A turbomachine turbine assembly extending around an axis and comprising: a plurality of ring sectors forming a turbine ring; a turbine ring support structure, each ring sector having, in a section plane defined by an axial direction (D A) and a radial direction (D R) of the turbine ring, said axial direction corresponding to the flow direction of a gas flow in said turbine, a portion forming a base with, in the radial direction (D R) of the turbine ring, a radially inner face defining the inner face of the turbine ring and a radially outer face from which latching tabs (52, 53) project, said ring support structure including a shroud from which radial flanges (61, 62) project, by which said latching tabs (52, 53) of each ring sector are retained; a stator located, relative to said flow direction of a gas flow in said turbine, downstream of said turbine ring and mounted via a hook at a mounting zone in a recess of the ring support structure, the stator including a vane provided with a radially outer platform, the platform extending axially facing said turbine ring; an annular space being defined between the ring, the support structure and the platform, this annular space being traversed, during the operation of said turbine, by a leakage air current originating in a space located radially outside the stator and which leaks while passing through the mounting zone, characterized by the fact that it includes a hollow ring which occupies said annular space and which is formed to collect said leakage air current, to channel it and to expel it in a radially inner region of said annular space, between said turbine ring and the platform. a plurality of ring sectors forming a turbine ring; a turbine ring support structure, each ring sector having, in a section plane defined by an axial direction (D A) and a radial direction (D R) of the turbine ring, said axial direction corresponding to the flow direction of a gas flow in said turbine, a portion forming a base with, in the radial direction (D R) of the turbine ring, a radially inner face defining the inner face of the turbine ring and a radially outer face from which latching tabs (52, 53) project, said ring support structure including a shroud from which radial flanges (61, 62) project, by which said latching tabs (52, 53) of each ring sector are retained; a stator located, relative to said flow direction of a gas flow in said turbine, downstream of said turbine ring and mounted via a hook at a mounting zone in a recess of the ring support structure, the stator including a vane provided with a radially outer platform, the platform extending axially facing said turbine ring; an annular space being defined between the ring, the support structure and the platform, this annular space being traversed, during the operation of said turbine, by a leakage air current originating in a space located radially outside the stator and which leaks while passing through the mounting zone, characterized by the fact that it includes a hollow ring which occupies said annular space and which is formed to collect said leakage air current, to channel it and to expel it in a radially inner region of said annular space, between said turbine ring and the platform.