The invention concerns land-based gas turbine plants with a multi-spool gas turbine arrangement for generating electrical power to supply a load (200). The invention comprises at least three spools (10a-10c). Each of the at least three spools (10a-10c) comprises a shaft (11a-11c), a compressor (C1-C3) and a turbine (T1-T3). Each one of the shafts (11a-11c) of the at least three spools (10a-10c) are independently rotatable with respect to each other. The invention further comprises electrical generators (G1-G3) mounted on each of the shafts (11a-11c) of the at least three spools (10a-10c), the output power of the generators being independently controllable and at least 60 percent of a total output power supplied to said load (200) in a form of electrical and rotational power is generated by the at least three generators (G1-G3) in the form of electrical energy.

A propulsion system for an aircraft comprises a gas generator including a turbine driving a main drive shaft, the main drive shaft, in turn, driving at least two fan drive shafts, wherein the at least two fan drive shafts are driven on non-coaxial axes, the fan drive shaft each driving a fan rotor through a fan drive system. A fan lubrication system provides lubrication to each of the fan drive systems.

A multi-stage turboexpander and a method for generating mechanical power therewith are disclosed. The multi-stage turboexpander includes a casing and a shaft, arranged for rotation in the casing. The shaft is supported by a first bearing at a first shaft end portion and a second bearing at a second shaft end portion. A first radial impeller and a second radial impeller are arranged between the first bearing and the second bearing on the shaft for co-rotation therewith around a rotation axis.

A turbomachine train with two shaft parts which each have a fixedly attached grooved wheel, with a first overrunning clutch, with two rotational speed sensors and with a control device. The clutch is designed to couple and decouple the first shaft part to and from the second shaft part. The first rotational speed sensor measures the rotational speed of the first grooved wheel. The second rotational speed sensor measures the rotational speed of the second grooved wheel. The control device determines the differential angle between the first shaft part and the second shaft part and accelerates the turbomachines, with an acceleration value determined on the basis of the measured rotational speeds and on the basis of the differential angle, such that the two shaft parts couple together at a predetermined target coupling angle.

A rotary system capable of maintaining a distance of separation between two rotary machines and inhibiting vibration in an intermediate shaft connecting rotary shafts of the two rotary machines to each other. The rotary system includes a first rotary machine having a first rotary shaft, a second rotary machine having a second rotary shaft, and an intermediate shaft device having an intermediate shaft main body having a first end portion connected to the first rotary shaft and a second end portion connected to the second rotary shaft and rotating about an axis and a plurality of bearing devices slidably supporting the intermediate shaft main body.

A two-shaft gas turbine having high operability is provided. The two-shaft gas turbine includes: a gas generator having a compressor, a combustor and a high pressure turbine; a power turbine having a low pressure turbine; a load connected to the power turbine; a motor/generator capable of rotatably driving the gas generator and capable of extracting power from the gas generator; electric equipment controlling the rotational driving and the power extraction by delivering electric power between the electric equipment and the motor/generator; and a control device controlling the electric equipment, wherein the combustor has a plurality of combustion regions to which a fuel is supplied through fuel adjustment means which are independent from each other, and the control device controls a delivery amount of the electric power delivered by the electric equipment corresponding to the number of combustion regions to which the fuel is supplied.

A decoupled gas turbine engine includes a high spool assembly and a low spool assembly each having a rotational axis that are spaced from one-another. The engine further includes a combustor that may have a centerline spaced from the rotational axes of each spool assembly. Turning ducts of the engine are configured to re-direct airflow from one spool assembly to the next and/or between one spool assembly and the combustor.

A method for coupling a first sub-shaft, which has a first turbomachine and a generator connected to a mains supply, to a second sub-shaft, which has a second turbomachine, by means of an overrunning clutch, has the following steps: a) rotating the second sub-shaft with a starting rotational speed which is lower than the rotational speed of the first sub-shaft; b) measuring the mains frequency of the mains supply; c) measuring a differential angle between the first sub-shaft and the second sub-shaft; d) accelerating the second sub-shaft with an acceleration value which is produced using the mains frequency measured in step b), the differential angle and the starting rotational speed, and therefore the overrunning clutch couples the two sub-shafts to each other with a previously determined target coupling angle.

A propulsion system for an aircraft comprises a gas generator including a turbine driving a main drive shaft, the main drive shaft, in turn, driving at least two fan drive shafts, wherein the at least two fan drive shafts are driven on non-coaxial axes, the fan drive shaft each driving a fan rotor through a fan drive system. A fan lubrication system provides lubrication to each of the fan drive systems.

There is provided an engine assembly for an aircraft, comprising a heat engine in driving engagement with an engine shaft having a first end coupled to a mechanical gearbox and a second end opposite the first end, an electric generator coupled to the second end to provide a generator output voltage, the electric generator separate from the mechanical gearbox, a power electronics module connected to the electric generator and configured to regulate the generator output voltage to provide a regulated output voltage that meets an electrical power demand of at least one aircraft accessory, and a voltage bus connected to the power electronics module and configured to supply the regulated output voltage to the at least one aircraft accessory.