A rotary machine satisfies at least one of Dr1<Dh1Dr2 or Dc1Dt1>Dc2. Dr1, Dh1, Dr2, Dc1, Dt1, and Dc2 are distances from a rotational center axis of a hub to an upstream end of a first blade-facing surface facing a hub-side end surface of a variable blade, an upstream end of the hub-side end surface when the blade angle is maximum, a downstream end of a first outer peripheral surface adjacent to an upstream side of the blade-facing surface, an upstream end of a second blade-facing surface facing a tip-side end surface of the variable blade, an upstream end of the tip-side end surface when the blade angle is minimum, and a downstream end of a first inner peripheral surface adjacent to an upstream side of the second blade-facing surface, respectively.

Conventional gas turbine engines are generally optimized to operate at nearly a fixed speed with fixed blade geometries for the design operating condition. When the operating condition of the engine changes, the flow incidence angles may not be optimum with the blade geometries resulting in reduced off-design performance. By contrast, according to embodiments of the present invention, articulating the pitch angle of turbine blades in coordination with adjustable nozzle vanes improves performance by maintaining flow incidence angles within the optimum range at all operating conditions of a gas turbine engine. Maintaining flow incidence angles within the optimum range can prevent the likelihood of flow separation in the blade passage and also reduce the thermal stresses developed due to aerothermal loads for variable speed gas turbine applications.

A variable vane mechanism for adjusting the angle of stator vanes in a gas turbine engine is provided. The mechanism includes a circumferentially extending unison ring that is driven circumferentially around a casing by an actuator. The unison ring is connected to the stator vanes via levers such that the angle of the vanes changes with circumferential movement of the unison ring. The unison ring and the casing are each provided with at least one rigging hole in order to set the initial angle of the vanes. At least one of the unison ring and the casing are each provided with at least two rigging holes, so that the initial angle of the vanes can be adjusted by selecting different combinations of rigging holes. This may allow accumulations in tolerances to be compensated for and/or may allow the engine to be tested at different initial vane angles.

A system for vane pitch actuation includes an electric motor with a rotary output shaft defining a drive axis. A worm shaft defines a drive axis, and is operatively connected to be driven in rotation about the drive axis by the rotary output shaft of the electric motor. A sync ring is defined about an engine axis that is orthogonal to the drive axis. The sync ring is configured to rotate about the engine axis over a range of positions for driving a plurality of variable pitch stator vanes to each have a pitch based on position of the sync ring. The sync ring includes a plurality of gear teeth for actuation of the sync ring by the electric motor.

Systems and methods are provided to control a rotor blade pitch. In one example, a system comprises a ratchet mechanism comprising a ratchet wheel configured to be rotated by a motor about a first axis. The ratchet mechanism comprises one or more followers each of which is coupled to the ratchet wheel. The ratchet wheel rotates the one or more followers in a first direction about the first axis when the ratchet wheel is rotated by the motor in the first direction about the first axis. One or more rotor blades rotate about the first axis. Each rotor blade is affixed to a respective follower. Each follower controls a pitch of the respective rotor blade based on a position of the follower relative to the ratchet wheel.

Module for mounting a turbomachine fan blade, including: a blade force take-up device, a blade support able to pivot about a radial axis and configured to be engaged axially inside the device, the support and the device being mutually configured to ensure a clamping of the support against the device and an axial retention of the support inside the device; the support and the device each including, on their respective surfaces in cooperation, an alternation of conical seats and recesses making it possible alternatively, on the one hand, when the recesses of one surface are in geometric correspondence with the seats of the other surface, to axially slide the support relative to the device, and on the other hand, when the seats of both surfaces are in geometric correspondence with each other, to prevent any axial sliding movement of the support relative to the device.

A compressor rotor for a turbomachine including a shaft and at least two disks mounted on the shaft to hold a single set of vanes that are rotatably mobile about the rotational axis of the shaft, at least one first disk being mounted in a mobile manner on the shaft to be able to generate an angular gap in relation to the second disk and to trigger a rotation of the vanes about the radial axis of same, at least one of the two disks being shaped to receive at least one mechanism for attaching the vanes, the connection between the disk and the attaching mechanism enabling a rotation of the attaching mechanism about a radial axis, and connection is a ball-jointed connection that is tangentially and axially mobile.

A method of transferring a fluid flow from a stationary member to an adjacent rotatable member and a fluid flow transfer system are provided. The system includes one or more fluid supply conduits and a gearbox flow path configured to channel the flow of fluid through the power gearbox. The system also includes a transfer sleeve device configured to receive the flow of fluid from the gearbox flow path. The transfer sleeve device includes a stationary transfer sleeve member and a rotatable transfer sleeve member. The transfer sleeve device is configured to transfer the flow of fluid between the stationary transfer sleeve member and the rotatable transfer sleeve member. A pitch change mechanism (PCM) actuator is configured to receive the flow of fluid through one or more of a plurality of flow ports wherein the plurality of flow ports direct the flow of fluid to a respective actuator.

A fan module for an aircraft turbine engine includes a fan having variable pitch blades and an oil transfer device configured to provide a transfer of oil between a stator and a rotor. The oil transfer device includes a stator ring having internal oil ducts, a shaft inserted into the ring and having internal oil ducts, and an annular support of the ring configured to deform elastically to allow movements of the ring in the radial direction. A plain bearing is located between the ring and the shaft, and roller bearings are mounted between the ring and the shaft on either side of the plain bearing.

A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbinethe compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.