Abstract: A method for operating a gas turbine installation (1) includes sucking in a gaseous medium (2) by the compressor (3) and compressed in the compressor space, a liquid medium (10) being injected into the gaseous medium (2), so that a two-phase flow comprising a gaseous phase and a liquid phase is formed at least in a subregion of the compressor (3). The gaseous medium (2) is then burnt with fuel (5) in a combustion chamber (6) to form hot gases (7), and the hot gases (7) are expanded in a turbine (8), the hot components of the gas turbine installation (1) being cooled by cooling air (14) of a cooling air system. A measurement is carried out to determine whether a liquid phase is present in a region of the compressor (3) and/or of the cooling air system.

Abstract: In an atomizer device for the production of a liquid-gas mixture (4), the mixture (4) is introduced, particularly for compression, into a nozzle arrangement (3) in which the kinetic energy of the mixture (4) is in large part converted into compression energy by a pressure rise of the air. The atomizer device (2) includes a central air feed (16) and a nozzle chamber (18) for the supply of liquid surrounding the air feed. At or in the atomizing device, means (17) are arranged in the nozzle chamber for producing a swirled liquid flow in the nozzle chamber (18), and the swirled liquid flow emerges via a nozzle aperture (19) surrounding the air feed.

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.

Abstract: A burner (24) which is useful for operating a heat generator includes a first upstream swirl generator (17) capable of swirling a combustion air stream, a device for injecting at least one fuel into the combustion air stream from the upstream swirl generator (17), an exit ring (1) located at the downstream end of the burner (24) at the edge to the combustion chamber (2) where the fuel is burnt, and preferentially a mixing section (20, 21) downstream from the upstream swirl generator (17) having a downstream end, having at least one transfer duct (20) for transferring downstream a flow of combustion air and fuel formed in the upstream swirl generator (17), and having a mixing tube (21) downstream from the at least one transfer duct (20) and receiving flow from the at least one transfer duct (20), wherein the downstream end of the mixing section borders the combustion chamber (2) and is formed by the exit ring (1).

Abstract: In an atomizer device for the production of a liquid-gas mixture (4), the mixture (4) is introduced, particularly for compression, into a nozzle arrangement (3) in which the kinetic energy of the mixture (4) is in large part converted into compression energy by a pressure rise of the air.

Abstract: 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.