Gas turbine

Patent metadata

Field	Value
Publication number	US-11118512-B2
Application number	US-201716089076-A
Country	US
Kind code	B2
Filing date	Mar 28, 2017
Priority date	Mar 30, 2016
Publication date	Sep 14, 2021
Grant date	Sep 14, 2021

Abstract

There is provided a gas turbine ( 1 ) including a compressor ( 2 ) that generates compressed air, a casing ( 5 ) into which the compressed air is introduced, a combustor ( 3 ) that generates a combustion gas, a turbine ( 4 ) that is driven by the combustion gas, a combustor cooling system ( 6 ) that has a sub-compressor ( 62 ), which is able to be operated independently of the compressor ( 2 ), and a heat exchanger ( 61 ), which extracts air in the casing ( 5 ) and causes the air to exchange heat after the sub-compressor ( 62 ) has increased a pressure of the air, and that introduces the air, which has exchanged heat, into a cooling passage ( 31 ) of a cylindrical body ( 30 ) of the combustor ( 3 ), and a combustor air introducing system that extracts air flowing in the combustor cooling system ( 6 ) and introduces the air into the combustor ( 3 ).

First claim

What is claimed is:

1. A gas turbine comprising:
a compressor that compresses external air to generate compressed air;
a casing into which the compressed air is introduced;
a combustor that receives the compressed air from an inside of the casing and mixes the compressed air with fuel to form a mixture, the combustor configured to combust the mixture to generate a combustion gas, the combustor having a cylindrical body through which the combustion gas passes;
a turbine that is driven by the combustion gas;
a combustor cooling system that extracts air from the casing and that introduces the air into a cooling passage of the cylindrical body; and
a combustor air introducing system that extracts air flowing in the combustor cooling system and introduces the air into the combustor,
wherein the combustor cooling system has a sub-compressor configured to operate independently of the compressor, and a heat exchanger which causes the air to exchange heat before the sub-compressor has increased a pressure of the air,
wherein the combustor cooling system has a first line that connects a space in the casing to the cooling passage,
wherein the combustor air introducing system has a second line that connects a position on the first line between the heat exchanger and the casing to the combustor,
wherein the sub-compressor and the heat exchanger are disposed on the first line such that air at a first pressure flowing through the first line to the cooling passage is compressed by the sub-compressor to a second pressure higher than the first pressure to provide air from the first line to the cooling passage at the second pressure whereas air flowing through the second line is provided to the combustor at the first pressure,
wherein the combustor has a first swirler that causes a swirl to be generated in the combustion gas,
wherein the combustor has:
an outer shell, a portion of the outer shell being positioned radially outward from the cylindrical body;
an air flow path, along which the compressed air flows in a circulation direction, defined between an outer circumferential surface of the cylindrical body and the outer shell; and
a peg formed so as to extend in a first direction intersecting the circulation direction of the compressed air along the air flow path, the peg having an injecting hole configured to inject the fuel in a second direction intersecting the circulation direction of the compressed air along the air flow path, the injecting hole having a first center axis,

wherein the peg is connected to the second line and configured to receive air at the first pressure supplied from the combustor air introducing system via the second line, and a peg air hole is formed in the peg, the peg air hole having a second center axis substantially perpendicular to the first center axis and being configured to inject the received air downstream in the circulation direction of the compressed air along the air flow path,
and wherein the peg is arranged such that the injected air from the peg air hole flows along the air flow path to the first swirler.

2. The gas turbine according to claim 1 ,
wherein the combustor has a first nozzle that supplies the fuel into the cylindrical body and mixes the fuel with the compressed air,
wherein the first swirler is provided on an outer circumferential side of the first nozzle, and
wherein a first nozzle air hole for injecting air supplied from the combustor air introducing system toward a vortex center of the swirl is formed in a tip of the first nozzle.

3. The gas turbine according to claim 2 ,
wherein the combustor has a second nozzle which is provided to be parallel to the first nozzle and in which a second nozzle injecting hole for injecting fuel is formed, and
wherein a second nozzle air hole that is formed on the second nozzle so as to surround the second nozzle injecting hole is configured to inject the air supplied from the combustor air introducing system in a flow of the fuel injected from the second nozzle injecting hole.

4. The gas turbine according to claim 2 ,
wherein a fuel flow path configured to allow the fuel to flow is formed inside the first nozzle, and
a first nozzle injection hole is formed in the first nozzle between the tip and the first swirler for injecting the fuel, the first nozzle injection hole extending at an angle with respect to the fuel flow path.

Assignees

• Mitsubishi Hitachi Power Sys Ltd
• Mitsubishi Heavy Ind Ltd
• Mitsubishi Power Ltd

Inventors

• Miyamoto Kenji
• Takiguchi Satoshi
• Nose Masakazu

Classifications

• F02C7/22

  Fuel supply systems · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F02C7/08

  Heating air supply before combustion, e.g. by exhaust gases · CPC title