Method for intermediate cooling and gas turbine system with...

Details Method for intermediate cooling and gas turbine system with... Method for intermediate cooling and gas turbine system with...

2005-11-22

2005-11-22

Verdier, Christopher (Department: 3745)

Rotary kinetic fluid motors or pumps

Method of operation

C415S179000, C060S728000, C060S775000

Reexamination Certificate

active

06966745

ABSTRACT:
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 (1) and one second compressor (2), a combustion chamber (3), and a turbine (4). At least one intermediate cooler (9) is located between the first (1) and second compressor (2). The intermediate cooling takes place at least in part or for the most part isentropically.

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patent: 0 903 483 (1999-03-01), None
patent: 00/60226 (2000-10-01), None

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