A turbine ring assembly comprising both a plurality of ring sectors made of ceramic matrix composite material to form a turbine ring, and also a ring support structure having first and second annular flanges (32, 36), each ring sector having a portion forming an annular base with, in a radial direction of the turbine ring, an inner face defining the inside face of the turbine ring and an outer face from which there extend first and second tabs (14, 16), the tabs of each ring sector being held between the two annular flanges (32, 36) of the ring support structure; wherein the first tab of each ring sector includes a first opening receiving a portion of a first holder element secured to the first annular flange and a second opening receiving a portion of a second holder element secured to the first annular flange, radial clearance being present when cold between the first and second openings (142, 143) in the first tab and the portions of the first and second holder elements present in said first and second openings, said holder elements being made of a material having a coefficient of thermal expansion that is greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors, the first opening presenting a shape that is oblong extending in the circumferential direction of the turbine ring; wherein the second tab of each ring sector includes a first opening receiving a portion of a third holder element secured to the second annular flange and a second opening receiving a portion of a fourth holder element secured to the second annular flange, radial clearance being present when cold between the first and second openings (162, 163) in the second tab and the portions of the third and fourth holder elements present in said first and second openings, said holder elements being made of a material having a coefficient of thermal expansion that is greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors, the first opening presenting a shape that is oblong extending in the circumferential direction of the turbine ring, the first and second openings of the first tab being in axial alignment with the first and second openings of the second tab; wherein the first annular flange includes on its face facing the first tab of each ring sector a plurality of thrust portions distributed circumferentially over the first flange, the end of the first tab of each ring sector when cold being in radial abutment against two thrust portions; and wherein the second annular flange includes on its face facing the second tab of each ring sector a plurality of thrust portions distributed in circumferential manner over the second flange, the end of each second tab of each ring sector when cold being in radial abutment against two thrust portions. wherein the first tab of each ring sector includes a first opening receiving a portion of a first holder element secured to the first annular flange and a second opening receiving a portion of a second holder element secured to the first annular flange, radial clearance being present when cold between the first and second openings (142, 143) in the first tab and the portions of the first and second holder elements present in said first and second openings, said holder elements being made of a material having a coefficient of thermal expansion that is greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors, the first opening presenting a shape that is oblong extending in the circumferential direction of the turbine ring; wherein the second tab of each ring sector includes a first opening receiving a portion of a third holder element secured to the second annular flange and a second opening receiving a portion of a fourth holder element secured to the second annular flange, radial clearance being present when cold between the first and second openings (162, 163) in the second tab and the portions of the third and fourth holder elements present in said first and second openings, said holder elements being made of a material having a coefficient of thermal expansion that is greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors, the first opening presenting a shape that is oblong extending in the circumferential direction of the turbine ring, the first and second openings of the first tab being in axial alignment with the first and second openings of the second tab; wherein the first annular flange includes on its face facing the first tab of each ring sector a plurality of thrust portions distributed circumferentially over the first flange, the end of the first tab of each ring sector when cold being in radial abutment against two thrust portions; and wherein the second annular flange includes on its face facing the second tab of each ring sector a plurality of thrust portions distributed in circumferential manner over the second flange, the end of each second tab of each ring sector when cold being in radial abutment against two thrust portions.