# US 8,782,865 B2 · Combustor liner and flow sleeve tool

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- Number: US 8,782,865 B2
- Document ID: US8782865B2
- Status: Granted
- Kind: B2
- Application number: 13/160,914
- Filed: 2011-06-15
- Published: 2012-09-20
- Granted: 2014-07-22
- Earliest claimed: 2011-03-16
- Assignees: General Electric Company
- Applicants: Mustafa Gerengi
- Inventors: Mustafa Gerengi
- Web page: https://patentgrep.com/patent/US8782865B2

## CPC

- F23R 3/00: Continuous combustion chambers using liquid or gaseous fuel
- F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing
- F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep
- F23R 3/44: Combustion chambers comprising a {single} tubular flame tube within a tubular casing (reverse-flow combustion chambers F23R3/54)
- F05D 2220/32: in gas turbines
- F05D 2230/60: Assembly methods
- F05D 2230/70: Disassembly methods
- F23R 3/60: Support structures; Attaching or mounting means
- F23R 2900/00017: Assembling combustion chamber liners or subparts
- F23R 2900/00019: Repairing or maintaining combustion chamber liners or subparts
- Y10T 29/49899: by multiple cooperating aligning means
- Y10T 29/53657: to apply or remove a resilient article [e.g., tube, sleeve, etc.]
- Y10T 29/53796: Puller or pusher means, contained force multiplying operator
- Y10T 29/53943: Hand gripper for direct push or pull
- 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)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- 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 tool includes an annular frame portion including a mount portion extending radially from the frame portion, a hook portion arranged on the mount portion, the hook portion sized and shaped to engage a member of a tubular component of a turbine combustor, and a force exertion portion arranged on the mount portion, the force exertion portion operative to engage a portion of the turbine combustor.

## Claims

### Claim 1

A tool comprising:
an annular frame portion including a mount portion extending radially from the frame portion;
a hook portion arranged on the mount portion, the hook portion sized and shaped to engage a member of a tubular component of a turbine combustor; and
a force exertion portion arranged on the mount portion, the force exertion portion operative to engage a portion of the turbine combustor, wherein the hook portion includes an aperture arranged in parallel to a rotational axis of the frame portion.

### Claim 2 (depends on 1)

The tool of claim 1, wherein the hook portion includes a plate defining the aperture.

### Claim 3 (depends on 2)

The tool of claim 2, wherein the aperture is defined by a first planar surface arranged substantially in parallel with a second planar surface.

### Claim 4 (depends on 3)

The tool of claim 3, wherein the aperture is further defined by a third planar surface arranged substantially perpendicular to the first planar surface.

### Claim 5 (depends on 3)

The tool of claim 3, wherein the first planar surface is arranged in parallel with a planar surface of the frame portion.

### Claim 6 (depends on 1)

The tool of claim 1, wherein the force exertion portion includes a first threaded member engaging the mount portion.

### Claim 7 (depends on 6)

The tool of claim 6, wherein the force exertion portion includes a second threaded member engaging the mount portion.

### Claim 8 (depends on 1)

The tool of claim 1, wherein the tool further includes a second annular frame portion, wherein the force exertion portion is connected to the second annular frame portion.

### Claim 9 (depends on 1)

The tool of claim 1, wherein the force exertion portion includes a hydraulic jack member.

### Claim 10 (depends on 1)

The tool of claim 1, wherein the tool further includes a handle arranged on the annular frame portion.

### Claim 11 (depends on 1)

The tool of claim 1, wherein the force exertion portion is operative to engage a threaded orifice of a combustor portion of a turbine system.

### Claim 12 (depends on 1)

The tool of claim 1, wherein the hook portion is secured to the mount portion with a fastener.