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 (F) 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 project, said ring support structure including a shroud from which radial flanges project, by which said latching tabs of each ring sector are retained; a stator located, relative to said flow direction (F) 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 (E) being defined between the ring , the support structure and the platform , this annular space (E) 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 (E) 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 (E), 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 (F) 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 project, said ring support structure including a shroud from which radial flanges project, by which said latching tabs of each ring sector are retained; a stator located, relative to said flow direction (F) 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 (E) being defined between the ring , the support structure and the platform , this annular space (E) 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 (E) 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 (E), between said turbine ring and the platform . <EOS>