Nozzle, burner, combustor, gas turbine, and gas turbine system

Patent metadata

Field	Value
Publication number	US-11242993-B2
Application number	US-201515115431-A
Country	US
Kind code	B2
Filing date	Mar 12, 2015
Priority date	Mar 20, 2014
Publication date	Feb 8, 2022
Grant date	Feb 8, 2022

Abstract

A combustor provided with: a nozzle having formed therein an air jet section that causes air to be jetted from a nozzle section; a cylindrical part covering the nozzle from the outer peripheral side thereof and forming an air flow path between the cylindrical part and the nozzle; and a pressure loss section provided to the air flow path. The pressure loss section causes a loss of pressure in the air that flows through the air flow path. The nozzle is provided with: at least one air inlet section that takes in air from an outer peripheral surface that is an upstream side from the pressure loss section; and a flow path-forming section forming a discharge air flow path that guides air that is taken in from the at least one air inlet section to the air jet section.

First claim

The invention claimed is:

1. A combustor comprising:
a burner having at a tip portion thereof a nozzle configured to jet fuel, the nozzle comprising:
a circular cone shaped tip that gradually decreases an outside diameter thereof toward a tip portion;
one air jet section configured to jet only air from the circular cone shaped tip; and
a flow path-forming section defining a plurality of flow path holes, extending in an axial direction, wherein the plurality of flow path holes are merged into one path in a merging section to communicate with the one air jet section,

a cylindrical part covering the nozzle from an outer peripheral side thereof, so that an air flow path is formed between the cylindrical part and the nozzle; and
a pressure loss section provided in the air flow path, the pressure loss section causing a loss of pressure in the air that flows through the air flow path;
the nozzle further comprising:
at least one air inlet section that takes in a part of the air that flows through the air flow path from an outer peripheral surface that is an upstream side relative to the pressure loss section,
wherein the flow path-forming section guides the air that is taken in from the at least one air inlet section to the one air jet section,
wherein the at least one air inlet section comprises a plurality of air inlet sections,
wherein the plurality of air inlet sections are provided on the outer peripheral surface of the nozzle,
wherein the flow path-forming section comprises the merging section that causes the air that is taken in from the plurality of air inlet sections to be merged at an upstream side relative to the one air jet section, and
wherein each of the plurality of air inlet sections is an opening that extends radially from the outer peripheral surface of the nozzle to an end of a respective one of the plurality of flow path holes.

2. The combustor according to claim 1 , wherein the flow path-forming section forms a flow path having an annular cross section.

3. The combustor according to claim 1 , wherein the flow path-forming section forms a plurality of flow paths arranged concentrically.

4. A gas turbine, comprising:
the combustor described in claim 1 ; and
a turbine main body comprising a rotor that is rotated by combustion gas fed from the combustor.

5. A gas turbine system, comprising:
the combustor according to claim 1 ;
a turbine main body comprising a rotor that is rotated by combustion gas fed from the combustor;
a chamber air supply section that supplies the air in a chamber of the turbine main body to the one air jet section;
a control valve that controls the air supply from the chamber of the turbine main body to the one air jet section in the chamber air supply section;
a detecting section that detects occurrence of a flashback in the combustor; and
a control device that controls opening/closing of the control valve on the basis of a detection result of the detecting section.

6. A gas turbine, comprising:
the combustor described in claim 1 ; and
a turbine main body comprising a rotor that is rotated by combustion gas fed from the combustor.

7. A gas turbine, comprising:
the combustor described in claim 2 ; and
a turbine main body comprising a rotor that is rotated by combustion gas fed from the combustor.

Assignees

• Mitsubishi Hitachi Power Sys Ltd
• Mitsubishi Power Ltd

Inventors

• Inoue Kei
• Takiguchi Satoshi
• Akamatsu Shinji
• Taniguchi Kenta
• Abe Naoki

Classifications

• F23D14/82

  Preventing flashback or blowback · CPC title

• F23R3/286 Primary

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

• F23R3/14

  by using swirl vanes · CPC title

• F23R3/16 Primary

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title