Method for intermediate cooling and gas turbine system with intermediate cooling
In a method and a device for intermediate cooling during compression in a gas turbine system, the gas turbine system includes at least one first and one second compressor, a combustion chamber, and a turbine. At least one intermediate cooler is located between the first and second compressor. The in...
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| Format: | Patent |
| Sprache: | eng |
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| Zusammenfassung: | In a method and a device for intermediate cooling during compression in a gas turbine system, the gas turbine system includes at least one first and one second compressor, a combustion chamber, and a turbine. At least one intermediate cooler is located between the first and second compressor. The intermediate cooling takes place at least in part or for the most part isentropically. |
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