between the shroud 34 and engine casing 36 under enough pressure to prevent combustion gases from entering this area through clearances between shroud segments 32 cooling air may also flow in channels within the blades not shown in the following description u201c axial u201d means generally parallel to the shaft axis 22 u201c circumferential u201d means generally along the circumference of a circle centered on the shaft axis 22 in a plane normal to the shaft axis 22 and u201c radial u201d means in a generally perpendicular orientation or direction relative to the shaft axis 22 a refractory shroud ring segment 32 of a combustion turbine engine is an exemplary application of the technology of the present invention this technology can also be applied to other components of combustion turbine engines fig2 and 3 show an isometric and top view of a pin loaded refractory core shroud ring segment 32 the segment 32 is an integrated refractory component having a cmc skin 40 bonded to at least a portion of an exterior surface of a refractory ceramic core 42 the hot side 44 of the segment 32 may be protected by a high temperature thermal insulation 46 deposited on the cmc skin 40 a wide range of ceramic matrix composites cmcs have been developed that combine a matrix material with a reinforcing phase of a different composition such as mullite silica or of the same composition alumina alumina or silicon carbide silicon carbide the fibers may be continuous or long discontinuous fibers the matrix may further contain whiskers platelets or particulates reinforcing fibers may be disposed in the matrix material in layers with the.