A gas turbine engine according to an example of the present disclosure includes, among other things, a fan including a plurality of fan blades rotatable about an engine axis. Each of the fan blades have a leading edge and rotate about a fan blade axis. A method of operating a gas turbine engine is also disclosed.

Methods and apparatus to reduce deflection of an airfoil are disclosed. An example apparatus disclosed herein includes a plate including an aperture, the airfoil disposed in the aperture, and a damper operatively coupled between the plate and a hub of the airfoil, the damper to transform flexural deflection of the airfoil to radial deflection of the plate.

The invention relates to a turbomachine module (1), comprising: —a rotating housing (7-8) supporting a propeller provided with a plurality of blades (5), —a system for varying the pitch of the propeller blades (5), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (7-8), in that the control means comprise an annular row of rotary actuators (16), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring (11) that is driven to rotate by rotary output shafts (17) of the actuators (16), the synchronisation ring (11) being guided in rotation relative to the rotary housing (7-8) by guide means and meshed by a first toothing (13) with pinions (14) of the blades (5).

A propulsion system includes a drive shaft movable about an axis of rotation, a fan, a fan shaft that drives the fan, and a reduction device coupling the drive shaft and the fan shaft. The reduction device has first and second reduction stages and includes a sun gear, centered on the axis and driven by the drive shaft, a ring gear that is coaxial with the sun gear and that drives the fan shaft about the axis, and planet gears distributed circumferentially about the axis between the sun gear and the ring gear. Each planet gear includes a first portion meshed with the sun gear and a second portion meshed with the ring gear. A diameter of the first portion is different from a diameter of the second portion, and the first portion of the planet gears extend between the second portion of the planet gears and the fan.

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.

A blade pivot of adjustable orientation for a turbomachine fan hub includes: a block having a retaining device configured to retain a fan blade root and a coupling device for the transmission of a torque; a ball type rolling bearing for taking up centrifugal forces having an inner ring; a clamping nut screwed onto an external thread of the block in order to clamp the inner ring of the ball type rolling bearing for taking up centrifugal forces to the block; a rolling bearing for taking up transverse forces; a pitch setting transmission ring positioned inside the inner radial end of the block and equipped with a coupling device cooperating with the coupling device of the block, and a device for locking the pitch setting transmission ring on the block.

A method is provided that includes providing a first turbine engine and providing a second turbine engine. The first turbine engine is configured with a first thrust rating. The first turbine engine includes a first engine rotating assembly and a first engine case structure housing at least the first engine rotating assembly. The second turbine engine is configured with a second thrust rating that is different than the first thrust rating. The second turbine engine includes a second engine rotating assembly and a second engine case structure housing at least the second engine rotating assembly. The first engine case structure and the second engine case structure have at least substantially common configurations. The first turbine engine and the second turbine engine are provided by a common entity.

A gas turbine engine includes a core turbine engine and a fan mechanically coupled to the core turbine engine. The fan includes a plurality of fan blades, each fan blade defining a base and an inner end along a radial direction of the gas turbine engine. The fan also includes a hub covering the base of each of the plurality of fan blades. Further, the fan includes one or more bearings for supporting rotation of the plurality of fan blades. The one or more bearings define a fan bearing radius along a radial direction of the gas turbine engine. Similarly, the hub defines a hub radius along the radial direction of the gas turbine engine. The ratio of the hub radius to the fan bearing radius is less than about three, providing for desired packaging of the various components within the fan of the gas turbine engine.

Method for controlling a first, a second and a third variable of a turbomachine as a function of a first, a second and a third control quantity of a turbomachine which can each be saturated as a function of the operating parameters of the turbomachine.

The method comprises a first multivariable correction (120) delivering a first value for the three control quantities, a selection (130) of the first control quantity to be delivered as a function of a minimum value, of a maximum value and of the value determined by the first correction, a second multivariable correction (140) delivering a second value for the second and third control quantities, and a selection (150) of the values of the second and third control quantities to be delivered in the values determined during the first correction and those determined during the second correction.

The invention relates to a vane (7) comprising: a structure made of composite material, a vane (7) root (16) attachment (9) comprising a base having a radial outer face (20) and in which a slot (24) configured to receive the vane (7) root (16) is formed and two platforms (26), extending on either side of the blade (18) opposite the radial outer face (20), and two stiffening parts (30), added and fixed on the radial outer face (20) on either side of the stilt (17) so as to tightly abut against the stilt (17).