Abstract: A fluid flow machine, in particular turbocompressor, with a housing, having a rotor mounted in the housing, and with a dry gas seal for sealing the rotor relative to the housing. The housing at least one recess or bore for a gaseous medium is introduced, via which the gaseous medium for temperature-controlling the dry gas seal can be conducted in the direction of the same. The gaseous medium can be directly conducted into a gas space formed between the housing and the dry gas seal via the or each recess or bore. Additionally or alternatively, the or each recess or bore receives a guide tube for the gaseous medium.

Abstract: A radial compressor unit for compressing gas has several compressor stages. Each compressor stage includes an impeller having rotor blades, and a flow channel arranged downstream of the impeller, as viewed in the flow direction of the gas to be compressed, having a diffusor section, a deflection section, and a recirculation section having guide blades. The gas compressed in a compressor stage can be removed as cooling gas for cooling a component to be cooled, and can be conveyed in the direction of the component to be cooled. The cooling gas can be removed adjacent to an intermediate wall of the compressor stage from the deflection section and/or the recirculation section of the flow channel of the compressor stage.

Abstract: A fluid flow machine, in particular turbocompressor, with a housing, having a rotor mounted in the housing, and with a dry gas seal for sealing the rotor relative to the housing. The housing at least one recess or bore for a gaseous medium is introduced, via which the gaseous medium for temperature-controlling the dry gas seal can be conducted in the direction of the same. The gaseous medium can be directly conducted into a gas space formed between the housing and the dry gas seal via the or each recess or bore. Additionally or alternatively, the or each recess or bore receives a guide tube for the gaseous medium.

Abstract: A radial compressor unit for compressing gas has several compressor stages. Each compressor stage includes an impeller having rotor blades, and a flow channel arranged downstream of the impeller, as viewed in the flow direction of the gas to be compressed, having a diffusor section, a deflection section, and a recirculation section having guide blades. The gas compressed in a compressor stage can be removed as cooling gas for cooling a component to be cooled, and can be conveyed in the direction of the component to be cooled. The cooling gas can be removed adjacent to an intermediate wall of the compressor stage from the deflection section and/or the recirculation section of the flow channel of the compressor stage.

Abstract: A turbine blade (1) with a side surface (7) having an aerodynamic profile. The turbine blade (1) further comprises an end surface (6) and is mounted in a turbine, whereby the end surface (6) is delimited by a gap from a casing (8) of the turbine. The end surface (6) comprises a recess (2) which is shaped such that it acts as an improved aerodynamic seal.