Abstract: A turbine ring assembly extending around an axis, including a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure held by a turbine casing, each ring sector including a base from which an upstream tab and a downstream tab extend radially outward, spaced axially from one another, wherein the assembly also includes a cross-member mechanically connected to the ring support and including a first radial flange bearing against the upstream latching tabs of the ring sectors, and, for each ring sector, at least two transverse pins and a radial spring, each transverse pin passing through the upstream latching tab and the downstream latching tab of the ring sector and the ring support to hold the ring sector and the ring support secured to one another.

Abstract: A rotor blade for a rotor disk of a turbine of an aeronautical turbomachine includes, in a radial direction from inside to outside, a blade foot root, a support, a platform and a rotor vane, where the root is connected to the support by a neck. The neck has a curvilinear profile defining, in a section in a plane perpendicular to the radial direction, a curved shape. The neck section overlaps at least 75% of the section of the rotor vane, as a projection of the sections of the neck and of the rotor vane in a plane perpendicular to the radial direction, where the section of the rotor vane joins with the platform.

Abstract: The main object of the invention is a rotor blade (18) for a rotor disk of a turbine of an aeronautical turbomachine including, in a radial direction (23) from inside to outside, a blade foot root, a support, a platform and a rotor vane (30), where the root is connected to the support by a neck (40), characterised by the fact that the neck (40) has a curvilinear profile defining, in a section in a plane perpendicular to the radial direction (23), a curved shape, and in that the said neck section (40) thus overlaps at least 75% of the section of the rotor vane (30), as a projection of the sections of the neck (40) and of the rotor vane (30) in a plane perpendicular to the radial direction (23), where the section of the rotor vane (30) joins with the platform.