Dual-fuel injector with a double pipe sleeve gaseus fuel flow path

Patent metadata

Field	Value
Publication number	US-10094567-B2
Application number	US-201414461532-A
Country	US
Kind code	B2
Filing date	Aug 18, 2014
Priority date	Sep 20, 2013
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

Abstract

A dual-fuel burning gas turbine combustor having a diffusive combustion burner to burn a liquid fuel and a gaseous fuel placed at the axis of the gas turbine combustor and a plurality of pre-mixing combustion burners to burn a liquid fuel and a gaseous fuel placed on an outer circumferential side of the diffusive combustion burner, each pre-mixing combustion burner having a liquid fuel nozzle, a plurality of gaseous fuel spray holes, a plurality of air holes, and a pre-mixing chamber to mix gaseous fuel and air, wherein each pre-mixing combustion burner has a double pipe sleeve at a connected portion between end cover and the pre-mixing combustion burner, and the double pipe sleeve has an inner sleeve having a gaseous fuel flow path, an outer sleeve positioned on an outer circumferential side of the inner sleeve, and a circular spacing formed between the inner sleeve and the outer sleeve.

First claim

The invention claimed is:

1. A dual-fuel burning gas turbine combustor comprising: a liquid fuel and a gaseous fuel, in which a diffusive combustion burner that burns the liquid fuel and the gaseous fuel is placed at the center of the axis of the gas turbine combustor and
a plurality of pre-mixing combustion burners that burns the liquid fuel and the gaseous fuel are placed on an outer circumferential side of the diffusive combustion burner, each pre-mixing combustion burner comprising:
a liquid fuel nozzle through which the liquid fuel is supplied;
a plurality of gaseous fuel spray holes through which the gaseous fuel is supplied;
a plurality of air holes through which a combustion air is supplied; and
a gaseous fuel flow path through which the gaseous fuel is supplied to the plurality of gaseous fuel spray holes, the fuel spray holes and the air holes are being placed on an outer circumferential side of the liquid fuel nozzle, and a pre-mixing chamber in which the gaseous fuel and the combustion air are mixed together;

an end cover which is provided with the pre-mixing combustion burner at the downstream side thereof, and a flow path through which the gaseous fuel supplied from the gaseous fuel flow path configured to provide gaseous fuel flow, is formed within the end cover; and
a double pipe sleeve which is attached to at a connected portion between the flow path disposed in the end cover and the gaseous fuel flow path disposed in the pre-mixing combustion burner;
wherein, the double pipe sleeve which is provided with a cylindrical inner sleeve through which the gaseous fuel flows down from the flow path disposed in the end cover to a gaseous fuel flow path disposed in the pre-mixing combustion burner, an outer sleeve which is disposed to be concentric with the cylindrical inner sleeve positioned on an outer circumferential side of the cylindrical inner sleeve;
the cylindrical inner sleeve and the outer sleeve of the double pipe sleeve both extend and overlap each other approximately between an upstream portion of the gaseous fuel flow path and a downstream portion of the gaseous fuel flow path;
the outer sleeve of the double pipe sleeve has a first end that is attached to an inner wall surface of the pre-mixing combustion burner by a first welded portion approximately at the downstream portion of the gaseous fuel flow path;
the cylindrical inner sleeve of the double pipe sleeve has a first end that is attached to a second end of the outer sleeve of the double pipe sleeve by a second welded portion at the upstream portion of the gaseous fuel flow path; and
a circular spacing is formed between and enclosed by the cylindrical inner sleeve and the outer sleeve of the double pipe sleeve.

2. The dual-fuel burning gas turbine combustor according to claim 1 , wherein: ends of the cylindrical inner sleeve and the outer sleeve of the double pipe sleeve are mutually welded; and
an end of the outer sleeve is welded to the end cover, and another end of the outer sleeve is welded to an inner wall surface of the gaseous fuel flow path disposed in the pre-mixing burner.

3. The dual-fuel burning gas turbine combustor according to claim 1 , wherein: ends of the cylindrical inner sleeve and the outer sleeve of the double pipe sleeve are joined so that the cylindrical inner sleeve is fitted to an inside of the outer sleeve; and
an end of the outer sleeve is welded to the end cover, and another end of the outer sleeve is welded to an inner wall surface of the gaseous fuel flow path disposed in the pre-mixing burner.

4. The dual-fuel burning gas turbine combustor according to claim 2 , wherein: a groove is formed on the inner wall surface of the gaseous fuel flow path formed in the pre-mixing burner so as to be close to a welded portion by which the another end of the outer sleeve of the double pipe sleeve is welded to the inner wall surface of the gaseous fuel flow path.

5. The dual-fuel burning gas turbine combustor according to claim 3 , wherein: a groove is formed on the inner wall surface of the gaseous fuel flow path formed in the pre-mixing burner so as to be close to a welded portion by which the another end of the outer sleeve of the double pipe sleeve is welded to the inner wall surface of the gaseous fuel flow path.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Igarashi Shota
• Takahashi Hirokazu

Classifications

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/36

  Supply of different fuels · CPC title

• F23D2900/00008

  Burner assemblies with diffusion and premix modes, i.e. dual mode burners · CPC title

• F23R2900/00002

  Gas turbine combustors adapted for fuels having low heating value [LHV] · CPC title

• F23D2211/00

  Thermal dilatation prevention or compensation · CPC title