Abstract: The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23) connected to the platform (13), a leading edge (21) and a trailing edge (22), a groove formed in the platform (13) around part of the root (23) of each blade (20) in an area adjacent to the leading edge (21) and/or the trailing edge (22), and a joint (30) placed in the groove (15) in such a way that it extends in the extension of the radially outer face (14) of the platform (13) in order to ensure a continuity of the inner flow stream.

Abstract: A system for changing the pitch of blades of at least one turbomachine rotor is provided. The system generally includes a control means acting on a connecting mechanism connected to the blades of the rotor and having a body mobile in translation along a longitudinal axis with respect to a fixed body, load-transfer bearing mounted on the mobile body cooperating with the connecting mechanism, and means for lubricating the bearing having a lubricant duct and extending radially above the fixed and mobile bodies. The duct generally includes first and second telescopic tubular parts that slide coaxially with respect to one another, the first part connected to the fixed body and the second part connected to the mobile body, and means for spraying lubricant into the bearing mounted on the mobile body and lubricant supply conduit mounted on the mobile body to connect the duct to the spraying means.

Abstract: The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23) connected to the platform (13), a leading edge (21) and a trailing edge (22), a groove formed in the platform (13) around part of the root (23) of each blade (20) in an area adjacent to the leading edge (21) and/or the trailing edge (22), and a joint (30) placed in the groove (15) in such a way that it extends in the extension of the radially outer face (14) of the platform (13) in order to ensure a continuity of the inner flow stream.

Abstract: A system for changing the pitch of blades of at least one turbomachine rotor is provided. The system generally includes a control means acting on a connecting mechanism connected to the blades of the rotor and having a body mobile in translation along a longitudinal axis with respect to a fixed body, load-transfer bearing mounted on the mobile body cooperating with the connecting mechanism, and means for lubricating the bearing having a lubricant duct and extending radially above the fixed and mobile bodies. The duct generally includes first and second telescopic tubular parts that slide coaxially with respect to one another, the first part connected to the fixed body and the second part connected to the mobile body, and means for spraying lubricant into the bearing mounted on the mobile body and lubricant supply conduit mounted on the mobile body to connect the duct to the spraying means.

Abstract: The invention relates to a propeller ring (10) of a turbomachine (1), with variable-pitch blades (P), the propeller ring (10) comprising a substantially coaxial annular body (11) with a main axis (A) and a plurality of radial housings (12) uniformly distributed around the main axis (A), each radial housing (12) being designed to receive a bearing (13) for a root (14) of a blade (P) so as to allow the variable pitch of the blade (P), the radial housings (12) having a substantially ovoid cross-section in a plane (T) tangential to the annular body (11).

Abstract: The invention relates to a hub for an unducted propeller (14) having variable-pitch blades (18) of a turbine engine, comprising two parallel annular side walls (34) between which are arranged rings (36) which are distributed angularly in a regular manner around a longitudinal axis (A) of the hub, which are connected to the annular side walls (34), and which comprise compartments (26) receiving bearings (32) having radial axes (R) for guiding in rotation roots (30) of blades of said propeller, said rings (36) being connected in pairs by connection means (40) which are arranged between the annular side walls (34) and which comprise substantially radial reinforcing partitions (42, 44, 46), characterised in that at least some of said reinforcing partitions (42, 44, 46) are connected to said annular side walls (34).

Abstract: A propeller ring of a turbomachine including an annular body substantially coaxial to a principal axis and a plurality of radial housings uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade, the annular body being made of composite material including a fibrous reinforcement densified by a polymer matrix and further including a plurality of metallic inserts configured to each receive the root of a blade, said metallic inserts being anchored in the composite material of the annular body.

Abstract: The invention relates to a propeller ring (10) of a turbomachine (1), with variable-pitch blades (P), the propeller ring (10) comprising a substantially coaxial annular body (11) with a main axis (A) and a plurality of radial housings (12) uniformly distributed around the main axis (A), each radial housing (12) being designed to receive a bearing (13) for a root (14) of a blade (P) so as to allow the variable pitch of the blade (P), the radial housings (12) having a substantially ovoid cross-section in a plane (T) tangential to the annular body (11).

Abstract: The invention relates to a hub for an unducted propeller (14) having variable-pitch blades (18) of a turbine engine, comprising two parallel annular side walls (34) between which are arranged rings (36) which are distributed angularly in a regular manner around a longitudinal axis (A) of the hub, which are connected to the annular side walls (34), and which comprise compartments (26) receiving bearings (32) having radial axes (R) for guiding in rotation roots (30) of blades of said propeller, said rings (36) being connected in pairs by connection means (40) which are arranged between the annular side walls (34) and which comprise substantially radial reinforcing partitions (42, 44, 46), characterised in that at least some of said reinforcing partitions (42, 44, 46) are connected to said annular side walls (34).

Abstract: A propeller ring of a turbomachine including an annular body substantially coaxial to a principal axis and a plurality of radial housings uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade, the annular body being made of composite material including a fibrous reinforcement densified by a polymer matrix and further including a plurality of metallic inserts configured to each receive the root of a blade, said metallic inserts being anchored in the composite material of the annular body.