A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.

A coolant pump for an internal combustion engine (ICE) in a vehicle with a central engine control, having a pump shaft that drives an impeller for pumping a coolant. An axial piston pump operated via a wobble plate on a rear face of the impeller, conducts part of the pumped coolant away to a hydraulic circuit that extends from the axial piston pump via a proportional valve back to the pumped coolant and has a branch-off between the axial piston pump and the proportional valve as the hydraulic actuator. A regulating slide valve adjusts coolant volume flow of depending on pressure in the hydraulic circuit. A sensor detects a parameter characteristic of the coolant volume flow and outputs an actual value signal. A dedicated pump control controls the proportional valve based on the actual value signal of the sensor and a desired value signal of the central engine control.

An actuator includes a housing that defines a first inlet to receive a fluid, a second inlet to receive the fluid and a chamber. The actuator includes an actuator rod movably coupled to the housing. The actuator rod includes a head. A first face of the head is responsive to the fluid from the first inlet, and a second face of the head is responsive to the fluid from the second inlet to move the actuator rod. The head defines at least one cross-bore. The actuator includes at least one plug coupled to the cross-bore to inhibit a flow of the fluid through the cross-bore in a first state such that the plug fluidly isolates the fluid from the first inlet from the fluid from the second inlet. The plug is to enable the flow of the fluid through the at least one plug in a second state.

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.

A fan module including variable-pitch blades, a fan rotor bearing the blades of the fan, each mounted to pivot about a pitch axis; a fan shaft extending along a longitudinal axis X inside the fan rotor and driving the fan rotor in rotation. A power shaft drives the fan shaft with a planetary gear speed reducer At least a first and a second bearing guide the rotation of the fan rotor, housed inside a lubrication chamber. A system varies the pitch of the fan blades, including a connecting mechanism connected to the blades of the fan and a controller acting on the connecting mechanism. The first bearing is disposed upstream of the speed reducer and the second bearing is disposed downstream of the speed reducer. The fan rotor is connected to the fan shaft by an annular trunnion extending at least along an upstream portion of the lubrication chamber.

The present disclosure relates to a hydraulic control system for a thrust reverser of an aircraft turbofan nacelle. The hydraulic control system includes devices for actuating and controlling the reverser having hydraulic locks and cylinders, the corresponding hydraulic solenoid valves, and sensors. The turbofan includes a full-authority electronic computer or aircraft having an avionics computer that gives reverse thrust commands. The system further includes an electronic concentration module, different from the computer, which concentrates the data relating to the operation of the reverser actuation and control devices. The module includes internal contact switches for controlling the solenoid valves, a device for monitoring the sensors, a device for analog or digital processing of the data, and a bus for communication with the computer.

A hybrid-driven dual pump for conveying a coolant for a combustion engine, is proposed. The dual pump comprises: a first pump assembly with a first pump impeller, a first spiral housing and a first pump shaft driven via a mechanical drive connection by a combustion engine; a second pump assembly with a second pump impeller, a second spiral housing, a second pump shaft and an electric drive; a joint pump housing enclosing the first pump assembly and the second pump assembly with a joint pump inlet and a joint pump outlet; and a flap arranged freely pivotably between an outlet of the first spiral housing and an outlet of the second spiral housing such that a direct flow connection between the first spiral housing and the second spiral housing is blocked.

A turbine engine including: a rotor having at least one variable-pitch blade which is guided to rotate on bearings relative to a fixed structure; a system for controlling the pitch of the at least one blade, the control system being rigidly secured to the rotor and including a first actuator driven by energy, and the control system further being disposed axially upstream of the bearings; a device for transferring the energy, which is disposed axially between the bearings, the transfer device including a stationary element and a mobile element; wherein the rotor is annular and delimits an inner space which is open towards the upstream side and inside of which the control system is disposed.

A system for modulating airflow into a bore defined by a rotor of a gas turbine engine defining an axial direction, a circumferential direction, and a radial direction is provided. The system includes a movable member positioned forward of a first stage of rotor blades of the rotor. The movable member is movable between at least a first position and a second position to modulate airflow into the bore via a plurality of opening in fluid communication with the bore.

Locking actuators for thrust reverser actuation systems, engines and aircraft including the same, and associated methods. A locking actuator includes an actuator housing, an extension element, and a lock assembly. The extension element is configured to translate along an actuator axis to transition between a retracted state and an extended state. The lock assembly transitions between a locked state and an unlocked state independent of transitioning the extension element between the retracted and extended states. In examples, a thrust reverser actuation system includes an actuator assembly with the locking actuator and a hydraulic control assembly. In examples, an engine includes a thrust generator, a nacelle, a transcowl, and the thrust reverser actuation system. In examples, a method of operating a thrust reverser actuation system includes transitioning a lock assembly from a locked state to an unlocked state and transitioning an extension element from a retracted state to an extended state.