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US 11,156,158 B2Granted
Combustion device and gas turbine engine system
AssigneeIHI Corporation
InventorsShintaro Ito, Soichiro Kato, Masahiro Uchida, Shogo Onishi, Taku Mizutani, Tsukasa Saitou, Toshiro Fujimori
Life of this patent
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Abstract
A combustion device burns fuel ammonia in a combustion chamber using compressed combustion air, and includes a combustion air cooling unit which is configured to cool the combustion air by heat exchange with the fuel ammonia during or before a compression process.
Claims4
A combustion device comprising:
- a vaporizer:
- an ammonia supply unit configured to provide fuel ammonia the ammonia supply unit configured to supply a first part of the fuel ammonia to the vaporizer and configured to supply a second part of the fuel ammonia such that it bypasses the vaporizer;
- a low pressure compressor which is configured to compress combustion air;
- a high pressure compressor which is configured to further compress the combustion air compressed by the low pressure compressor;
- a combustion chamber in which the first and the second part of the fuel ammonia is burned using the combustion air compressed by the low pressure compressor and the high pressure compressor;
- and
- a combustion air cooling unit which is configured to cool the combustion air after being supplied to the low pressure compressor and before being supplied to the high pressure compressor by heat exchange with the second part of the fuel ammonia during a compression process,
- wherein a flow path through which the second part of the fuel ammonia flows is formed inside a stationary blade of the low pressure compressor, the flow path inside the stationary blade of the low pressure compressor being separate from a flow path of the combustion air through the low pressure compressor, and
- a region in which the flow path inside the stationary blade is formed is used as the combustion air cooling unit, and the combustion air cooling unit is configured to cool the combustion air by indirect heat exchange between the second part of the fuel ammonia flowing through the flow path inside the stationary blade and the combustion air flowing through the flow path of the combustion air through the low pressure compressor,
- wherein the first part of the fuel ammonia and the second part of the fuel ammonia are configured to be combined prior to being burned in the combustion chamber and after the first part of the fuel ammonia passes through the vaporizer and after the second part of the fuel ammonia passes through the combustion air cooling unit.
7 more elements
Dependencies are inferred from the claim text.