Patent attributes
A turbine engine turbine ring, in particular for a helicopter, in which vibratory behavior is reduced. The turbine ring includes an essentially cylindrical support, and one or more sectors forming a circle configured to define a segment of an air passage, each sector being fastened to the support by an attachment device, wherein the attachment device includes a hook portion belonging to the support and projecting towards the sector, and a hook portion belonging to the sector and projecting towards the support, the hook portions of the support and of the sector being configured to co-operate in order to fasten the sector to the support, the ring further includes a damper device provided within the attachment device and stressed radially between a portion of the sector and a portion of the support so as to damp relative movements between the sector and the support.
