Gas turbine system

Patent metadata

Field	Value
Publication number	US-2024011435-A1
Application number	US-202318474785-A
Country	US
Kind code	A1
Filing date	Sep 26, 2023
Priority date	Mar 30, 2021
Publication date	Jan 11, 2024
Grant date	—

Abstract

Provided is a gas turbine system, including: an ammonia tank; a combustor including a combustion chamber, which is connected to the ammonia tank; an intake flow passage connected to the combustor; a compressor provided in the intake flow passage; a cracked-gas reservoir connected to the combustor; and an ammonia cracking catalyst arranged in a bleed flow passage connected to the compressor, between the compressor and the combustor in the intake flow passage, or in a space in the combustor, which brings the combustion chamber and the intake flow passage into communication with each other, the ammonia cracking catalyst being connected to the ammonia tank and the cracked-gas reservoir.

First claim

1 . A gas turbine system, comprising:
an ammonia tank; a combustor including a combustion chamber, which is connected to the ammonia tank; an intake flow passage connected to the combustor; a compressor provided in the intake flow passage; a cracked-gas reservoir connected to the combustor; and an ammonia cracking catalyst arranged in a bleed flow passage connected to the compressor, between the compressor and the combustor in the intake flow passage, or in a space in the combustor, which brings the combustion chamber and the intake flow passage into communication with each other, the ammonia cracking catalyst being connected to the ammonia tank and the cracked-gas reservoir.

2 . The gas turbine system according to claim 1 , wherein a cooling device is provided in a flow passage that connects the ammonia cracking catalyst and the cracked-gas reservoir to each other.

3 . The gas turbine system according to claim 2 ,
wherein the cooling device is a heat exchanger provided in a flow passage that connects the ammonia cracking catalyst and the cracked-gas reservoir, and wherein a flow passage that connects the ammonia tank and the ammonia cracking catalyst passes through the heat exchanger.

4 . The gas turbine system according to claim 1 ,
wherein a first flow rate control valve is provided in a flow passage that connects the ammonia tank and the ammonia cracking catalyst, and wherein the gas turbine system comprises a controller configured to control the first flow rate control valve so that ammonia is supplied from the ammonia tank to the ammonia cracking catalyst during an operation of the gas turbine system.

5 . The gas turbine system according to claim 2 ,
wherein a first flow rate control valve is provided in a flow passage that connects the ammonia tank and the ammonia cracking catalyst, and wherein the gas turbine system comprises a controller configured to control the first flow rate control valve so that ammonia is supplied from the ammonia tank to the ammonia cracking catalyst during an operation of the gas turbine system.

6 . The gas turbine system according to claim 3 ,
wherein a first flow rate control valve is provided in a flow passage that connects the ammonia tank and the ammonia cracking catalyst, and wherein the gas turbine system comprises a controller configured to control the first flow rate control valve so that ammonia is supplied from the ammonia tank to the ammonia cracking catalyst during an operation of the gas turbine system.

7 . The gas turbine system according to claim 4 ,
wherein a second flow rate control valve is provided in a flow passage that connects the cracked-gas reservoir and the combustor, wherein a third flow rate control valve is provided in a flow passage that connects the ammonia tank and the combustor, and wherein the controller controls the second flow rate control valve and the third flow rate control valve so that supply of the ammonia from the ammonia tank to the combustor is started after supply of a cracked gas from the cracked-gas reservoir to the combustor is started at the time of activation of the gas turbine system.

8 . The gas turbine system according to claim 5 ,
wherein a second flow rate control valve is provided in a flow passage that connects the cracked-gas reservoir and the combustor, wherein a third flow rate control valve is provided in a flow passage that connects the ammonia tank and the combustor, and wherein the controller controls the second flow rate control valve and the third flow rate control valve so that supply of the ammonia from the ammonia tank to the combustor is started after supply of a cracked gas from the cracked-gas reservoir to the combustor is started at the time of activation of the gas turbine system.

9 . The gas turbine system according to claim 6 ,
wherein a second flow rate control valve is provided in a flow passage that connects the cracked-gas reservoir and the combustor, wherein a third flow rate control valve is provided in a flow passage that connects the ammonia tank and the combustor, and wherein the controller controls the second flow rate control valve and the third flow rate control valve so that supply of the ammonia from the ammonia tank to the combustor is started after supply of a cracked gas from the cracked-gas reservoir to the combustor is started at the time of activation of the gas turbine system.

Assignees

• Ihi Corp

Inventors

• Ito Shintaro
• Uchida Masahiro

Classifications

• F02C3/22 Primary

  the fuel or oxidant being gaseous at standard temperature and pressure (F02C3/28 takes precedence) · CPC title

• F02C7/22

  Fuel supply systems · CPC title

• F02C3/24 Primary

  the fuel or oxidant being liquid at standard temperature and pressure · CPC title

• F02C9/40

  specially adapted to the use of a special fuel or a plurality of fuels · CPC title

• F02C7/232

  Fuel valves {(control of fuel supply by means of fuel metering valves F02C9/263)}; Draining valves or systems (valves in general F16K) · CPC title