A turbomachine including a low-pressure shaft; a stator supporting the low-pressure shaft by bearings including a rear bearing; an electrical machine located at a rear portion of the turbomachine and including a rotor disconnectably driven by the low-pressure shaft and a stator surrounding the rotor and attached to the stator of the turbomachine; the turbomachine includes a journal for supporting the rotor of the electrical machine, the journal including a shaft segment releasably attached to a rear end of the low-pressure shaft by extending the low-pressure shaft, a frame to which the rotor of the electrical machine is attached and which surrounds the shaft segment, and at least one bearing mounted between the frame and the shaft segment; and a sleeve that is axially movable about the low-pressure shaft and/or the shaft segment that is rotationally connected to the low-pressure shaft and the shaft segment.

A hybrid propulsion system can include a turbomachine having a compressor, a combustion chamber, and a compressor turbine. The compressor can be connected to the compressor turbine via a first shaft. The system can include a hybrid drive assembly which can include a power turbine in fluid communication with an outlet of the compressor turbine to be driven by compressor turbine exhaust to drive a second shaft that is disconnected from the first shaft. The hybrid drive assembly can also include an electrical machine mechanically coupled to the second shaft either to convert rotational energy to electrical energy or to convert electrical energy to rotational energy of the second shaft.

The invention concerns land-based gas turbine plants with a two-spool gas turbine arrangement for generating electrical power. The invention comprises two spools. The first spool comprises a first shaft, a first compressor and a first turbine. The second spool comprises at least a second shaft and a second turbine. The shafts of the first and the second spools are independently rotatable of each other. The invention further comprises the first generator and the second generator having nominally substantially equal power ratings, and the rotating parts of the first generator and the second generator have nominally substantially equal rotational speed ratings, and at least 60 percent of a total output power supplied to said load in a form of electrical and rotational power is generated by the two electrical generators.

A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. The rotary component is rotatable with the compressor section and the turbine section. The gas turbine engine additionally includes an electric machine rotatable with the rotary component and positioned coaxially with the rotary component at least partially inward of the core air flowpath. The electric machine is flexibly mounted to a static frame member, or flexibly coupled to the rotary component, or both, such that the electric machine is mechanically isolated or insulated from various internal and external forces on the gas turbine engine.

In one aspect, the present disclosure is directed to a gas turbine starting system that includes a shaft coupling a compressor and a turbine. An annular housing extends circumferentially around the shaft such that the annular housing defines a compartment. A flange extends radially outward from the annular housing for mounting the annular housing to a stationary wall. A starter is positioned in the compartment. A collar rotatably couples to the annular housing and selectively couples to the starter. The collar includes a radially inner surface having a plurality of splines for engaging the shaft. The starter, when activated, rotates the collar, which rotates the shaft to start the gas turbine.

An aircraft fuel system includes a fuel tank, a fuel pump configured to receive a fuel flow from the fuel tank via a fuel supply line. The fuel system further includes a tap fluidly coupled to an outlet of the fuel pump, at least one generator or permanent magnet machine fluidly connected to the fuel pump via the tap, and the tap is configured to deliver fuel to the at least one generator or permanent magnet machine. The fuel system further includes a gearbox mechanically connected to the at least one generator or permanent magnet machine.

A propulsor is provided including a gas turbine engine having a shaft and one or more bearings supporting the shaft, a rotor hub operatively coupled to the shaft and comprising a hub flange, an electric machine comprising a stator assembly and a rotor assembly, a rotor connection member operatively coupled to the rotor assembly of the electric machine and comprising a connection flange, and an insulated joint for operatively coupling the rotor assembly with the shaft. The insulated joint includes a plurality of insulative layers, at least one of the plurality of insulative layers extending between the hub flange and the connection flange to interrupt common mode electric current from flowing between the rotor assembly and the shaft.

An electrical turbine generator is herein disclosed. The electrical turbine generator comprises a movable shaft and a rotor assembly. The rotor assembly comprises a plurality of blades not configured to compress gas and a generator rotor, the plurality of blades coupled to the generator rotor, the rotor assembly being supported by the movable shaft; a stator assembly including a plurality of stator windings electro-magnetically coupled to the rotor assembly; a housing supporting the rotor assembly and the stator assembly, the housing having an exhaust inlet opening and exhaust outlet opening, the exhaust inlet opening and the exhaust outlet opening aligned with the blades of the rotor assembly; and a power converter in communication with the stator windings to convert electrical energy induced in the stator windings into an output current having at least one of a steady frequency and a steady voltage.