An exemplary continuous variable pitch rotor system includes a blade extending radially from a hub along a longitudinal axis, the blade rotationally coupled to the hub to permit limited rotation of the blade about the longitudinal axis in response to a change in a rotational speed of the hub. In some embodiments, the blade is held in a radially fixed position relative to the hub. In some embodiments, the blade is permitted to translate radially.

A variable pitch propeller is designed to adjust the pitch of the propeller blade during flight to maximize the propeller efficiency. The propeller blade may comprise airfoil cross-sections. Each cross-section may be composed of different materials at the leading edge and trailing edge. In various embodiments, these materials are selected and oriented to achieve the necessary elastic moduli of the leading and trailing edge for the airfoil cross-section. During liftoff, the airfoil at the blade tip possesses a high blade pitch (e.g. 20 degrees), thereby increasing the generated lift on the propeller blades. During flight or hover conditions when maximal lift is no longer required, the trailing edge of the airfoil displaces upward and reduces the blade pitch to minimize the drag forces on the blade tip.

A variable pitch propeller is designed to adjust the pitch of the propeller blade during flight to maximize the propeller efficiency. The propeller blade may comprise airfoil cross-sections. Each cross-section may be composed of different materials at the leading edge and trailing edge. In various embodiments, these materials are selected and oriented to achieve the necessary elastic moduli of the leading and trailing edge for the airfoil cross-section. During liftoff, the airfoil at the blade tip possesses a high blade pitch (e.g. 20 degrees), thereby increasing the generated lift on the propeller blades. During flight or hover conditions when maximal lift is no longer required, the trailing edge of the airfoil displaces upward and reduces the blade pitch to minimize the drag forces on the blade tip.

The method can include, while the airplane is on the ground: entering a disking mode including positioning the blades at a disking pitch including rotating each blade around the length, the disking pitch oriented parallel to the plane of rotation; maintaining the blades at the disking pitch; and exiting the disking mode when a disking mode exit condition is met, including rotating each blade around the length, away from the disking pitch.

An electronic control system (30) for a turbopropeller engine (12) having a gas turbine (20) and a propeller assembly (13) coupled to the gas turbine (20), controls propeller operation based on a pilot input request, via generation of a driving quantity (Ip) for an actuation assembly (29) designed to adjust a pitch angle (β) of propeller blades (2) of the propeller assembly (13). The control system (30) envisages: a propeller speed regulator (39), receiving at its input a propeller speed error (ep), indicative of a difference between a propeller speed measure (Nr) and a propeller speed demand (Nrref), and generating at its output, based on the propeller speed error (ep), a first control quantity (Outi); a propeller pitch regulator (42), receiving at its input a propeller pitch error (ep), indicative of a difference between a propeller pitch demand ( ) and a pitch position measure (β), and generating at its output, based on the propeller pitch error (ep), a first control quantity (Out2); and a priority selection stage (45), configured to implement a priority selection between the first and the second control quantities, for providing at the output the driving quantity (IP), based on the priority selection between the first and the second control quantities.

There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.

There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.

The present invention relates to a rotor assembly where associated electric motors are configured to rotate the rotor, control the collective pitch of the rotor/assembly, and/or control the cyclic pitch of the rotor/assembly, by varying the relative rotational angle between two or more of the associated electric motors.

The present invention relates to a rotor assembly where associated electric motors are configured to rotate the rotor, control the collective pitch of the rotor/assembly, and/or control the cyclic pitch of the rotor/assembly, by varying the relative rotational angle between two or more of the associated electric motors.

A fan assembly for a gas turbine engine includes a fan disk, a trunnion, a fan blade, and a counterweight assembly. The fan disk is configured to rotate about an axial centerline of the gas turbine engine when installed in the gas turbine engine. The trunnion is mounted to the fan disk and defines a slot extending through a portion of the trunnion. The fan blade defines a pitch axis and is rotatably attached to the fan disk about its pitch axis through the trunnion. The counterweight assembly includes a link arm extending to the trunnion and an engagement device mounted to the link arm that is disposed to move through the slot of the trunnion.