marra John J
• Wessell Brian J
• James Allister W
• Marsh Jan H
• Gear Paul J
• Siemens Energy Inc

Inventors

• Marra John J
• Wessell Brian J
• James Allister W
• Marsh Jan H
• Gear Paul J

Classifications

• F01D11/006

  Sealing the gap between rotor blades or blades and rotor · CPC title

• F05D2300/518

  Ductility · CPC title

• B22D19/0072

  for making objects with integrated channels · CPC title

• F01D9/042 Primary

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F05D2300/10

  Metals, alloys or intermetallic compounds · CPC title