A gas turbine engine, comprising: a housing; at least one compressor (12, 13) positioned within the housing; at least one turbine (15, 16, 17) operably coupled to the at least one compressor (12, 13) and including a plurality of blades extending radially from a longitudinal axis of the engine; and a seal segment positioned along a portion of the housing and comprising: a radially outer wall including at least one aperture extending along a width of the seal segment and defining a slot configured to receive a connector member; a radially inner wall comprised of ceramic matrix composite material; a first lateral wall and a second lateral wall, extending between the outer wall and the inner wall; and characterized in that the gas turbine engine further comprises: a rib member integrally formed with and extending between the outer wall and the inner wall intermediate the first and second lateral walls (34, 36) without overlapping the at least one aperture of the outer wall; a first cooling passage bounded by the outer wall, the inner wall, the rib member, and the first lateral wall; and a second cooling passage bounded by the outer wall, the inner wall, the rib member, and the second lateral wall, the second cooling passage having a smaller cross-section than the first cooling passage. a housing; at least one compressor (12, 13) positioned within the housing; at least one turbine (15, 16, 17) operably coupled to the at least one compressor (12, 13) and including a plurality of blades extending radially from a longitudinal axis of the engine; and a seal segment positioned along a portion of the housing and comprising: a radially outer wall including at least one aperture extending along a width of the seal segment and defining a slot configured to receive a connector member; a radially inner wall comprised of ceramic matrix composite material; a first lateral wall and a second lateral wall, extending between the outer wall and the inner wall; and characterized in that the gas turbine engine further comprises: a rib member integrally formed with and extending between the outer wall and the inner wall intermediate the first and second lateral walls (34, 36) without overlapping the at least one aperture of the outer wall; a first cooling passage bounded by the outer wall, the inner wall, the rib member, and the first lateral wall; and a second cooling passage bounded by the outer wall, the inner wall, the rib member, and the second lateral wall, the second cooling passage having a smaller cross-section than the first cooling passage. a radially outer wall including at least one aperture extending along a width of the seal segment and defining a slot configured to receive a connector member; a radially inner wall comprised of ceramic matrix composite material; a first lateral wall and a second lateral wall, extending between the outer wall and the inner wall; and characterized in that the gas turbine engine further comprises: a rib member integrally formed with and extending between the outer wall and the inner wall intermediate the first and second lateral walls (34, 36) without overlapping the at least one aperture of the outer wall; a first cooling passage bounded by the outer wall, the inner wall, the rib member, and the first lateral wall; and a second cooling passage bounded by the outer wall, the inner wall, the rib member, and the second lateral wall, the second cooling passage having a smaller cross-section than the first cooling passage. a rib member integrally formed with and extending between the outer wall and the inner wall intermediate the first and second lateral walls (34, 36) without overlapping the at least one aperture of the outer wall; a first cooling passage bounded by the outer wall, the inner wall, the rib member, and the first lateral wall; and a second cooling passage bounded by the outer wall, the inner wall, the rib member, and the second lateral wall, the second cooling passage having a smaller cross-section than the first cooling passage.