Pin-loaded mounting apparatus for a refractory component in a combustion turbine engine
View Patent ↗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 ( 52 S, 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.
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.