Patent ID: 8425184

Claim:
A turbine shroud ring sector for a turbomachine supported at an upstream end by a downstream support of a turbine casing with circular sliding, comprising a stop able to collaborate with a second stop borne by an element of said turbomachine adjacent to said shroud ring in order to immobilize said shroud ring circularly, said turbine shroud ring sector comprising; on an end facing said element, a recess able to allow said second stop to pass to come into contact with said first stop, said recess including first and second sides extending into said ring sector and a third side at a bottom of the recess connecting the first and second sides, the bottom of the recess having corners between the first and third sides and second and third sides that are rounded in a circular arc of radius r, wherein the third side at the bottom of the recess has a convex shape tangential to the circular arcs of the rounded corners and with a curvature that evolves between a radius of curvature r at a first point where the bottom of the recess connects with one of the rounded corners and a radius of R, greater than the radius r, at a second point situated between the two rounded corners.