Abstract: A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. The shaft includes a main shaft and a flex shaft having bellows. The flex shaft is secured to the main shaft at a first end and includes a second end opposite the first end. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supports the shaft relative to the inlet case. The second bearing is arranged radially outward from the flex shaft.

Abstract: A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.

Abstract: A gearbox has a first rotative component and a second rotative component, the gearbox having a rotary input and a rotary output, a first brake for braking the first rotative component of the gearbox against rotation thereof, and a second brake for braking the second rotative component of the gearbox against rotation thereof. The rotary input drives the rotary output if the first brake brakes the first rotative component of the gearbox and the rotary output drives the first rotative component of the gearbox if the second brake brakes the second rotative component of the gearbox.

Abstract: A gas turbine engine arrangement comprises a first gas turbine engine, a second gas turbine engine, a differential gearbox and an electrical generator. The differential gearbox has a first input drive, a second input drive and an output drive. The output drive of the differential gearbox is arranged to drive the electrical generator via an external, accessory, gearbox. The external, accessory, gearbox drives other accessories. The first gas turbine is arranged to drive the first input drive of the differential gearbox and the second gas turbine engine is arranged to drive the second input drive of the differential gearbox. The electrical generator and accessories are driven at a constant frequency speed/frequency.

Abstract: A gas turbine engine includes a core housing providing a core flowpath. A shaft supports a compressor section arranged within the core flowpath. First and second bearings support the shaft relative to the core housing and are arranged radially inward of and axially overlapping with the compressor section.

Abstract: A gas turbine engine includes a spool, a turbine coupled to drive the spool and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the spool drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 16 of the propulsor blades.

Abstract: An open-rotor gas turbine engine comprising a starter/generator, a first spool and a second spool, the second spool is of a lower pressure than the first spool; wherein the starter/generator is connected to the first and second spools via first and second clutches respectively. The method of operating the open-rotor engine comprises the step of supplying power to the starter/generator to drive the first spool via the first clutch to start the engine and, once the engine is self-propelling, a step of driving the starter/generator from the second spool via the second clutch to generate electricity.

Abstract: A jet engine (1) includes at least one emergency drive unit (10), with the jet engine (1) having at least one engine shaft (2a) coupled via at least one gear train (4) with at least one auxiliary gearbox (7), which is connected to at least one auxiliary equipment (8), especially an electric generator. The emergency drive unit (10) includes at least one rotatable component. In order to provide a jet engine with an emergency drive unit in a simple configuration, the rotatable component of the emergency drive unit (10) is attached to the gear train (4).

Abstract: A gas turbine engine is provided, including an air inlet in fluid communication with a compressor, a combustor, a compressor turbine, and a power turbine. The compressor and compressor turbine may be mounted on a first drive shaft, and the power turbine may be mounted on a second shaft. The engine further includes an engagement mechanism adapted to selectively engage the first drive shaft to the second drive shaft, wherein the first drive shaft and second drive shaft rotate at substantially the same speed when the engagement mechanism is engaged. The disclosed multi-spool gas turbine engine provides improved part power fuel consumption at reduced output shaft speeds. The proposed invention can relate to turbines with two or more gas generator spools.

Abstract: The invention relates to a combination power plant which is embodied as a single shaft, power plant, essentially consisting of a gas turbine, a steam turbine and a generator which is connected therebetween. A coupling is arranged between the generator and the steam turbine, and at least one drive device, which is used to drive the single-shaft power plant, is also provided. The coupling is uncoupled during a turning operation and a control unit, which is used to control the rotational speed of the steam turbine, is provided.

Abstract: A device for producing electrical power in a multi-spool gas turbine engine is disclosed. The device includes at least one first rotary spool and a second rotary spool which drives an electrical machine. The electrical machine is of the twin-rotor type with a first rotor and a second rotor. The first rotor is mechanically connected to the first rotary spool and the second rotor is mechanically connected to the second rotary spool.

Abstract: A turbine engine power generation system includes a gearbox that receives rotational drive from a low spool through an input gear, in one example. The gearbox includes first and second clutches that are coupled to an input shaft of an auxiliary component, such as a generator. First and second output gears are driven at different rotational speeds by the input gear and respectively associated with the first and second clutches. An actuator selectively engages at least one of the first and second clutches to select between first and second rotational speeds in response to a command from a controller.

Abstract: A turbine engine includes low and high pressure spools. A high power take-off shaft is coupled to the high spool. An auxiliary component, such as a generator, is configured to be driven by the high power take-off shaft at a first speed. The low spool, in part, drives the auxiliary component, for example, by interconnecting the high power take-off shaft to a lower power take-off shaft through a speed summing gearbox. The gearbox drives the auxiliary component and increases the rotational speed of the auxiliary component from the first speed to the second speed. The low power take-off shaft also drives another generator, in one example. The turbine engine can be started by the low pressure generator, for example, in response to a command from a controller, which transforms the generator into a starter motor.

Abstract: A method of emergency operation of an aircraft turbofan engine during an aircraft flight is provided. The engine includes a fan shaft with a fan, and an electric motor/generator mounted for rotation therewith. The method includes shutting down the engine while allowing the engine to windmill, operating the electric motor/generator to rotate the shaft at a determined windmilling speed which is desired for the fan shaft, and operating the engine at the desired windmilling speed for substantially a remainder of the aircraft flight.

Abstract: With a two-shaft engine, the accessory drive gearbox (5) for the operation of a generator and other auxiliaries (6) is connected to the high-pressure shaft (1) via a high-pressure shaft gearbox (3), which is coupled to a low-pressure shaft gearbox (8) connecting to the low-pressure shaft (7), via an overrunning clutch (11), a conical-pulley variable transmission (10) settable on the basis of the shaft speed on both sides, and a first switchable clutch (9). Under certain operating conditions with low speed of the high-pressure shaft or in case of engine failure, the power of the low-pressure shaft, with the clutch (9) engaged, is transferred to the high-pressure shaft gearbox and hence to the accessory drive gearbox via the conical-pulley variable transmission, which compensates for shaft speed difference, and the overrunning clutch, in order to reliably further operate the generator and other accessories with low fuel consumption or by windmilling only.

Abstract: Several improvements to an aircraft turbine engine and Auxiliary Power Unit (APU) are disclosed, as well as methods of using these improvements in routine and emergency aircraft operations. The improvements comprise the addition of cockpit-controllable clutches that can be used to independently disconnect the engine's integrated drive generator (IDG), engine driven pump (EDP), fuel pump, and oil pump from the engine gearbox. These engine components may then be connected to air turbines by the use of additional clutches and then powered by the turbines. Similar arrangements are provided for the APU components. Cranking pads, attached to various engine and APU components, are disclosed to provide a means for externally powering the components for testing purposes and to assist with engine and APU start.

Abstract: A system for transferring mechanical torque variably between a plurality of rotating machines in a turbofan engine. Two devices are used, where the first device relies upon magnetic properties of a planetary magnetic gearbox to couple the magnetic machines. The second device is used to variably control the torque transfer between the magnetic machines. The system couples rotating shafts rotating at differing speeds within a turbofan engine for controllably transferring power. To transfer power in the system, a fixed gear ratio is obtained by coupling the relatively high- and low-speed engine shafts to an epicyclic magnetic gearbox.

Abstract: A shaft coupling device to couple first and second shafts, said device comprising a fluid coupling having a first portion attached to the first shaft and a second portion attached to the second shaft wherein the device further comprises engagement means operable to switch the device between an engaged position and a disengaged position, the engaged position having each of the first and second shafts engaged with its respective portion of the fluid coupling and the disengaged position having at least one of the first and second shafts disengaged from its respective portion of the fluid coupling.

Abstract: A power transmission arrangement comprises a first power transmission member connectable to a first main shaft of an engine. The arrangement also includes a second power transmission member connectable to a second main shaft of the engine and to a third power transmission member. A coupling assembly is provided which has a selectable coupling condition to couple the first power transmission member to the second power transmission member to allow power to be transmitted from the third power transmission member to the first main shaft of the engine via the first power transmission member. The coupling assembly has a decoupling condition to decouple the first power transmission member from the second power transmission member to allow power to be transmitted from the main shaft of the engine to the third power transmission member via the second power transmission member.

Abstract: A system for driving first and second accessory machines of a double-bodied turbine engine with an LP shaft and an HP shaft is disclosed. The system includes a first power train disposed between the shaft of the HP rotor and the first machines, which mechanically drives the first machines, and a first coupling means and a second power train between the shaft of the LP rotor and the second machines arranged so as to drive the said second machines. The system also includes a second coupling means between the first power train and the second power train allowing the second accessory machines to be driven by the shaft of the HP rotor, particularly when the engine operates at high speeds. The system may include a gearbox with at least two speed ratios and the first coupling means may be arranged to selectively couple one or other of the two ratios or else to decouple the mechanical transmission from the shaft of the LP rotor.

Abstract: A hybrid engine installation (200) includes drive element (204) suitable for driving a mechanical element (BTP, BTA) in rotation. In addition, the hybrid engine installation is remarkable in that it includes at least one gas turbine (253, 254) and at least one electric motor (201) mechanically linked to the drive element (204) to drive it in rotation.

Abstract: A turbine combustion chamber is provided with deflectors on the cold side generating vortices in a secondary gas flow into the chamber, thereby confining the flame front under variable operating conditions and cooling the chamber walls. The high-speed cantilever shaft has a longitudinal duct and an array of fine orifices in the wall of the shaft for directing pressurized oil jets that impinge on the shaft bearings with little relative speed to increasing wetting of the bearing components. Oil is supplied to the duct by means of a positive-displacement pump directly driven by the output shaft. The pump output pressure is monitored to signal the end of the start-up sequence when the turbine reaches sufficient speed. The turbo-engine further includes devices for decoupling vibrations between the three systems thereof, including a loosely-mounted removable spline pivotable at both ends for coupling the high-speed shaft to the step-down gearbox.

Abstract: A turbofan gas turbine propulsion engine includes a system to transfer power from the low pressure turbine to the high pressure turbine and/or extract additional load from the low pressure turbine during certain turbofan engine operational conditions. The systems include a hydrostatic power transfer system that includes a hydraulic pump and a hydraulic motor coupled to the low pressure and high pressure turbine, respectively. The systems additionally include a mechanical and electrical load shifting/loading sharing systems that use clutches and gear assemblies to share and/or shift load between the turbines.

Abstract: A turbine engine includes low and high pressure spools. A high power take-off shaft is coupled to the high spool. An auxiliary component, such as a generator, is configured to be driven by the high power take-off shaft at a first speed. The low spool, in part, drives the auxiliary component, for example, by interconnecting the high power take-off shaft to a lower power take-off shaft through a speed summing gearbox. The gearbox drives the auxiliary component and increases the rotational speed of the auxiliary component from the first speed to the second speed. The low power take-off shaft also drives another generator, in one example. The turbine engine can be started by the low pressure generator, for example, in response to a command from a controller, which transforms the generator into a starter motor.

Abstract: A power transmission arrangement comprises a first power transmission member connectable to a first main shaft of an engine. The arrangement also includes a second power transmission member connectable to a second main shaft of the engine and to a third power transmission member. A coupling assembly is provided which has a selectable coupling condition to couple the first power transmission member to the second power transmission member to allow power to be transmitted from the third power transmission member to the first main shaft of the engine via the first power transmission member. The coupling assembly has a decoupling condition to decouple the first power transmission member from the second power transmission member to allow power to be transmitted from the main shaft of the engine to the third power transmission member via the second power transmission member.

Abstract: A drivetrain for a multi-spool counter rotating gas turbine engine may include a lay shaft for connecting a power turbine shaft of the engine with a gas generator shaft of the engine when the drivetrain is in engine start mode. In normal operation mode, an actuator disengages the lay shaft, thereby allowing free and independent rotation of the power turbine shaft and the gas generator shaft.

Abstract: A device is provided which can serve one or more of the multiple functions of impeding rotation of a shaft de-coupled turbine rotor, selectively impeding rotation of a first spool of the engine, for example to permit a second spool to generate power for use in ground operation, and facilitating reduced aircraft ground speed.

Abstract: A synchronizing stationary clutch system for compression braking in a two spool gas turbine engine is provided by the present invention. The synchronizing stationary clutch system allows the two shafts of a two spool gas turbine engine to be reliably coupled at any given speed of either shaft. This coupling ability is useful to a gas turbine engine functioning in a land vehicle for the purpose of slowing the forward momentum of a rolling vehicle. The clutch system may also allow the use of auxiliary power from an electrical motor to start the engine.

Abstract: Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a supercharger compressor, which may provide compressed air at increased altitudes. The supplemental power system disclosed herein provides necessary shaft horsepower at high altitudes to drive a generator and produce cooling air.

Abstract: Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a supercharger compressor, which may provide compressed air at increased altitudes. The supplemental power system disclosed herein provides necessary shaft horsepower at high altitudes to drive a generator and produce cooling air.

Abstract: A synchronizing stationary clutch system for compression braking in a two spool gas turbine engine is provided by the present invention. The synchronizing stationary clutch system allows the two shafts of a two spool gas turbine engine to be reliably coupled at any given speed of either shaft. This coupling ability is useful to a gas turbine engine functioning in a land vehicle for the purpose of slowing the forward momentum of a rolling vehicle. The clutch system may also allow the use of auxiliary power from an electrical motor to start the engine.

Abstract: An emergency device for relighting a windmilling turbojet, the jet comprising a fan driven by a low-pressure turbine via a first shaft and a compressor driven by a high-pressure turbine via a second shaft disposed coaxially around the first shaft, a differential interconnecting said first and second shafts while compensating for their different speeds of rotation in normal operation or the turbojet, and a braking system connected to the differential so as to enable it to be slowed down or blocked when the turbojet shuts down, thereby enabling the first shaft to entrain the second shaft so that it reaches a speed that favors relighting of the turbojet.

Abstract: A combined cycle power plant generally comprises a gas turbine power facility, a heat recovery steam generator, a steam turbine power facility, and an existing boiler. The power generation plant further comprises a system for introducing steam, which is generated in the heat recovery steam generator and the existing boiler, to the steam turbine of the steam turbine power facility through steam lines, which extend from the existing boiler and heat recovery steam generator and are then joined together, and a system for causing a line, which is arranged on a downstream side of a condenser provided in the steam turbine power facility, to branch off into feedwater lines, and supplying condensed water condensed by the condenser into the heat recovery steam generator and the existing boiler.

Abstract: An aero-engine is provided with an integrated switched reluctance generator permanently connected to the low speed spool of the engine such that “windmilling” of the engine enables the generator to be turned if the engine suffers a flame out. The generator is driven by a step up gearbox so as to provide reasonable electrical output, say 25 kW, during flameout whilst keeping the generator weight down.