Bladed turbomachine assembly including means for limiting vibrations between platforms

A bladed turbomachine assembly extending about a main axis and including at least two circumferentially adjacent blades,

• each blade comprising an airfoil extending according to a direction of radial extension with respect to said main axis and a platform located at a free radial end of the airfoil,
• wherein the platform of each blade of the bladed assembly is located circumferentially facing a platform of the other circumferentially adjacent blade of the bladed assembly,
• wherein the bladed assembly includes an insert arranged circumferentially between the platforms and which cooperates with the platforms,
• wherein each platform includes a circumferential bearing face against which a circumferential end of the insert is in contact, and the direction of the contact between each circumferential bearing face and the insert is oriented circumferentially with respect to the main axis, and
• wherein said bladed turbomachine assembly comprises means for axial retention of the insert between the two platforms that comprise at least one finger carried by the insert which protrudes circumferentially from the insert and which is received in an associated notch formed circumferentially in recess in at least one of the platforms, said at least one finger and the associated notch are designed to allow a relative movement of the insert with respect to the platforms according to the radial direction.