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An apparatus for mounting a refractory component such as a turbine shroud ring segment (32) with a ceramic core (42) onto a combustion turbine engine structure (34). The ring segment has a ceramic matrix composite skin (40), and optionally, a thermal insulation layer (46). A pin (60) is inserted thr

An apparatus for mounting a refractory component such as a turbine shroud ring segment (32) with a ceramic core (42) onto a combustion turbine engine structure (34). The ring segment has a ceramic matrix composite skin (40), and optionally, a thermal insulation layer (46). A pin (60) is inserted through a bore (48) in the core and through an attachment bar (54) with ends received in wells (50) in the core. The attachment bar may be attached to a backing member, or tophat (64), by a biasing device (76) that urges the refractory component snugly against the backing member to eliminate vibration. The backing member and refractory component have mating surfaces that may include angled sides (52S, 70). The backing member is attached to the engine structure. Turbine shroud ring segments can be attached by this apparatus to a surrounding structure to form a shroud ring.

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We claim as our invention: 1. An apparatus for use in a combustion turbine engine, the apparatus comprising: a refractory ceramic core comprising an exterior surface; a ceramic matrix composite skin bonded to at least a portion of the exterior surface of the core; the core and skin forming an integ

We claim as our invention: 1. An apparatus for use in a combustion turbine engine, the apparatus comprising: a refractory ceramic core comprising an exterior surface; a ceramic matrix composite skin bonded to at least a portion of the exterior surface of the core; the core and skin forming an integrated refractory component; a bore in the core comprising a length; a well formed into the refractory component through the exterior surface and intersecting the bore at an intermediate position along the length of the bore; a support bar comprising a first end in the well; a pin disposed in the bore and crossing the well at an intermediate position on the pin and connected to the bar; and a tophat contacting a back surface of the refractory component, wherein the support bar extends through an opening in the tophat and is attached to the tophat with a biasing device that urges the back surface of the refractory component against the tophat; whereby the refractory component is supported by the support bar via the pin. 2. The apparatus of claim 1, further comprising a compliant material disposed between the pin and the core. 3. The apparatus of claim 2, wherein the compliant material comprises a split spring bushing disposed around at least a part of the pin. 4. The apparatus of claim 1, wherein the refractory component comprises a segment of a ring of arcuate segments associated with a path of a blade tip moving within the combustion turbine engine. 5. The apparatus of claim 1, wherein the back surface of the refractory component comprises a central generally flat central section and two radially-inwardly sloping side sections, a front surface of the tophat comprises a geometry that mates with the back surface of the refractory component. 6. The apparatus of claim 1, further comprising a layer of compliant material between the tophat and the refractory component. 7. The apparatus of claim 1, wherein the bore and the pin are disposed generally perpendicular to a shaft axis of the engine. 8. A gas turbine engine comprising the apparatus of claim 1. 9. A shroud ring apparatus for a combustion turbine engine, the apparatus comprising: a shroud ring segment comprising a refractory ceramic core and a ceramic matrix composite skin bonded to at least a portion of an exterior surface of the core; a plurality of bores in the core, each comprising a length; a plurality of wells in a back surface of the ring segment that each intersect a bore at distributed intermediate positions along the length of the respective bores; a plurality of support bars, each bar comprising a first end received in one of the wells intersecting a particular bore and a second end received in another of the wells intersecting the particular bore, each end of each bar comprising a through-hole that is aligned with the respective bore; and a pin in each bore that passes through the holes in the respective support bars; a backing member with a front surface abutting the back surface of the ring segment; the support bars attached to the backing member by a biasing device that urges the ring segment against the backing member; and the backing member comprising an attachment element for connection to a surrounding engine structure. 10. The apparatus of claim 9, further comprising a split spring bushing mounted between each pin and respective bore. 11. A gas turbine engine comprising the apparatus of claim 9. 12. A shroud segment for a gas turbine engine comprising: a ceramic core; a ceramic matrix composite material bonded around a surface of the ceramic core to form an integrated refractory component; a pin disposed within a bore in the ceramic core; a well extending from a surface of the integrated refractory component to the bore and exposing a portion of the pin; a support member extending into the well and attached to the pin for supporting the integrated refractory component via the pin; a tophat disposed against the surface of the integrated refractory component and attached to the support member; and the tophat comprising a support element for attachment to a structure of the engine. 13. The shroud segment of claim 12, further comprising a biasing device urging the tophat and the surface of the integrated refractory component together. 14. The shroud segment of claim 12, wherein the pin comprises a metal alloy, and further comprising a slotted split spring disposed between the pin and the core.