Method for intermediate cooling and gas turbine system with intermediate cooling

摘要

In a method and a device for intermediate cooling during compression in a gas turbine system, the gas turbine system comprises 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.