A gas turbine engine assembly (10), includes a core gas turbine engine (12), a low-pressure turbine (14) coupled to the core turbine engine, a counter-rotating fan assembly (16) coupled to the low-pressure turbine, and a booster compressor (24) coupled directly to the low-pressure turbine such that the booster compressor and the low-pressure turbine rotate in the same direction.

Gas turbine engine assembly and methods of assembling same

A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached.

Reconfigurable battery-operated vehicle system

An engine power extraction control system controls the main propulsion engines and the electrical machines that are coupled thereto to supply an appropriate amount of aircraft thrust and electrical energy to the aircraft. The engines and electrical machines are also controlled so that the propulsion thrust that is generated is split between the various turbines in the main propulsion engines to maintain an adequate surge margin and to minimize residual thrust generation.

Engine power extraction control system

A turbofan gas turbine propulsion engine includes a multi-speed transmission between the high pressure and low pressure turbines and associated high pressure and low pressure starter-generators. The multi-speed transmission reduces the operating speed range from the low pressure turbine to its associated starter-generator, and is configurable to allow the starter-generator associated with the low pressure turbine to supply starting torque to the engine.

More electric aircraft starter-generator multi-speed transmission system

A two-stage turbofan system for use in a gas turbine engine comprises a first-stage fan shaft, a second-stage fan shaft, a stationary torque tube and a gear system. The second-stage fan shaft connects with a drive shaft in the gas turbine engine such that the second-stage fan shaft is driven at the speed of the drive shaft. The stationary torque tube is connected with a fan case in the gas turbine engine. The gear system is connected to the second-stage fan shaft and the torque tube. The first-stage fan shaft extends from the gear system such that the first-stage fan shaft is driven at a speed reduced from that of the drive shaft.

Epicyclic gear train for turbo fan engine

A method and apparatus for controllable distribution of power from a turbine of a gas turbine engine between two rotatable loads of the gas turbine engine, comprises transferring a shaft power of the turbine to the respective rotatable loads using differential gearing operatively coupled with the turbine and the rotatable loads, respectively; and controlling the power transfer using machines operatively coupled with the respective rotatable loads, operable as a generator or a motor for selectively taking power from one of the rotatable loads to drive the other of the rotatable loads, or the reverse.

Differential geared turbine engine with torque modulation capability

An aircraft propulsion system (10) or a fixed wing aircraft (12) having a power plant or gas turbine engine (18) driving a number of outboard propulsion units (20) mounting to pylons (24) extending laterally outwardly from the fuselage (14) of the aircraft and propelling the fixed wing aircraft (12) via mechanical transmission (28). The propulsion units (20) are powered by the gas turbine engine (18) independently from one another to permit selective shutdown of at least one of the propulsion units (20) while still allowing the remaining propulsion units (20) to be driven by the engine (18). The mechanical transmission (28) is a multibranch transmission wherein an overload decoupling device (48) is provided in each transmission shaft branch (30) set to automatically disconnect an associated propulsion unit (20) when a predetermined critical value is reached. Both the propulsion units (20) and the gas turbine engine (18) having lubrication systems (50, 54) to lubricate transmission components and the decoupling devices (48).

Aircraft propulsion system

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Differential geared turbine engine with torque modulation capability

Aircraft propulsion system