An aircraft includes a fuselage and an engine housed in the fuselage. A ram-air engine inlet is formed on an exterior of the fuselage. The ram-air engine inlet is defined, at least in part, by a cowling door. The cowling door is moveable between a closed position and an open position. An intake duct fluidly couples the ram-air engine inlet to the engine. A filter is disposed across the intake duct. A bypass duct is formed in the ram-air engine inlet aft of the intake duct. The bypass duct is operable to be selectively opened and closed.

A control system for a gas turbine engine including a power turbine is disclosed. The control system may include a control module to receive engine operating goals and an estimated current engine state, wherein the estimated current engine state is produced by a model-based estimation module using a bandwidth signal produced by an adaptation logic module. The control module is operative to determine fuel flow, inlet guide vane schedules and stability bleed schedules based at least in part on the received engine operating goals and the estimated current engine state, and to send signals to a gas generator of the gas turbine engine in order to control the gas generator according to the determined fuel flow, inlet guide vane schedules and stability bleed schedules.

An aircraft windshield wiper system includes a wiper arm, a wiper blade coupled to a first end of the wiper arm, and an output shaft coupled to a second end of the wiper arm. The wiper blade includes a fluid dispensing system including nozzles, a fluid control unit, fluid lines, fluid source, and a user interface. The wiper blade with the fluid dispensing system is configured to dispense a variety of fluids directly from the wiper blade onto the windshield of an aircraft.

A method for generating electric power for a rocket system includes burning a primary solid propellant grain to create a primary high pressure gas for providing thrust to the rocket, opening a first valve to divert a portion of the high pressure gas to an auxiliary solid propellant grain for igniting the auxiliary solid propellant grain, wherein the auxiliary solid propellant grain is disposed in a housing separate from the primary solid propellant grain, and burning the auxiliary solid propellant grain to create an auxiliary high pressure gas for turning a turbine. The method further includes driving a generator with the turbine and generating an electric power with the generator.

There is proposed a method for controlling a bistable shutoff vale for an aircraft engine, involving the steps of: emitting a closure signal on one of the control channels—emitting an open signal on the other control channel, the method being characterized in that—the amplitude of the close signal is designed to cause the vane to move into a first position constantly in a given period of time,—in the same period, the amplitude of the open signal fluctuates between a value designed to urge the valve toward a second position and a rest value, the actuating values of the two signals being adapted to one another in order to keep the vane immobile when the two signals received by the valve simultaneously adopt said actuation values.

An actuation system is provided for varying the pitch of the blades of a variable pitch fan or propeller. The actuation system includes a first actuator and a second actuator. The actuation system further includes a first linkage which operably connects the first actuator to the blades such that operation of the first actuator varies the pitch of the blades via the first linkage. The actuation system further includes a second linkage which operably connects the second actuator to the first actuator such that operation of the second actuator varies the pitch of the blades by series connection of the second linkage to the first linkage.

A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

Embodiments of a gas turbine engine actuation system are provided, as are embodiments of a high temperature actuator and methods for the manufacture thereof. In one embodiment, the gas turbine engine actuation system includes an actuated gas turbine engine component and a high temperature actuator, which has a rotor mechanically linked to the actuated gas turbine engine component and a stator surrounding at least a portion of the rotor. The stator includes, in turn, a coil support structure having a plurality of spokes extending radially therefrom. A plurality of pre-formed electromagnetic coils is circumferentially distributed about the coil support structure. Each of the plurality of pre-formed electromagnetic coils is inserted over at least one of the plurality of spokes in a radial direction. The stator further includes an inorganic dielectric material in which each of the plurality of pre-formed electromagnetic coils is at least partially embedded.

An actuator system for actuating a movable structure of a thrust reverser, the system including a first motor, a first actuator driven by the first motor, a second actuator, and a first transmission shaft that is connected to the second actuator and to the first motor so that the second actuator is driven by the first motor, a second motor, a third actuator driven by the second motor, a fourth actuator, and a second transmission shaft that is connected to the fourth actuator and to the second motor so that the fourth actuator is driven by the second motor, and control means for controlling the motors to cause the first actuator, the second actuator, the third actuator, and the fourth actuator to be driven synchronously by the two motors. The invention also relates to a thrust reverser and to a jet engine fitted with such an actuator system.

A turbine engine including: a rotor supporting a blade and guided by means of bearings; a control system for controlling the blade, which is solidly connected to the rotor and which includes an actuator driven by energy, the control system being disposed axially upstream of the bearings; and a device for transferring the energy, disposed axially between the bearings and including a stationary member and a moving member. The rotor includes a support ring supporting the blade and a shaft having a frustoconical portion and a cylindrical portion on which the bearings and the moving member are mounted, the frustoconical portion extending about the cylindrical portion.