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 (14, 16) protrude, the ring support structure including a central shroud from which a first and a second radial clamps (32, 36) protrude between which the first and second attachment tabs (14, 16) 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 intended to pass through the turbine ring assembly, the first and second annular flanges (33, 34) having respectively a first free end (331, 341) and a second end (332, 342) 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 (332, 342) of the first and second annular flanges (33, 34) 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 (330, 340), 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 intended to pass through the turbine ring assembly, the first and second annular flanges (33, 34) having respectively a first free end (331, 341) and a second end (332, 342) 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 (332, 342) of the first and second annular flanges (33, 34) 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 (330, 340), 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.