Abstract: Shim for a turbomachine blade, for covering the root of said blade, the shim comprising: two branches for covering the bearing surfaces of the blade root; a base interconnecting these branches; and at least one holder element located at one end of the shim and suitable for coming into contact with the blade root to retain the shim relative to the blade root, the shim further comprising, at its other end, at least one foolproofing element projecting from the base in the opposite direction to the branches. A turbomachine rotor assembly including such a shim.

Abstract: A fan blade assembly of a turbojet with fan and a fan blade damper is disclosed. The fan blade includes a root and a platform. The fan blade damper is suitable for being attached in a housing formed in the lower face of the platform. The housing includes an upstream side perpendicular to the root of the blade. The damper includes a front edge of which a first portion is parallel to the upstream side of the housing and of which a second portion is inclined relative to said upstream side. A fan blade damper and a method for calibrating the damper are also disclosed.

Abstract: A shim for a turbomachine blade is disclosed. The shim includes two branches which wrap around flanks of a blade root, and two tabs. Each of the tabs extend from one end of a respective one of the two branches. The tabs are folded towards each other and are interconnected in such a manner as to prevent them from unfolding. Advantageously, the shim includes a connection part which interconnects the tabs in such a manner as to prevent them from unfolding. The connection part is assembled to the tabs in such a manner as to allow the branches of the shim to spread apart. For example, the connection part can be suitable for stretching in the direction for spreading the branches apart.

Abstract: A shim for a turbomachine blade is disclosed. The shim includes two branches which wrap around flanks of a blade root, and two tabs. Each of the tabs extend from one end of a respective one of the two branches. The tabs are folded towards each other and are interconnected in such a manner as to prevent them from unfolding. Advantageously, the shim includes a connection part which interconnects the tabs in such a manner as to prevent them from unfolding. The connection part is assembled to the tabs in such a manner as to allow the branches of the shim to spread apart. For example, the connection part can be suitable for stretching in the direction for spreading the branches apart.

Abstract: A method of calibrating the mass of components intended to be mounted at the periphery of a rotor, the method consisting, for each of the components, in removing by machining a volume of material in a region of the component situated on one of its axes of inertia in order to bring the mass of the component to a predetermined value.

Abstract: The invention relates to a fan blade assembly of a turbojet with fan and a fan blade damper, the fan blade comprising a root and a platform, the fan blade damper being suitable for being attached in a housing formed in the lower face of the platform, said housing comprising an upstream side perpendicular to the root of the blade. The damper comprises a front edge of which a first portion is parallel to the upstream side of the housing and of which a second portion is inclined relative to said upstream side. The invention also relates to a fan blade damper and a method for calibrating said damper.

Abstract: Shim for a turbomachine blade, for covering the root of said blade, the shim comprising: two branches for covering the bearing surfaces of the blade root; a base interconnecting these branches; and at least one holder element located at one end of the shim and suitable for coming into contact with the blade root to retain the shim relative to the blade root, the shim further comprising, at its other end, at least one foolproofing element projecting from the base in the opposite direction to the branches. A turbomachine rotor assembly including such a shim.

Abstract: A device for damping vibration of a retention ring for axially retaining turbomachine fan blades, the blades being designed to be mounted via their roots on a rotary disk having an annular flange extending axially and provided with a plurality of radial crenellations for coming into contact with a plurality of complementary radial crenellations of a retention ring designed to be mounted around the disk flange, the device comprising an abutment element of elastomer material designed to be received axially between two adjacent crenellations of the flange and two adjacent complementary crenellations of the retention ring, and radially between the flange of the rotary disk and the retention ring, said abutment element presenting contact surfaces for coming into contact with the adjacent crenellations, with the retention ring, and with the flange of the rotary disk.

Abstract: A device for damping vibration of a retention ring for axially retaining turbomachine fan blades, the blades being designed to be mounted via their roots on a rotary disk having an annular flange extending axially and provided with a plurality of radial crenellations for coming into contact with a plurality of complementary radial crenellations of a retention ring designed to be mounted around the disk flange, the device comprising an abutment element of elastomer material designed to be received axially between two adjacent crenellations of the flange and two adjacent complementary crenellations of the retention ring, and radially between the flange of the rotary disk and the retention ring, said abutment element presenting contact surfaces for coming into contact with the adjacent crenellations, with the retention ring, and with the flange of the rotary disk.

Abstract: Method of calibrating the mass of components intended to be mounted at the periphery of a rotor A method of calibrating the mass of components intended to be mounted at the periphery of a rotor, the method consisting, for each of the components, in removing by machining a volume of material in a region of the component situated on one of its axes of inertia in order to bring the mass of the component to a predetermined value.

Abstract: A turbojet engine fan rotor including a rotor disk having a peripheral rim with a plurality of axially extending channels carrying a plurality of fan blades each having a blade root interengaging with the channels of the disk, and a mounting arrangement for securing the blades to the disk. The mounting arrangement includes an annular member having a plurality of radially extending teeth, a plurality of wedges each interposed between one of the blade roots and a corresponding one of the channels and including a radially extending boss provided at one end, and a plurality of radially extending protrusions from the disk. The plurality of teeth and the plurality of protrusions cooperate with one another to secure the annular member with the rotor disk.