The invention relates to a device comprising a fixed actuator for a control system for the orientation of fan blades of a turbomachine, comprising: at least one actuator body housed inside an annular casing of the turbomachine forming a bearing support, the annular casing being centred on a longitudinal axis of the turbomachine an inclined relative thereto, the actuator body having an internal volume in which a piston is able to slide, separating the internal volume into two chambers isolated from one another; and a plurality of actuator rods passing through the annular casing forming a bearing support and each having one end fixed to the piston and an opposite end intended to be connected to an internal ring of a movement transfer bearing in order to drive it in translation, the internal volume of the actuator body being closed downstream by a chamber bottom which forms a single part with the annular casing forming a bearing support.

Rotor assembly apparatus are disclosed. An example rotor assembly includes a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the rotor assembly. A first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts. Each of the second shafts to provide torque to a respective blade coupled to the rotor assembly.

Rotor assembly apparatus are disclosed. An example rotor assembly includes a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the rotor assembly; and a first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts, each of the second shafts to provide torque to a respective blade coupled to the rotor assembly.

The disclosed subject matter relates to a hydraulic and electrical interface ring for a turbine engine, characterized in that said ring comprises fluid transfer pipes which axially pass therethrough and having axial ends that form axial interlocking means, the supporting means of at least one electrical device, and at least one electrical linking connector of the device, said connector being configured to engage by axial interlocking with a complementary electrical connector of another part.

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 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 control system includes a power actuator coaxial with the axis of rotation of the propeller, and a transmission device connecting the power actuator to pivots, of the blades to be controlled, arranged substantially radially with respect to the axis of rotation. The actuator is a rotary jack whose mobile part rotates about the axis of rotation and is connected to the transmission device by a mobile mechanical connection which transforms the rotation imparted by the mobile part of the jack about the axis of rotation into a rotation of the blades about the axes of the pivots which are perpendicular to the axis of rotation.

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.

A method and system for controlling a pitch of blades of a fan assembly having a centerline axis of rotation is provided. The system includes a pitch change mechanism (PCM) including a hydraulic actuator positioned axisymmetric with respect to the fan assembly and configured to angularly displace the blades of the fan assembly between a first position and a second position. The PCM further includes a plurality of hydraulic fluid supply lines coupled in flow communication between the hydraulic actuator and a hydraulic fluid transfer sleeve, the hydraulic fluid transfer sleeve configured to transfer a flow of pressurized hydraulic fluid across a gap between a stationary member of the hydraulic fluid transfer sleeve and a rotatable member of the hydraulic fluid transfer sleeve.

A multi-stage centrifugal pump assembly allows for multiple fixed ratio pressure levels. The multiple pressure levels permit optimization of actuation loops without the need for pressure regulators, and can be used directly by the actuators.