A ceramic matrix composite (CMC) component for a combustion turbine engine ( 10 ). A blade shroud assembly ( 30 ) may be formed to include a CMC member ( 32 ) supported from a metal support member ( 32 ). The CMC member includes arcuate portions ( 50, 52 ) shaped to surround extending portions ( 46, 48 ) of the support member to insulate the metal support member from hot combustion gas ( 16 ). The use of a low thermal conductivity CMC material allows the metal support member to be in direct contact with the CMC material. The gap ( 42 ) between the CMC member and the support member is kept purposefully small to limit the stress developed in the CMC member when it is deflected against the support member by the force of a rubbing blade tip ( 14 ). Changes in the gap dimension resulting from differential thermal growth may be regulated by selecting an angle (A) of a tapered slot ( 76 ) defined by the arcuate portion.

Ceramic matrix composite component for a gas turbine engine

An air seal is illustrated as used in a gas turbine engine. The seal includes at least a seal substrate, a relatively dense, erosion resistant ceramic layer applied over the bond coat, and an abradable ceramic layer applied in a local area over the dense ceramic layer. The abradable ceramic interacts with a component moving relative to the seal, such as a turbine blade that moves relative to the seal, and cooperates with the moving component to provide sealing and thermal insulation.

Article having durable ceramic coating with localised abradable portion

This invention provides a shaped, graded, cermet article comprising at least one continuous ceramic phase and at least one discontinuous metal phase, the ratio of ceramic/metal being controlled and varied over the thickness of the article. The ceramic phase preferably is microcrystalline.

Graded refractory cermet article

To enable shroud segments in a gas turbine rotor blade stage to operate at high temperatures with an adequate margin of safety, the shroud segments are mounted and cooled such that they are thrust outwards against seatings on surrounding high strength support structure by the gas pressure in the turbine passage, the shroud segments being provided with strengthening ribs or the like so that the outward thrust is transferred to the support structure through a plurality of load paths distributed over the outer sides of the shroud segments as necessary to avoid overstressing.

Turbine shroud and turbine shroud assembly

A turbine blade shroud assembly for a gas turbine engine includes a metal substrate ring on the engine, a continous ceramic barrier ring inside the substrate ring and exposed to hot gas in a hot gas flow path of the engine, and a wire mesh compliant ring between the barrier and substrate rings. The temperature of the barrier ring increases faster than the temperature of the substrate ring as the temperature in the hot gas flow path increases. The coefficient of thermal expansion of the substrate ring is less than the coefficient of thermal expansion of the barrier ring so that the barrier ring expands relative to the substrate ring with increasing temperature in the hot gas flow path and development of tensile hoop stress in the ceramic barrier ring is minimized.

Turbine blade shroud assembly

Outer air seal structures of particular suitability for use in gas turbine engines are disclosed. Techniques for improving resistance to erosion while maintaining good abradability are discussed. In one particular structure the ceramic facing material of an outer air seal (30) at the leading edge region (36) is densified by a plasma gun to produce a glazed area (52) which is resistant to erosion.

Ceramic faced outer air seal for gas turbine engines

Keramikbeschichtete aeussere luftdichtung fuer gasturbinentriebwerke

The present invention relates to a method for depositing a coating of abrasive powder on a substrate by means of a plasma arc torch. The particles of abrasive powder and of matrix material come simultaneously into contact with the surface of the substrate to be coated. For narrow substrates, this substrate is offset with respect to the axis of the plasma flow discharged from the torch. The invention may for instance be used for applying abrasive coatings to gas turbine engine elements such as rotor blades.

Eaton Harry Edwin

Papers

Ceramic faced outer air seal for gas turbine engines

Keramikbeschichtete aeussere luftdichtung fuer gasturbinentriebwerke

Method for depositing a coating of abrasive powder on a substrate