Gas turbine combustor

Patent metadata

Field	Value
Publication number	US-10401031-B2
Application number	US-201514807071-A
Country	US
Kind code	B2
Filing date	Jul 23, 2015
Priority date	Jul 24, 2014
Publication date	Sep 3, 2019
Grant date	Sep 3, 2019

Abstract

A combustor is capable of ignition and flame propagation at low fuel concentrations for gas or liquid fuel. Combustors are disposed annularly along an outer peripheral portion of a casing of a turbine. A combustion chamber burns fuel and air to generate a combustion gas. A diffusion burner is disposed upstream of the combustion chamber; and a plurality of premix burners are disposed around the diffusion burner. Cross fire tubes provide communication between combustion chambers of combustors adjacent to each other. A cross fire tube connected to a combustor adjacent to a first side in the circumferential direction of the casing is disposed so as to have a central axis passing over a premix burner as viewed from the combustion chamber and another cross fire tube connected to the combustor adjacent to a second side is disposed so as to have a central axis passing between two premix burners.

First claim

What is claimed is:

1. A plurality of combustors disposed annularly along an outer peripheral portion of a casing of a turbine, each of the combustors respectively comprising:
a combustion chamber that burns fuel and air to thereby generate a combustion gas;
a diffusion burner disposed upstream of the combustion chamber;
a liquid fuel system that supplies liquid fuel to the diffusion burner;
a plurality of premix burners disposed around the diffusion burner;
a plurality of cross fire tubes configured to communicate between the combustion chamber and respective combustion chambers of the combustors adjacent to the combustion chamber in a circumferential direction of the casing; and
a gas fuel system that supplies gas fuel to a first premix burner, of the plurality of premix burners, and the diffusion burner, located at an axial center of the combustion chamber,
wherein a central axis of a first cross fire tube, of the plurality of cross fire tubes, is aligned with a straight line that passes through the axial center of the combustion chamber and an axial center of the first premix burner,
wherein the first cross fire tube is connected to one of the plurality of combustors adjacent to a first side of the combustion chamber in the circumferential direction of the casing, and
wherein a second cross fire tube, of the plurality of cross fire tubes, is connected to another one of the plurality of combustors adjacent to a second side of the combustion chamber in the circumferential direction of the casing, a central axis of the second cross fire tube passes through the axial center of the combustion chamber and between a second premix burner and a third premix burner, of the plurality of premix burners, which are adjacent to each other and closest to the second cross fire tube,
wherein the diffusion burner is further disposed on the extension of the central axis of the second cross fire tube,
wherein at a time of ignition using the gas fuel, the gas fuel is supplied by the gas fuel system, and
wherein at a time of ignition using the liquid fuel, the liquid fuel is supplied by the liquid fuel system.

2. The combustors according to claim 1 , further comprising:
a first ignition plug disposed to have a leading end arranged on one of the plurality of premix burners; and
a second ignition plug disposed to have a leading end arranged between adjacent ones of the plurality of premix burners.

3. The combustors according to claim 2 , wherein the plurality of premix burners consist of six premix burners disposed around the diffusion burner.

4. A gas turbine plant comprising:
the plurality of combustors according to claim 1 ;
a compressor that supplies compressed air to the plurality of combustors; and
a turbine driven by a combustion gas supplied from the plurality of combustors.

5. The combustors according to claim 1 , wherein a first straight line and a second straight line pass through the axial center of the combustion chamber and are tangent to respective inner wall surfaces of the first premix burner,
wherein an angle formed between the first line and the second line is less than or equal to 30°.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Hirata Yoshitaka
• Sekiguchi Tatsuya
• Uruno Tomoki
• Hayashi Akinori
• Takahashi Hirokazu

Classifications

• F23R3/04

  Air inlet arrangements · CPC title

• F23R3/36

  Supply of different fuels · CPC title

• F23R2900/03343

  Pilot burners operating in premixed mode · CPC title

• F23R3/48 Primary

  Flame tube interconnectors, e.g. cross-over tubes · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title