# US 11,112,116 B2 · Gas turbine combustor and gas turbine

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- Number: US 11,112,116 B2
- Document ID: US11112116B2
- Status: Granted
- Kind: B2
- Application number: 16/719,262
- Filed: 2019-12-18
- Published: 2020-08-27
- Granted: 2021-09-07
- Earliest claimed: 2019-02-27
- Assignees: Mitsubishi Power, Ltd.
- Applicants: Mitsubishi Power, Ltd.
- Inventors: Hironori Tsukidate; Kunihiro Oga; Yoshitaka Terada; Koichi Nishida
- Web page: https://patentgrep.com/patent/US11112116B2

## CPC

- F23R 3/28: characterised by the fuel supply (burners F23D)
- F02C 7/22: Fuel supply systems
- F02C 7/222: {Fuel flow conduits, e.g. manifolds}
- F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances}
- F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)}
- F05D 2240/35: Combustors or associated equipment
- F23R 3/46: Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings
- F23R 2900/00005: Preventing fatigue failures or reducing mechanical stress in gas turbine components
- F23R 2900/00017: Assembling combustion chamber liners or subparts
- 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)
- 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

## Abstract

The present invention reduces thermal stress that is applied to the weld zone of a cavity formed in the structural material of a burner. The burner includes the cavity distributing a fuel to fuel nozzles. The cavity is demarcated by a groove formed in the structural material of the burner so as to create a level difference at an opening, and a cover fitted into the level difference to close the groove. The cover is formed by a web covering the opening in the groove and a flange extending in the depth direction of the groove to be fitted into the level difference, and is joined by welding to the structural material in such a manner as to have an L-shaped cross-section. When viewed in a cross-section orthogonal to the groove, a cover-side inner surface that is an inner surface of the flange forming a lateral surface of the cavity is flush with a groove-side inner surface that is an inner surface of the groove forming a lateral surface of the cavity. The boundary between the cover-side inner surface and the groove-side inner surface is away from a first corner of the cavity sandwiched between the cover-side inner surface and the inner surface of the web forming a ceiling surface of the cavity.

## Claims

### Claim 1

A gas turbine combustor that receives compressed air discharged from a compressor, mixes the compressed air with a fuel, burns a mixture of the compressed air and the fuel to generate a combustion gas, and supplies the generated combustion gas to a turbine, the gas turbine combustor comprising:
an inner cylinder configured to form a combustion chamber therein;
an outer cylinder configured to cover the inner cylinder and form a cylindrical outer circumferential flow path between the outer cylinder and the inner cylinder to allow the compressed air to flow; and
a burner that is mounted on an end of the outer cylinder, the end being positioned on an opposite side to a side where the turbine is located, and that faces the combustion chamber, wherein
the burner includes a plurality of fuel nozzles configured to inject the fuel, and a cavity configured to distribute the fuel to the fuel nozzles,
the cavity is demarcated by a groove formed in a structural material of the burner to create a level difference at an opening, and a cover fitted into the level difference to close the groove,
the cover is formed by a web and a flange and joined by welding to the structural material in such a manner as to have an L-shaped or U-shaped cross-section, the web facing a bottom surface of the groove and covering the opening in the groove, the flange extending in a depth direction of the groove from an edge of the web and fitted into the level difference,
when viewed in a cross-section orthogonal to the groove, a cover-side inner surface that is an inner surface of the flange is flush with a groove-side inner surface that is an inner surface of the groove, the cover-side inner surface and the groove-side inner surface together forming a lateral surface of the cavity, and
a boundary between the cover-side inner surface and the groove-side inner surface is spaced away from a first corner of the cavity that is sandwiched between the cover-side inner surface and an inner surface of the web, the inner surface of the web forming a ceiling surface of the cavity.

### Claim 2 (depends on 1)

The gas turbine combustor according to claim 1, wherein
the web of the cover includes a thin section that is thinner than a section adjacent to the thin section of the web.

### Claim 3 (depends on 2)

The gas turbine combustor according to claim 2, wherein
the ceiling surface of the cavity formed by the web has a recess that forms the thin section.

### Claim 4 (depends on 3)

The gas turbine combustor according to claim 3, wherein an inner surface of the recess is flush with an other inner surface of the groove, and an other boundary between the inner surface of the recess and the other inner surface of the groove is spaced away from a second corner of the cavity formed by the recess.

### Claim 5 (depends on 1)

The gas turbine combustor according to claim 1, wherein the cavity is connected to a fuel supply source directly not via a fuel heating facility.

### Claim 6 (depends on 1)

The gas turbine combustor according to claim 1, wherein
the welding is performed by a laser welding method or an electron beam welding od.

### Claim 7 (depends on 1)

The gas turbine combustor according to claim 1, wherein
a penetration depth achieved by the welding is greater than a bead width.

### Claim 8 (depends on 1)

A gas turbine comprising:
a compressor configured to compress air to generate compressed air;
the gas turbine combustor according to claim 1 that receives compressed air discharged from the compressor, mixes the compressed air with a fuel, and burns a mixture of the compressed air and the fuel to generate a combustion gas; and
a turbine configured to be driven by the combustion gas supplied from the gas turbine combustor.