A gas turbine power plant comprises a gas turbine, a power turbine, a clutch, an electrical generator and a controller. The power turbine is fluidly connected to the gas turbine without any mechanical connection. The clutch comprises an input mechanically connected to the power turbine and an output mechanically connected to the electric generator. The controller can identify that a speed of the electric generator is greater than a speed of the power turbine, determine a difference between the speed of the electric generator and the power turbine, in response to the difference being greater than a threshold, control the gas turbine to a first maximum acceleration of the power turbine, and in response to the difference being equal or less than to the threshold, control the gas turbine to a second maximum acceleration of the power turbine that is less than the first maximum acceleration.

Shaft stability is enhanced and reliability is improved. In a gas turbine power generation system of an embodiment, a pressurizing unit, a rotation control unit, a diaphragm coupling, a turbine, and a generator are disposed to line up sequentially on the same shaft. A thrust bearing is provided between the turbine and the generator. The turbine is configured such that a working medium flows from the diaphragm coupling side toward the rotation control unit side.

In one embodiment, a plant control apparatus includes a first stop controller configured to, when stopping a plant, stop a steam turbine to start to drop rotating speed of a second shaft of the steam turbine from rated speed, and start to drop rotating speed of a first shaft of a gas turbine from the rated speed while continuing combustion of a combustor after the stop of the steam turbine. The apparatus further includes a second stop controller configured to shut off fuel of the combustor to stop the gas turbine when the rotating speed of the first shaft drops to first speed. The second stop controller stops the gas turbine such that the rotating speed of the first shaft catches up with the rotating speed of the second shaft at second speed that is equal to or lower than the first speed and a clutch is engaged.

A single unducted rotor engine includes a power source; a casing surrounding the power source; an unducted rotor assembly driven by the power source having a single row of rotor blades; and an outlet guide vane assembly having a plurality of pairs of outlet guide vanes, each pair of the plurality of pairs of outlet guide vanes including a first outlet guide vane extending from the casing at a location downstream from the single row of rotor blades of the unducted rotor assembly and a second outlet guide vane also positioned downstream from the single row of rotor blades of the unducted rotor assembly. The first outlet guide vane of each pair of outlet guide vanes defines a first geometry. The second outlet guide vane of each pair of outlet guide vanes defines a second geometry. The first geometry is not equal to the second geometry.

The gas turbine generator includes: a first gas turbine element 2; a second gas turbine element 3; a single combustor 4 connected to the gas turbine elements 2 and 3; a first supply pipe 51 that connects the first compressor 21 to the combustor 4; a second supply pipe 52 that connects the second compressor 31 to the combustor 4; a first discharge pipe 53 that connects the combustor 4 to the first turbine 22; a second discharge pipe 54 that connects the combustor 4 to the second turbine 32; and a flywheel 7 that is connected to at least one of the first rotation shaft 23 and the second rotation shaft 33 and absorbs a torque fluctuation generated in the connected gas turbine element.

Gas turbine engines and methods of their operation are provided. For example, a method of operating a gas turbine engine comprises selectively engaging and disengaging an engine clutch disposed between a low speed spool and a rotor assembly of the engine. Engagement or disengagement of the engine clutch is selected based on an operating condition of an aircraft comprising the engine. Further, an inter-spool clutch disposed between the low speed spool and a high speed spool of the engine transitions between engaged and disengaged, disengaging when the high speed spool reaches a speed greater than an operational speed of the low speed spool. Similarly, a gas turbine engine comprises an engine clutch configured to selectively position a low speed spool in operative communication with a rotor assembly and an inter-spool clutch configured to position the low speed spool in operative communication with a high speed spool.

The present invention relates to a generator drive disconnect device, of a generator arranged to be driven by an aircraft engine. The disconnect device comprises: a drive transfer means (1) having a first, connected configuration, and a second, disconnected configuration; a disconnect biasing means (200), configured to bias the drive transfer means to the disconnected configuration; and a fluid cavity (300), configured such that provision of a pressurised fluid in the fluid cavity biases the drive transfer means to the connected configuration.

A pumping device for a vehicle seat is proposed. The pumping device includes: a housing made of plastic, including a bottom surface having a through hole, a side wall arranged along an outer circumferential surface of the bottom surface, and an open upper surface, with a clutch device and a brake device, and a lever being connected to the housing at an outside of the bottom surface through the through hole so that the housing is configured to transmit drive force from the lever to the clutch device; and a housing cover made of metal, including a first side surface covering the open upper surface of the housing, a plurality of bending parts at an edge thereof such that the bending parts are bent toward the housing to achieve coupling between the housing cover and the housing, and a second side surface coupled to a seat frame.

A rotational position of a variable-vane of a variable-vane turbine nozzle upstream of a turbine of a gas-turbine engine is biased towards a corresponding rotational position that will mitigate against an overspeed condition of the turbine during operation of the gas-turbine engine. When the turbine is operating at a rotational speed that is less than an overspeed threshold, the rotational position of the variable-vane is controlled independently of the biasing using a variable-vane actuator operatively coupled to the variable-vane. Responsive to a rotational speed of the turbine in excess of the overspeed threshold, the variable-vane actuator is operatively decoupled from the variable-vane so as to provide for the variable-vane to be repositioned towards the corresponding rotational position that will mitigate against the overspeed condition.

A gas turbine engine is provided. The gas turbine engine defines a radial direction. The engine includes: an airfoil positioned within an airflow and extending between a root end and a tip along the radial direction; and a mount coupled to or formed integrally with the root end of the airfoil for mounting the airfoil to the engine, the mount including an outer surface along the radial direction exposed to the airflow and defining an air-cooling channel extending between an inlet and an outlet, the inlet positioned on the outer surface of the mount.