Combustion device and gas turbine

Patent metadata

Field	Value
Publication number	US-10995662-B2
Application number	US-201916524627-A
Country	US
Kind code	B2
Filing date	Jul 29, 2019
Priority date	Jan 31, 2017
Publication date	May 4, 2021
Grant date	May 4, 2021

Abstract

The combustion device includes: a combustion chamber in which fuel is combusted using combustion air; and a reducing agent injector that injects a reducing agent toward flames in the combustion chamber.

First claim

What is claimed is:

1. A combustion device comprising:
a combustor in which a combustion chamber in which fuel is combusted using combustion air is formed wherein
the combustor includes:
a reducing agent injector that injects a reducing agent toward flames in the combustion chamber;
a liner having an internal space used as the combustion chamber;
a casing accommodating the liner;
a fuel nozzle configured to inject the fuel into the combustion chamber; and
a flow adjuster which is annularly provided around the fuel nozzle at one end of the casing and is configured to supply the combustion air from one end of the combustion chamber and to form a swirling flow of the combustion air inside the combustion chamber, and
the reducing agent injector is configured to inject the reducing agent n a direction along the swirling flow formed by the flow adjuster when viewed from a plane perpendicular to a mainstream direction in the combustion chamber.

2. The combustion device according to claim 1 , wherein the reducing agent injector is configured to inject the reducing agent to an area of the flames in which an oxygen concentration thereof is lower than other areas of the flames.

3. The combustion device according to claim 1 , wherein the reducing agent injector is configured to inject the reducing agent toward a center portion of the flames, the center portion being at a center of the flames in a mainstream direction in the combustion chamber.

4. The combustion device according to claim 1 , wherein reducing agent injector includes one or a plurality of injection holes provided around the flames and is configured to inject the reducing agent from the one or the plurality of injection holes toward the flames.

5. The combustion device according to claim 1 , wherein the reducing agent is ammonia.

6. A gas turbine comprising the combustion device according to claim 1 .

Assignees

• Ihi Corp

Inventors

• Ito Shintaro
• Kato Soichiro
• Uchida Masahiro
• Onishi Shogo
• Mizutani Taku
• Saitou Tsukasa
• Fujimori Toshiro

Classifications

• Y02E20/34

  Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery · CPC title

• F23R3/40

  characterised by the use of catalytic means · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23L7/007

  Supplying oxygen or oxygen-enriched air · CPC title

• F23K5/002

  Gaseous fuel · CPC title