The present disclosure provides a blade positioning and support system for a gas turbine engine including a blade, the blade having a root and a tip, with the root having a surface oriented away from the tip, the surface having a forward end and an aft end, the forward end projecting farther away from the tip than the aft end. Further, the present disclosure provides a blade receiver, the blade receiver having a face and a facet, with the face being oriented away from the facet, the face having a forward end and an aft end, the aft end projecting farther away from the facet than the forward end.

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.

In some embodiments, a rotorcraft includes a fuselage, a tailboom, a drive system and a variable thrust cross-flow fan system. The cross-flow fan system includes a cross-flow fan assembly that is mechanically coupled to a drive shaft and operable to rotate with the drive shaft about a longitudinal axis. The cross-flow fan assembly includes first and second driver plates having a plurality of blades rotatably mounted therebetween. The blades are disposed radially outwardly from the longitudinal axis and have a generally circular path of travel when the cross-flow fan assembly rotates about the longitudinal axis. The blades are moveable between a plurality of pitch angle configurations. A control assembly is coupled to the blades. The control assembly is operable to change the pitch angle configuration of the blades to generate variable thrust at a substantially constant rotational speed of the cross-flow fan assembly.

A system for controlling a variable orientation vane of a turbomachine compressor, for example a low-pressure compressor of a turbojet engine. Such a vane is also known as a variable stator vane. The system comprises a support, an orientable vane that is movable in rotation relative to the support and that comprises a lever for controlling the orientation of the orientable vane (26), and a magnetic field source that defines an air gap with the lever. When the source is powered electrically, it forms an electromagnet attracting the lever by induction such that the orientable vane changes orientation.

Pre-assembled blade (20) for fans (10) for cooling the coolant contained inside the radiator (1) of operating machines and/or vehicles, comprising a blade body (20a) rigidly connected to an axial shank (21), a part of which situated radially on the outside of the blade body is in the form of a cylindrical pin (21b); wherein the shank (21) has a part axially on the outside of the blade body in the form of a cylindrical pin (21b), holes (21c) with internal female threading being formed inside the pin (21b); and in that the blade (20) comprisesa blade flange (22) comprising. a hollow cylindrical body (22a), the opposite end bases of which comprise respectively: a flat edge (22b) provided with through-holes (22c). an inset annular seat (22d); a disk (23) provided with through-holes (23a) and an eccentric recess (23d) for stably containing with friction a pin (24) which is also eccentric, for rotationally actuating the blade about its axis;screws (25) designed to pass through the through-holes (23a) in the disk (23) and mate with the female thread of the holes (21c) in the pin (21b) in order to fix relative to each other the disk (23), flange (22) and pin (21b), thus ensuring a definite angular alignment of the blade relative to the pin (24) during pre-assembly.

A system includes a linear-displacement fluidic actuator coaxial with the propeller, and a transmission device connecting the actuator to the blades that are to be controlled. The transmission device includes at least two radial arms arranged symmetrically with respect to the actuator and connected, on the inside, to a translationally mobile part of the actuator and, on the outside, to a translationally movable rotary transmission ring which is connected to the pivot pins of the blades by intermediate connecting mechanisms that convert the translational movement of the rotary ring brought about by the actuator into a rotation of the blades of the propeller.

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 fan of a turbine engine, the fan including a fan disk provided with blades on its periphery, the blades being pivotally mounted on the disk around a pivoting axis and having a center of gravity, and a pitch change mechanism for the blades, each blade being configured so that its center of gravity is positioned on or at a small distance from a fictitious plane which passes through the pivoting axis of the blade and which is perpendicular to the axis of revolution of the fan when the blade is in a minimum drag position.

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.