A device for driving an integrated generator from an accessories relay box of a turbomachine. The device includes first and second electric motors arranged to transfer electric power from one to the other, one or more controllers configured for controlling said electric motors, and an epicyclic reduction gear train. The gear train includes a first element intended to be coupled to the accessories relay box, a second element intended to be coupled to the generator, and a third element driven to rotate by said first electric motor. The control means are configured to modify the speed of rotation of the third element in such a way that the second element is driven to rotate at a constant speed.

Embodiments of a direct-drive fan system and a variable process control system are disclosed herein. The direct-drive fan system and the variable process control system efficiently manage the operation of fans in a cooling system such as a wet-cooling tower or air-cooled heat exchanger (ACHE), HVAC systems, mechanical towers or chiller systems.

An engine housing of a gas turbine engine includes a plurality of leg members. An air intake space is formed between the plurality of leg members. A shroud case supported by the engine housing is disposed in the air intake space. A rotary electric machine housing of a rotary electric machine system includes a rectifying member. The rectifying member includes a distal end facing toward the shroud case, and the distal end is inserted inside the shroud case.

A hybrid-electric propulsion system is provided. In one example aspect, the hybrid-electric propulsion system includes a power converter and a propulsor. The propulsor includes a gas turbine engine having a shaft and one or more bearings supporting the shaft. The propulsor also includes an electric machine electrically coupled with the power converter. The electric machine includes a stator assembly and a rotor assembly. The rotor assembly has a rotor and a rotor connection assembly. The rotor connection assembly operatively couples the rotor with the shaft. The rotor connection assembly has an insulated joint for interrupting common mode electric current from flowing from the rotor of the electric machine to the shaft. A grounding device is included to electrically ground the shaft. The power converter includes an electromagnetic interference filter to reduce common mode voltage reaching the electric machine.

A power generation system includes a shroud that defines a fluid flow path. A gas turbine engine is in the fluid flow path, and the gas turbine engine includes a compressor, a combustor downstream from the compressor, and a turbine downstream from the combustor. An electric generator is in the fluid flow path upstream from the compressor. The electric generator includes a rotor coaxially aligned with the turbine, and the turbine and the rotor rotate at the same speed.

A method is provided for maintaining a gas turbine engine installed on an aircraft, the gas turbine engine including an electric machine mounted at least partially inward of a core air flowpath of the gas turbine engine. The method includes removing a rotor mount connecting a rotor of the electric machine to a rotary component of the gas turbine engine; removing a stator mount connecting a stator of the electric machine to a stationary component of the gas turbine engine; and removing in situ the electric machine.

A system includes a clutchless synchronous condensing coupling configured to couple a turbine shaft of a gas turbine system to a generator shaft of a synchronous generator of a power generation system. The clutchless synchronous condensing coupling includes a first coupling portion configured to couple to the turbine shaft, and a second coupling portion configured to couple to the generator shaft. The clutchless synchronous condensing coupling is configured to allow the power generation system to operate in an active power mode and a reactive power mode without a clutch assembly.

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 electrical generator is housed in an annular cavity between the casing and the propeller shaft of a turboprop, while imposing little or no additional space requirement and with lightweight ancillary equipment. The rotor of the generator is mounted on an autonomous shaft end. A flange of the outer casing is removable in order to access the generator and to enable its easy removal and remounting.

A generalized frequency conversion system for a steam turbine generator unit. The system comprises at least a variable speed steam turbine with an adjustable rotating speed, a water feeding pump, a variable frequency generator operating at a variable speed, a speed increasing gearbox with a fixed rotating speed ratio, a variable frequency bus and an auxiliary machine. With a change in load of the unit, parameters of steam entering the variable speed steam turbine and an extracted steam amount are adjusted (changed) accordingly, so that the rotating speed of the steam turbine changes accordingly. In this way, on one hand, the rotating speed of the water feeding pump is changed through the speed increasing gearbox; and on the other hand, the frequency of alternating current outputted by the variable frequency generator is changed. In the present invention, there is no need to additionally provide other types of frequency converters, and the system is simple, reliable, low in cost and high in efficiency.