Abstract: The invention relates to a device (12) for a non-streamlined propeller (6, 7) with blades (10) having variable pitch of a turbomachine (1), the device comprising a support (15) intended to support a blade (10) and including a cylindrical foot (17), a bearing comprising a radially internal annular section (20) and a radially external annular section (21) capable of pivoting with respect to each other, the foot (17) being mounted in said internal section (20) of the bearing. The device comprises a hub (27) mounted in the foot (17), said hub (27) including a rim (29) comprising a face (30) coming to bear on the radially internal annular section (20) of the bearing, the hub (27) and the foot (17) of the support (15) comprising complementary engagement elements (18, 28) interacting with a locking component (23).

Abstract: A hub for a propeller having variable-pitch blades for a turbomachine with longitudinal rotation axis, including a plurality of blade platforms, each one being designed to receive a blade root, the platforms being distributed around the annular outer periphery of the hub concentrically with the longitudinal rotation axis, wherein each blade platform has the general geometric shape of a spherical cap, and wherein, between two adjacent blade platforms around the longitudinal rotation axis, the transverse dimension, in particular the diameter, of the hub can vary axially and radially.

Abstract: A pivot for an adjustable-pitch blade for a turbine engine fan hub, the pivot including a stud having coupling device for transmitting a twisting torque and an outside thread, a force-decoupling part positioned around the stud, provided with an outside thread, pressing transversely against the stud at its radially outer end, an outer rolling bearing having an inside ring mounted to press transversely against the force-decoupling part, an inner rolling bearing assembled around the force-decoupling part and held thereby, a pitch transmission ring provided with a coupling device co-operating, with the coupling device of the stud, a first clamping nut screwed onto the outside thread of the force-decoupling part in order to clamp the outer and inner rolling bearings around the fan hub, and a second clamping nut screwed onto the outside thread of the stud in order to provide clamping between the stud, the force-decoupling part, and the pitch transmission ring.

Abstract: The invention relates to an intermediate case for a twin spool turbomachine for an aircraft, comprising at least one lubricant passage and piece (88a) associated with at least one of its vanes (24), comprising a lubricant passage (98a) extending along a passage axis (134a) and opening up into the lubricant duct (55a). The passage axis (134a) and the orifice axis (140a) are also at a spacing from each other along a circumferential direction (91), and a connection piece (125a) through which a connection conduit (142a) passes is firstly partially housed in the vane root (34) so as to create a communication between the connection duct (142a) and the lubricant passage orifice (124a), and secondly is partially housed in an end-piece support device (108a) or in the lubricant passage end-piece (88a), such that the connection conduit (142a) communicates with the lubricant passage (98a) in the end-piece.

Abstract: A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.

Abstract: The invention relates to an intermediate case (25) for a twin spool turbomachine for an aircraft, comprising a hub (26), an outer shell (23) and outlet guide vanes (24) installed at their ends on the hub and on the outer shell, and each of at least some of the outlet guide vanes (24) performing a heat exchanger function and comprising a lubricant passage (50a, 50b) designed to be cooled by the fan flow (58) following an outer surface of the outlet guide vane. According to the invention, the case also comprises at least one lubricant duct (55) passing along a circumferential direction of the hub (26) and at least part of which is made from a single casting with the hub, the lubricant duct (55) having at least one lateral opening communicating with the lubricant passage (50a, 50b) of at least one of the vanes (24).

Abstract: A control device of the pitch of blades of a rotor of a propeller is provided. The control device includes: a radial shaft; a pivot connected to the blade, the rotation of the radial shaft driving the rotation of the pivot for the modification of the pitch of the blade; an insert fixed rigidly to the pivot so as to block their relative displacement, the radial shaft being configured to drive in rotation the insert; at least one peg passing through the insert and the pivot for transmission of the rotation of the insert to the pivot; and a heat insulation element arranged between the insert and the pivot, whereof the thermal conductivity is less than the thermal conductivity of the pivot and of the radial shaft.

Abstract: The invention relates to a device (12) for a non-streamlined propeller (6, 7) with blades (10) having variable pitch of a turbomachine (1), the device comprising a support (15) intended to support a blade (10) and including a cylindrical foot (17), a bearing comprising a radially internal annular section (20) and a radially external annular section (21) capable of pivoting with respect to each other, the foot (17) being mounted in said internal section (20) of the bearing. The device comprises a hub (27) mounted in the foot (17), said hub (27) including a rim (29) comprising a face (30) coming to bear on the radially internal annular section (20) of the bearing, the hub (27) and the foot (17) of the support (15) comprising complementary engagement elements (18, 28) interacting with a locking component (23).