The present disclosure provides a novel turbine design for converting a high-pressure fluid stream into useful energy, the turbine comprising a cylindrical housing having a fluid inlet and fluid outlets on opposing ends and being constrained by rotational bearings, with the housing containing a multi-helical structure for efficiently directing the fluid flow from the inlet to the outlets with minimal strain on the moving components. A method of use of the turbine for generating energy is also provided.

A screw rocket nozzle may include a disc shaped nozzle body and a spiral flow path having an inlet and an outlet. In some examples the flow path is radial with the inlet positioned at a higher pressure region than the outlet.

A turbine for a power plant unit for a hybrid power plant is arranged in a turbine housing in which a flow channel for a compressible medium is arranged. A drive shaft and at least one output impeller are arranged in the flow channel, the output impeller containing an output shaft for operating a generator, wherein the output impeller is connected in a rotationally fixed manner to the output shaft. The drive shaft is not connected to the output shaft.

A turbine for a power plant unit for a hybrid power plant is arranged in a turbine housing in which a flow channel for a compressible medium is arranged. A drive shaft and at least one output impeller are arranged in the flow channel, the output impeller containing an output shaft for operating a generator, wherein the output impeller is connected in a rotationally fixed manner to the output shaft. The drive shaft is not connected to the output shaft.

A turbine for a power plant unit for a hybrid power plant is arranged in a turbine housing in which a flow channel for a compressible medium is arranged. A drive shaft and at least one output impeller are arranged in the flow channel, the output impeller containing an output shaft for operating a generator, wherein the output impeller is connected in a rotationally fixed manner to the output shaft. The drive shaft is not connected to the output shaft.

A boundary-layer turbomachine coupled to a shaft for transmitting power, comprising a plurality of ducts, and a plurality of blades and/or one or more protrusions. The plurality of ducts are defined by duct walls configured to rotate about the longitudinal axis and are concentrically arranged thereabout to convey fluid between inlet and outlet ends. Flow inlets draw the fluid into the plurality of ducts at least partially azimuthally around the longitudinal axis towards the outlet end. The plurality of blades and/or one or more protrusions extend radially in the duct between opposing duct walls. The one or more protrusions may spirally extend at least partially along and around the longitudinal axis to induct fluid into the duct. Slots may be provided in duct walls for centrifugal separation of liquid phase. Systems and methods of generating power using a plurality of boundary-layer turbines, including without condensers, pumps, and/or compressors.

A screw rocket nozzle may include a disc shaped nozzle body and a spiral flow path having an inlet and an outlet. In some examples the flow path is radial with the inlet positioned at a higher pressure region than the outlet. In other examples the flow path is axial with the inlet positioned at a lower pressure region than the outlet. The nozzle may rotate about its center as a turbine in an axial configuration.

An electrical generator, comprising a rotatable impeller locatable within a flow path of a conduit. The impeller is rotated by fluid flowing along said flow path. The impeller comprises a magnetic portion, the generator further including a stator located external of the flow path. The stator generating electrical power in response to rotation of the magnetic portion.

A gas turbine engine includes a compressor configured to receive inlet air at a compressor inlet and generate compressed air at a compressor exit, a combustor positioned fluidically and physically downstream of the compressor, a turbine positioned fluidically and physically downstream of the combustor, and a shaft mechanically connecting the turbine and the compressor. The combustor is fluidically connected to the compressor to receive a first portion of the compressed air as combustor primary inlet air. The combustor includes a combustor liner having an inner combustor liner and an outer combustor liner, surrounding one or more combustion zones. A cooling air flow path is configured to direct a second portion of the compressed air around the outer combustor liner to cool the combustor liner and to provide a source of quench air, inner combustor liner cooling air, fuel injector air, and combustor secondary inlet air.

A gas turbine engine includes a compressor configured to receive inlet air at a compressor inlet and generate compressed air at a compressor exit, a combustor positioned fluidically and physically downstream of the compressor, a turbine positioned fluidically and physically downstream of the combustor, and a shaft mechanically connecting the turbine and the compressor. The combustor is fluidically connected to the compressor to receive a first portion of the compressed air as combustor primary inlet air. The combustor includes a combustor liner having an inner combustor liner and an outer combustor liner, surrounding one or more combustion zones. A cooling air flow path is configured to direct a second portion of the compressed air around the outer combustor liner to cool the combustor liner and to provide a source of quench air, inner combustor liner cooling air, fuel injector air, and combustor secondary inlet air.