A segmented turbine shroud that extends around a central axis, the segmented turbine shroud comprising a first shroud segment including a first carrier segment, a first blade track segment, and a first retainer that couples the first carrier segment to the first blade track segment, the first blade track segment made from a ceramic-matrix-composite material, a second shroud segment arranged circumferentially adjacent to the first shroud segment around the central axis, the second shroud segment including a second carrier segment, a second blade track segment, and a second retainer that couples the second carrier segment to the second blade track segment, the second blade track segment made from a ceramic-matrix-composite material, and a circumferential seal arranged between the first shroud segment and the second shroud segment to block gasses from passing through a circumferential interface of the first shroud segment and the second shroud segment, the circumferential seal engaging a first seal-locating feature (143, 145) formed in the first carrier segment and a second seal-locating feature (143, 145) formed in the second carrier segment so that the circumferential seal is held in place circumferentially between the first shroud segment and the second shroud segment, wherein the each carrier segment includes a central attachment body engaged with a corresponding blade track segment and a pair of end caps (144, 146) that extend circumferentially in opposing directions from the central attachment body and each end cap (144, 146) is formed to include a seal-locating feature (143, 145), characterised in that a closed cavity sealed from airflow from most adjacent cavities is formed by the first shroud segment between the first carrier segment and the first blade track segment, the closed cavity extends along the central attachment body of the first carrier segment, and the closed cavity is circumferentially bounded by the pair of end caps (144, 146). a first shroud segment including a first carrier segment, a first blade track segment, and a first retainer that couples the first carrier segment to the first blade track segment, the first blade track segment made from a ceramic-matrix-composite material, a second shroud segment arranged circumferentially adjacent to the first shroud segment around the central axis, the second shroud segment including a second carrier segment, a second blade track segment, and a second retainer that couples the second carrier segment to the second blade track segment, the second blade track segment made from a ceramic-matrix-composite material, and a circumferential seal arranged between the first shroud segment and the second shroud segment to block gasses from passing through a circumferential interface of the first shroud segment and the second shroud segment, the circumferential seal engaging a first seal-locating feature (143, 145) formed in the first carrier segment and a second seal-locating feature (143, 145) formed in the second carrier segment so that the circumferential seal is held in place circumferentially between the first shroud segment and the second shroud segment, wherein the each carrier segment includes a central attachment body engaged with a corresponding blade track segment and a pair of end caps (144, 146) that extend circumferentially in opposing directions from the central attachment body and each end cap (144, 146) is formed to include a seal-locating feature (143, 145), characterised in that a closed cavity sealed from airflow from most adjacent cavities is formed by the first shroud segment between the first carrier segment and the first blade track segment, the closed cavity extends along the central attachment body of the first carrier segment, and the closed cavity is circumferentially bounded by the pair of end caps (144, 146).