Ceramic matrix composite component for a gas turbine engine

A blade shroud assembly for a combustion turbine engine comprising:

• a metal support member supported within a combustion turbine engine and comprising an upstream edge and an opposed downstream edge each extending along a circumferential length;
• a ceramic matrix composite shroud member comprising an upstream portion and an opposed downstream portion each extending along a circumferential length and each having an arcuate shape defining an upstream slot and a downstream slot receiving and in direct contact with respectively the upstream edge and the downstream edge of the support member for supporting the shroud member and for shielding the support member from a combustion gas flowing within the combustion turbine engine;
• a layer of an abradable material disposed on a radially inner surface of the ceramic matrix composite shroud member for abradable wear against a rotating blade tip of the combustion turbine engine;
• the layer of abradable material and the ceramic matrix composite shroud member providing a degree of thermal insulation sufficient to maintain the metal support member below a predetermined temperature at respective points of direct contact between the ceramic matrix composite shroud member and the metal support member during operation of the combustion turbine engine;
• and
• a radially inner surface of the support member and a radially outer surface of the shroud member having respective closest points separated by a gap having a predetermined dimension;
• wherein a predetermined maximum dimension of the gap is selected so that a predetermined level of stress in the shroud member is not exceeded when the radially outer surface of the shroud member is deflected radially outwardly by the rotating blade tip to make contact with the radially inner surface of the support member.

A shroud assembly for sealing a cavity extending radially outward from a rotating blade tip to a blade ring of a combustion turbine engine to isolate the cavity from a combustion gas flowing past the blade tip, the shroud assembly comprising:

• a ceramic matrix composite member comprising a radially inner surface for wearing contact with the rotating blade tip and defining a primary pressure boundary for the combustion gas, the ceramic matrix composite member further comprising an arcuate portion defining a slot;
• a metal support member attached to a blade ring of the combustion turbine engine and comprising a radially inner surface separated from a radially outer surface of the ceramic matrix composite member by a gap and further comprising a portion extending into the slot for supporting the ceramic matrix composite member within the combustion turbine engine, the radially inner surface of the metal support member defining a secondary pressure boundary for the combustion gas in the event of failure of the ceramic matrix composite member;
• and
• the gap having a dimension sufficiently small to limit resonance of fluid surrounding the rotating blade tip in the event of failure of the ceramic matrix composite member.

A shroud assembly for sealing a cavity extending radially outward from a rotating blade tip to a blade ring of a combustion turbine engine to isolate the cavity from a combustion gas flowing past the blade tip, the shroud assembly comprising:

• a ceramic matrix composite member comprising a radially inner surface for wearing contact with the rotating blade tip and defining a primary pressure boundary for the combustion gas;
• a support member supporting the ceramic matrix composite member apart from the blade ring and comprising a radially inner surface separated from a radially outer surface of the ceramic matrix composite member by a gap, the radially inner surface of the support member defining a secondary pressure boundary for the combustion gas in the event of failure of the ceramic matrix composite member;
• and
• the gap having a dimension sufficiently small to limit resonance of fluid surrounding the rotating blade tip in the event of failure of the ceramic matrix composite member.