# US 6,345,441 B1 · Method of repairing combustion chamber liners

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- Number: US 6,345,441 B1
- Document ID: US6345441B1
- Status: Granted
- Kind: B1
- Application number: 09/618,379
- Filed: 2000-07-18
- Granted: 2002-02-12
- Earliest claimed: 2000-07-18
- Assignees: General Electric Company
- Inventors: Gilbert Farmer; James Michael Caldwell; Steven Allen Stiverson; David Bruce Patterson; Edward John Emilianowicz
- Web page: https://patentgrep.com/patent/US6345441B1

## CPC

- B23P 6/005: {using only replacement pieces of a particular form}
- F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)}
- B23P 2700/13: Parts of turbine combustion chambers
- F23R 2900/00019: Repairing or maintaining combustion chamber liners or subparts
- Y10T 29/49318: Repairing or disassembling
- Y10T 29/4932: Turbomachine making
- Y10T 29/49737: Metallurgically attaching preform
- B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q)
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A method of repairing an annular transpiration cooled liner for a combustion chamber of a gas turbine engine. An annular portion of the liner including a damaged region is removed from between an upstream section and a downstream section of the liner. Sheet metal is formed into an annular replacement section having at least one axial seam extending between an upstream end and a downstream end of the replacement section. The replacement section is sized and shaped similarly to the removed annular portion of the liner. The upstream end of the formed annular section is joined to the upstream section of the liner and the downstream end of the formed annular section is joined to the downstream section of the liner.

## Claims

### Claim 1

A method of repairing a damaged annular transpiration cooled liner of a gas turbine engine combustion chamber comprising the steps of:
removing an annular portion of the liner including a damaged region from between an upstream section and a downstream section of the liner;
forming sheet metal into an annular replacement section having at least one axial seam extending between an upstream end of the replacement section and a downstream end opposite said upstream end, the replacement section being sized and shaped similarly to said removed annular portion of the liner;
joining the upstream end of the formed annular replacement section to said upstream section of the liner; and
joining the downstream end of the formed annular replacement section to said downstream section of the liner.

### Claim 2 (depends on 1)

A method as set forth in claim 1 wherein the seam is formed by electron beam welding.

### Claim 3 (depends on 1)

A method as set forth in claim 1 wherein the formed annular section is joined to said upstream section and to said downstream section by electron beam welding.

### Claim 4 (depends on 1)

A method as set forth in claim 1 wherein the replacement section is permanently deformed to a final shape after being joined to the upstream section and the downstream section of the liner.

### Claim 5 (depends on 1)

A method as set forth in claim 1 wherein the liner is heat treated after the replacement section is joined to the upstream section and the downstream section of the liner.

### Claim 6 (depends on 1)

A method as set forth in claim 1 wherein cooling holes are machined in the liner after the replacement section is joined to the upstream section and the downstream section of the liner.

### Claim 7 (depends on 6)

A method as set forth in claim 6 wherein the cooling holes are machined in the liner at different positions than cooling holes in the removed annular portion.

### Claim 8 (depends on 6)

A method as set forth in claim 6 wherein the cooling holes are machined in the liner with different sizes than cooling holes in the removed annular portion.