A turbine ring assembly comprising a plurality of ring sectors forming a turbine ring and a ring support structure , each ring sector having, along a section plane defined by an axial direction (D A ) and a radial direction (D R ) of the turbine ring , a portion forming an annular base with, in the radial direction (D R ) of the turbine ring , an inner face defining the inner face of the turbine ring and an outer face from which a first and a second attachment tabs protrude, the ring support structure including a central shroud from which a first and a second radial clamps protrude between which the first and second attachment tabs of each ring sector are maintained, characterized in that it comprises a first annular flange and a second annular flange disposed upstream of the first annular flange with respect to the direction of an air flow (F) intended to pass through the turbine ring assembly , the first and second annular flanges having respectively a first free end and a second end opposite to the first end, the first end of the first flange bearing against the first attachment tab , the first end of the second annular flange being distant from the first end of the first annular flange in the axial direction (D A ), the second ends of the first and second annular flanges being removably fastened to the first radial clamp of the central shroud of the ring support structure , and the second end of the first flange and the second end of the second flange being separated by a contact abutment , the first flange having a thickness in the axial direction (D A ) smaller than the thickness in the axial direction (D A ) of the second flange the second radial clamp of the ring support structure has a first free end and a second end secured to the central shroud of the ring support structure , the first end of the second radial clamp being in contact with the second attachment tab of the turbine ring and having a thickness in the axial direction (D A ) greater than the thickness of the first end of the first annular flange . characterized in that it comprises a first annular flange and a second annular flange disposed upstream of the first annular flange with respect to the direction of an air flow (F) intended to pass through the turbine ring assembly , the first and second annular flanges having respectively a first free end and a second end opposite to the first end, the first end of the first flange bearing against the first attachment tab , the first end of the second annular flange being distant from the first end of the first annular flange in the axial direction (D A ), the second ends of the first and second annular flanges being removably fastened to the first radial clamp of the central shroud of the ring support structure , and the second end of the first flange and the second end of the second flange being separated by a contact abutment , the first flange having a thickness in the axial direction (D A ) smaller than the thickness in the axial direction (D A ) of the second flange the second radial clamp of the ring support structure has a first free end and a second end secured to the central shroud of the ring support structure , the first end of the second radial clamp being in contact with the second attachment tab of the turbine ring and having a thickness in the axial direction (D A ) greater than the thickness of the first end of the first annular flange . <EOS>