Methods for treating field operated components

Patent metadata

Field	Value
Publication number	US-2016376893-A1
Application number	US-201514752186-A
Country	US
Kind code	A1
Filing date	Jun 26, 2015
Priority date	Jun 26, 2015
Publication date	Dec 29, 2016
Grant date	—

Abstract

A method for treating a field operated component is disclosed which includes providing the component including a ceramic matrix composite and removing a first portion of the component, forming a first exposed surface on the component. The method further includes providing a second portion including the composite, the second portion having a second exposed surface including a conformation adapted to mate with the first exposed surface. The second portion is positioned in association with the component so as to replace the first portion, and the second portion and the component are joined to form a treated component. Another method is disclosed wherein the component is a turbine component which further includes removing an environmental barrier coating from the component, arranging and conforming the first exposed surface and the second exposed surface to define a joint, and applying an environmental barrier coating to the treated component.

First claim

What is claimed is:

1 . A method for treating a field operated component, the method comprising:
providing the field operated component including a ceramic matrix composite; removing a first portion of the field operated component, forming a first exposed ceramic matrix composite surface on the field operated component; providing a second portion including the ceramic matrix composite, the second portion having a second exposed ceramic matrix composite surface including a conformation adapted to mate with the first exposed ceramic matrix composite surface; positioning the second portion in association with the field operated component so as to replace the first portion; and joining the second portion and the field operated component to form a treated component.

2 . The method of claim 1 , wherein the field operated component is a gas turbine component.

3 . The method of claim 1 , wherein the second portion is selected from the group consisting of a repurposed portion of another field operated component, a repurposed portion from a non-operated component, an incomplete component and combinations thereof.

4 . The method of claim 1 , wherein joining the second portion and the field operated component includes applying a joining material to at least one of the first exposed ceramic matrix composite surface and the second exposed ceramic matrix composite surface.

5 . The method of claim 4 , wherein the joining material includes a material selected from the group consisting of a carbon source, elemental carbon, a hydrocarbon, an alcohol, silicon carbide, and a combination thereof.

6 . The method of claim 4 , wherein joining the second portion and the field operated component includes drying the joining material under a vacuum.

7 . The method of claim 1 , wherein joining the second portion and the field operated component includes adding at least one matrix ply over a joint defined by the first exposed ceramic matrix composite surface and the second exposed ceramic matrix composite surface.

8 . The method of claim 7 , wherein at least one layer of unidirectional tape is disposed between the at least one matrix ply and the joint.

9 . The method of claim 8 , wherein the at least one layer of unidirectional tape includes a plurality of alternating layers of unidirectional ceramic matrix composite tape, each of the plurality of alternating layers alternating fiber orientation at 90° intervals.

10 . The method of claim 8 , wherein joining the second portion and the field operated component includes densifying the at least one matrix ply, the at least one layer of unidirectional tape, the second portion and the field operated component.

11 . The method of claim 8 , wherein adding the at least one matrix ply includes forming an inset depth about equal to a height of the at least one matrix ply and the at least one layer of unidirectional tape.

12 . The method of claim 1 , wherein the first exposed ceramic matrix composite surface and the second exposed ceramic matrix composite surface are arranged and conformed to define a joint.

13 . The method of claim 12 , wherein the joint is selected from the group consisting of a scarf joint, a plain scarf joint, a nibbed scarf joint, a keyed nibbed scarf joint, and combinations thereof.

14 . The method of claim 13 , wherein the joint includes a w/t ratio between about 0 to about 50.

15 . The method of claim 1 , wherein joining the second portion and the field operated component includes a technique selected from the group consisting of autoclaving, burning out, melt infiltration, local heat treatment, inductive heating, laser heating, and combinations thereof.

16 . The method of claim 1 , wherein the method further includes removing a first environmental barrier coating from the field operated component.

17 . The method of claim 1 , wherein the method further includes applying a second environmental bond coating to the treated component.

18 . The method of claim 1 , wherein the method further includes machining a surface of the treated component.

19 . A method for treating a field operated turbine component, the method comprising:
providing the field operated turbine component selected from the group consisting of a shroud, a turbine strut, a nozzle, a combustion liner, a bucket, a shroud ring, an exhaust duct, an augmentation liner, a jet exhaust nozzle, and combinations thereof, the field operated turbine component including a ceramic matrix composite; removing a first environmental barrier coating from the field operated turbine component; removing a first portion of the field operated turbine component, forming a first exposed ceramic matrix composite surface on the field operated turbine component; providing a second portion including the ceramic matrix composite, the second portion having a second exposed ceramic matrix composite surface including a conformation adapted to mate with the first exposed ceramic matrix composite surface; positioning the second portion in association with the field operated turbine component so as to replace the first portion, the first exposed ceramic matrix composite surface and the second exposed ceramic matrix composite surface being arranged and conformed to define a joint; joining the second portion and the field operated turbine component to form a treated turbine component; and applying a second environmental barrier coating to the treated turbine component.

20 . The method of claim 19 , wherein the second portion is selected from the group consisting of a repurposed portion of another field operated turbine component, a repurposed portion from a non-operated turbine component, an incomplete turbine component and combinations thereof.

Assignees

• Gen Electric

Inventors

• Hardwicke Canan Uslu
• Delvaux John Mcconnell
• Parolini Jason Robert
• Hafner Matthew Troy

Classifications

• B23P6/005 Primary

  using only replacement pieces of a particular form · CPC title

• B29L2031/7504

  Turbines · CPC title

• B29C65/02

  by heating, with or without pressure · CPC title

• F01D5/14 Primary

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• B29C65/002

  Joining methods not otherwise provided for · CPC title