Abstract: A geothermal energy system, having a carbon dioxide store at a first temperature and density, a retrieving device for retrieving carbon dioxide at a second temperature higher than the first temperature and a second density lower than the first density, a heat pump having a first heat exchanger, a compressor, a second heat exchanger, and an expander or a throttle. The first heat exchanger transmits thermal energy of the carbon dioxide to a process medium of the heat pump. The compressor compresses the process medium downstream of the first heat exchanger. The second heat exchanger transmits thermal energy of the compressed process medium to a consumer, and the expander or the throttle expands the process medium downstream of the second heat exchanger, and an introduction device introduces carbon dioxide downstream of the retrieving device and upstream of the heat pump into the system.

Abstract: A device for generating energy from compressed air, having an air turbine for expanding gaseous air starting out from a first pressure level to a second pressure level and in the process produce first energy, a combustion chamber for receiving the air expanded in the air turbine and combust fuel in the same, and an exhaust gas turbine for expanding exhaust gas generated during the combustion of the fuel in the combustion chamber and in the process produce second energy. At least the air turbine and the exhaust gas turbine have a common housing.

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.