Abstract: A method for generating a gas-product includes: a) providing a first part of a feed stream; b) providing a second part of a feed stream; c) combining the first part of the feed stream with the second part of the feed stream into the feed stream; d) heating at least one of: the first part of the feed stream, the second part of the feed stream before step c, the feed stream after step c; e) conducting the feed stream into a reactor; f) reacting the feed stream into the gas-product. To reduce investment and in particular the footprint of the machine step d) is at least partly performed by compressing the respective stream by a supersonic compressor such that the respective stream is heated.

Abstract: A compressor rotor comprising a pinion shaft which has multiple interconnected segments that are arranged axially one behind the other and including a multipart seal which seals the pinion shaft is provided. The pinion shaft has a rotor segment which supports a rotor, a connection segment, and a toothed segment arranged axially between the rotor segment and the connection segment, the toothed segment having a toothing at each of the two ends of the toothed segment. The toothed segment is held axially between the rotor segment and the connection segment via toothings by means of corresponding mating toothings at ends of the rotor segment and the connection segment, and a multipart seal sealing element which is connected to the toothed segment in an at least force-fitting manner is arranged on said toothed segment.

Abstract: A gas system has a first compressor stage for compressing a process gas. The first compressor stage includes an intake side and a pressure side. A seal gas is provided outside the first compressor stage in order to prevent process gas from issuing from leaks in the first compressor stage, having at least one second line for returning a gas mixture issuing from the gas system, this mixture including at least of process gas and seal gas. The at least one second line is configured for returning the issuing gas mixture to the intake side of the first compressor stage and/or to a location in the gas system upstream of the first compressor stage.

Abstract: A compressor rotor comprising a pinion shaft which has multiple interconnected segments that are arranged axially one behind the other and including a multipart seal which seals the pinion shaft is provided. The pinion shaft has a rotor segment which supports a rotor, a connection segment, and a toothed segment arranged axially between the rotor segment and the connection segment, the toothed segment having a toothing at each of the two ends of the toothed segment. The toothed segment is held axially between the rotor segment and the connection segment via toothings by means of corresponding mating toothings at ends of the rotor segment and the connection segment, and a multipart seal sealing element which is connected to the toothed segment in an at least force-fitting manner is arranged on said toothed segment.

Abstract: A gas system has a first compressor stage for compressing a process gas. The first compressor stage includes an intake side and a pressure side. A seal gas is provided outside the first compressor stage in order to prevent process gas from issuing from leaks in the first compressor stage, having at least one second line for returning a gas mixture issuing from the gas system, this mixture including at least of process gas and seal gas. The at least one second line is configured for returning the issuing gas mixture to the intake side of the first compressor stage and/or to a location in the gas system upstream of the first compressor stage.

Abstract: A nose dome for a turbomachine rotor is provided. The turbomachine rotor has an impeller which is arranged in an overhung fashion with respect to a bearing point of the turbomachine rotor. The nose dome can be connected axially to the impeller in order to guide an axial inflow and/or outflow of the impeller, and includes a coupling device. The impeller and the nose dome can be mechanically coupled radially with the coupling device, such that the vibration behavior of the turbomachine rotor may be influenced. The turbomachine with the turbomachine rotor including the nose dome is also provided. The impeller and nose dome are coupled radially using the coupling device, such that the vibration of the turbomachine rotor is damped.

Abstract: A method is provided where carbon dioxide is compressed in a multi-stage geared compressor using a substantially isothermic process to a pressure which lies above the pressure of the critical point of carbon dioxide. The carbon dioxide is subsequently cooled to ambient temperature in a cooling device and then compressed to a predefined final pressure in a pump device.

Abstract: A method is provided where carbon dioxide is compressed in a multi-stage geared compressor using a substantially isothermic process to a pressure which lies above the pressure of the critical point of carbon dioxide. The carbon dioxide is subsequently cooled to ambient temperature in a cooling device and then compressed to a predefined final pressure in a pump device.

Abstract: A nose dome for a turbomachine rotor is provided. The turbomachine rotor has an impeller which is arranged in an overhung fashion with respect to a bearing point of the turbomachine rotor. The nose dome can be connected axially to the impeller in order to guide an axial inflow and/or outflow of the impeller, and includes a coupling device. The impeller and the nose dome can be mechanically coupled radially with the coupling device, such that the vibration behavior of the turbomachine rotor may be influenced. The turbomachine with the turbomachine rotor including the nose dome is also provided. The impeller and nose dome are coupled radially using the coupling device, such that the vibration of the turbomachine rotor is damped.