Method for replacing metal airfoil with ceramic airfoil, and related turbomachine blade

Patent metadata

Field	Value
Publication number	US-10907484-B2
Application number	US-201916270071-A
Country	US
Kind code	B2
Filing date	Feb 7, 2019
Priority date	Feb 7, 2019
Publication date	Feb 2, 2021
Grant date	Feb 2, 2021

Abstract

A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.

First claim

What is claimed is:

1. A method, comprising:
in a used metal turbomachine blade including a root having a shank, a platform coupled to the shank and an airfoil coupled to the platform:
removing the airfoil, leaving a remaining base including an entirety of the platform and the root with an entirety of the shank;
forming a radially extending opening in a surface of the platform, through the platform, and into the shank;
inserting a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base; and
fixedly attaching the ceramic airfoil to the remaining base to form a repaired turbomachine blade.

2. The method of claim 1 , further comprising forming at least one connector opening through the shank, the connector opening configured to receive a connector therein.

3. The method of claim 2 , wherein the ceramic shank nub includes at least one connector opening therein configured to receive the connector, and wherein fixedly attaching the ceramic airfoil to the remaining base includes inserting a connector through each connector opening in the shank and each connector opening in the ceramic shank nub.

4. The method of claim 3 , wherein the at least one connector opening in the shank includes a first connector opening in a first face of the shank and a corresponding, second connector opening in a second, opposing face of the shank.

5. The method of claim 2 , further comprising fixating each connector in place relative to the shank.

6. The method of claim 5 , wherein fixating each connector includes deforming a portion of each connector.

7. The method of claim 5 , wherein fixating each connector includes attaching a fixating fastener to each connector.

8. The method of claim 1 , further comprising, after removing the airfoil, removing any remnants of the airfoil remaining on the platform, leaving the remaining base including the entirety of the platform and the root with the entirety of the shank.

9. The method of claim 1 , wherein after removing the airfoil, the platform remains intact and an upper surface of the platform remains holeless, and wherein the radially extending opening is formed in the holeless upper surface of the platform, through the platform, and into the shank.

10. The method according to claim 1 , wherein the radially extending opening is formed by electrical discharge machining, laser cutting, and/or machining.

Assignees

• Gen Electric

Inventors

• Hafner Matthew Troy
• Delvaux John Mcconnell
• Farrell Thomas Raymond
• Feigl Markus

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D5/3053 Primary

  by means of pins · CPC title

• F05D2230/80

  Repairing, retrofitting or upgrading methods · CPC title

• F01D5/3084

  the blades being made of ceramics · CPC title

• F01D5/005 Primary

  Repairing methods or devices · CPC title