A sensor system includes a rotor antenna, a radio frequency (RF) sensor, a stator antenna, and one or more processors. The rotor antenna and the RF sensor are configured to be disposed on a shaft of a rotor assembly and are conductively connected to each other. The RF sensor generates measurement signals. The stator antenna is mounted to a stator member of the rotor assembly and positioned radially outward from the rotor antenna. The stator antenna is wirelessly connected to the rotor antenna across an air gap. The one or more processors are communicatively connected to the stator antenna and are configured to monitor one or more electrical characteristics of the measurement signals that are received by the stator antenna from the rotor antenna over time as the shaft rotates and to determine rotational speed of the shaft based on recurrent variations in the one or more electrical characteristics.

A pitch actuation system for a turbomachine propeller, comprising an actuator with a movable portion configured to be connected to blades of the propeller in order to rotate them relative to the blade-pitch setting axes, wherein the actuator is an electromechanical actuator and comprises: blade-pitch control having a transmission screw rotated about an axis; a nut through which the transmission screw passes; and a member configured to engage with the blades in order to move the blades, wherein the nut is connected to the member via a decoupler configured such that a translational movement of the nut causes a translational movement of the member, but rotational movement of the member does not cause rotational movement of the nut.

An aircraft turboprop engine has at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the means for supplying air has at least one compressor of which the rotor is coupled to the low-pressure body. The compressor has an air inlet connected to means for bleeding air from an air inlet duct of the turboprop engine.

An apparatus and method for mounting a turbine engine to an aircraft can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section.

A gas turbine engine comprises a gearbox including a first epicyclic gearbox and a second epicyclic gearbox. The first epicyclic gearbox comprises a first sun gear meshing with the first planet gears and the first planet gears meshing with a first annulus gear. The second epicyclic gearbox comprises a second sun gear meshing with the second planet gears and the second planet gears meshing with a second annulus gear. An input shaft is arranged to drive the first sun gear and a first planet gear carrier is arranged to drive a propulsor. The first and second annulus gears are fixed to a static structure. A first clutch is arranged between the first planet gear carrier and the second planet gear carrier and a second clutch is arranged between the second sun gear and the input shaft. The gearbox is more efficient at cruise conditions.

A method and a turbine rotor system for reducing over-speed potential of a turbine of a gas turbine engine involve mechanically connecting the turbine to at least two mechanical loads via first and second mechanical drives extending in opposite directions from the turbine.

A gas turbine engine includes an engine spool with a turbine section, a propeller, a motor, and a variable drive arrangement. The variable drive arrangement mechanically couples the engine spool to the propeller, and includes a first gear connection rotationally coupled to the propeller, a second gear connection rotationally coupled to the engine spool, and a sprag clutch rotationally coupled to the first gear connection. The sprag clutch is configured to passively decouple the motor from the first gear connection when a torque input from the engine spool exceeds a torque input from the motor, and is configured to passively couple the motor to the first gear connection when the torque input from motor exceeds a torque input from the engine spool.

An aircraft intake duct for channeling a flow of ambient air toward an annular engine compressor inlet of a gas turbine engine having a compressor reference axis and a reference plane that extends from such compressor reference axis. The aircraft intake duct includes an oblong air intake inlet for receiving the flow of ambient air, the air intake inlet being offset radially outwardly relative to the compressor reference axis and located on a first side of the reference plane. Two distal intake channels fluidly link distal extremities of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a second side of the reference plane. A central channel fluidly links a central section of the oblong air intake inlet to a segment of the annular engine compressor inlet located on a first side of the reference plane. The distal channels are blended together by the central channel so that a single intake duct is formed.

An unducted thrust producing system, includes a rotating element, a stationary element. An inlet may be located forward or aft of the rotating element and the stationary element. An exhaust may be located forward, aft, or between the rotating element and the stationary element.

A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.