# US 2009/0260206 A1 · Turbine vane airfoil reconfiguration method

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- Number: US 2009/0260206 A1
- Document ID: US20090260206A1
- Status: Published application
- Kind: A1
- Application number: 12/372,168
- Filed: 2009-02-17
- Published: 2009-10-22
- Earliest claimed: 2005-10-13
- Assignees: Siemens Energy, Inc.; Chromalloy Gas Turbine Corporation
- Inventors: Martin C. Gosling; Jefferson Davis; Yong Kang
- Web page: https://patentgrep.com/patent/US20090260206A1

## CPC

- B23P 6/002: {Repairing turbine components, e.g. moving or stationary blades, rotors, (B23P6/045 takes precedence)}
- F01D 5/005: {Repairing methods or devices}
- F05D 2230/80: Repairing, retrofitting or upgrading methods
- Y10T 29/37: Impeller making apparatus
- Y10T 29/49316: Impeller making
- Y10T 29/49318: Repairing or disassembling
- Y10T 29/49325: Shaping integrally bladed rotor
- Y10T 29/49336: Blade making
- Y10T 29/49716: Converting
- Y10T 29/49718: Repairing
- Y10T 29/53: Means to assemble or disassemble
- B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A system and method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

## Claims

### Claim at position 1

1-10. (canceled)

### Claim 11

A device for reconfiguring an airfoil of a turbine vane segment, comprising:
a fixture adapted to receive and fix an outer shroud of the turbine vane segment;
reaction arms extending from the fixture and adapted to be inserted into recesses within an outer surface of the outer shroud the turbine vane segment, wherein the reaction arms are supported by the fixture; and
a force exertion system adapted to exert a force on an inner shroud of the turbine vane segment in a direction that is generally tangential to the outer shroud of the turbine vane segment while allowing movement in other directions.

### Claim 12 (depends on 11)

The device of claim 11, wherein the force exertion system comprises a jack.

### Claim 13 (depends on 12)

The device of claim 12, wherein the force exertion system comprises a floating bracket having an extension arm for contacting a first side surface of the inner shroud of the turbine vane segment and a force application surface adapted to contact a second side surface of the inner shroud of the turbine vane segment, wherein the second side surface is adjacent to the first side surface of the inner shroud.

### Claim 14 (depends on 13)

The device of claim 13, wherein the force exertion system further comprises a reaction bracket for supporting the jack.

### Claim 15 (depends on 11)

The device of claim 11, wherein the force exertion system comprises a floating bracket having an extension member for contacting a first side surface of the inner shroud of the turbine vane segment and a force application surface adapted to contact a second side surface of the inner shroud of the turbine vane segment, wherein the second side surface is adjacent to the first side surface of the inner shroud.

### Claim 16 (depends on 11)

The device of claim 11, further comprising a twist limiting device extending from the fixture for limiting twist of the turbine vane segment.

### Claim 17 (depends on 16)

The device of claim 16, wherein the twist limiting device comprises a roller extending from the fixture to contact the inner shroud of the turbine vane segment to limit twist of the airfoil.

### Claim 18 (depends on 16)

The device of claim 16, wherein the twist limiting device comprises at least one guide bar extending from the fixture to contact the inner shroud of the turbine vane segment to limit twist of the airfoil.

### Claim 19 (depends on 11)

The device of claim 11, further comprising a clamping device adapted to attach the turbine vane segment to the fixture to prevent the reaction arms from being dislocated from the recesses in the turbine vane segment.

### Claim 20 (depends on 19)

The device of claim 19, wherein the clamping device comprises at least one clamp.