A method of operating a multi-engine aircraft having two or more gas turbine engines includes operating a first engine in a powered mode to provide motive power to the aircraft, and, in flight, operating a second engine in either a powered mode to provide motive power to the aircraft or in a standby mode to provide substantially no motive power to the aircraft. When operating the second engine in the powered mode, pressurized air is bled from a first bleed location of a compressor of the second engine. When operating the second engine in the standby mode, pressurized air is bled from a second bleed location of the compressor of the second engine and supplying the pressurized air to a bleed air system of the second engine. The second bleed location is downstream of the first bleed location within the compressor of the second engine.

An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly extending along the length of the wing and moveable between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the plurality of vertical thrust electric fans when in the vertical thrust position.

An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan driven by the power source; and a wing extending from the fuselage. The vertical thrust electric fan is positioned on or within the wing, the wing including a diffusion assembly movable between a first position and a second position and positioned at least partially downstream of the vertical thrust electric fan when in the second position, the diffusion assembly including a first member and a second member, the second member movable generally along the vertical direction relative to the first member such that the first member and second member together define at least in part an exhaust flowpath for the first vertical thrust electric fan when the diffusion assembly is in the second position.

An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust propulsor driven by the power source; and a wing extending from the fuselage, the vertical thrust propulsor positioned on or at least partially within the wing, the wing including a diffusion assembly, the diffusion assembly including at least one diffusion member fixed in position and located downstream of the vertical thrust propulsor for diffusing an airflow from the vertical thrust propulsor.

An aircraft defining a vertical direction and a transverse direction. The aircraft may include a fuselage, a wing extending from the fuselage, and a hybrid-electric propulsion system. The hybrid-electric propulsion system may include a power source, a plurality of vertical thrust electric fans arranged along the wing and driven by the power source, and a forward thrust propulsor. The power source may include a combustion engine and an electric generator. The combustion engine may also define a flowpath for exhausting combustion gases. The forward thrust propulsor may be selectively or permanently mechanically coupled to the combustion engine. The forward thrust propulsor may include a propulsor fan having a plurality of fan blades arranged outside of the flowpath of the combustion engine for exhausting combustion gases.

An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust electric fan oriented to generate thrust along a vertical direction and powered by the power source; and a wing extending from the fuselage and including the vertical thrust electric fan positioned at least partially therein. The wing includes a variable geometry assembly having partial wing assembly, the partial wing assembly including a frame and a first member, the partial wing assembly moveable generally along a longitudinal direction when the variable geometry assembly is moved between a forward thrust position and a vertical thrust position, the first member moveable relative to the frame to form an exhaust path for the vertical thrust electric fan.

An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly moveable generally along a horizontal direction between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering at least one vertical thrust electric fan of the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the at least one vertical thrust electric fan when in the vertical thrust position.

An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along the wing, the wing including one or more components being moveable to selectively expose the plurality of vertical thrust electric fans, the wing further including a diffusion assembly positioned downstream of at least one vertical thrust electric fan of the plurality of vertical thrust electric fans, the diffusion assembly defining a diffusion area ratio greater than 1:1 and less than about 2:1.

Aircraft autothrottle system, having a motor to impart rotational movement to a shaft extending from the motor. An actuator is connected to the shaft and to an attachment end of a throttle lever having a control end, opposite the attachment end. The actuator has bearings to apply thrust to a longitudinal surface of the shaft such that the actuator is translated longitudinally along the shaft surface in response to motor-imparted rotation of the shaft. The shaft surface being smoothly continuous and longitudinally unbroken along its elongation to allow the actuator to longitudinally slip along the shaft irrespective of any shaft rotation by the motor when the thrust force exceeds a linear force manually applied at the throttle lever. An electronic controller for the motor to move the throttle lever so the motor moves the actuator assembly along the shaft based on an engine parameter monitored by the controller.

A method of operating a gas turbine engine of a multi-engine aircraft is disclosed, where the gas turbine engine has an engine shaft mounted for rotation in a bearing of a bearing assembly. The method comprises limiting motive power supplied to the aircraft by the gas turbine engine by operating the gas turbine engine in a standby mode; and when the gas turbine engine is operating in the standby mode, using an oil piston integrated in the bearing supporting the engine shaft of the gas turbine engine to generate an axial preload force on the bearing.