Abstract: A ceramic matric composite (CMC) component for a gas turbine engine, such as blade outer air seal (BOAS), may be shielded from thermal stress. The CMC component includes a first surface configured for exposure to a hot gas stream, a second surface configured for exposure to a cold gas stream, an edge surface of the CMC component disposed between and connecting the first and second surfaces. At least one coating layer is disposed on the first surface and wrapped over the edge surface and the second surface, wherein the at least one coating layer disposed on the second surface has a lower thermal conductivity than the CMC component so as to reduce a thermal gradient between the cooled first surface and the heated second surface.

Abstract: A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

Abstract: A ceramic matric composite (CMC) component for a gas turbine engine, such as blade outer air seal (BOAS), may be shielded from thermal stress. The CMC component includes a first surface configured for exposure to a hot gas stream, a second surface configured for exposure to a cold gas stream, an edge surface of the CMC component disposed between and connecting the first and second surfaces. At least one coating layer is disposed on the first surface and wrapped over the edge surface and the second surface, wherein the at least one coating layer disposed on the second surface has a lower thermal conductivity than the CMC component so as to reduce a thermal gradient between the cooled first surface and the heated second surface.

Abstract: A ceramic matrix composite (CMC) vane or layup therefor includes first and second platforms, and an airfoil portion extending therebetween. The airfoil portion includes a first portion of a shear tube extending relatively orthogonal to the first and second platforms, wherein the first portion of the shear tube extends through the first and second platforms, and wherein the first portion of the shear tube defines a leading edge and a hollow core of the airfoil portion. A second portion of the shear tube is connected to the first portion of shear tube and extends relatively orthogonal to the first and second platforms, wherein the second portion of the shear tube also extends through the first and second platforms, and wherein the second portion of the shear tube includes a Y-weave ply and a trailing edge noodle that define a trailing edge of the airfoil portion.

Abstract: A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

Abstract: A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

Abstract: A method of forming a ceramic matrix composite (CMC) vane including an inner diameter platform, an outer diameter platform, and an airfoil extending between the inner diameter platform and the outer diameter platform includes laying up a ceramic preform by arranging at least one core formed from a first ceramic material, and laying up, over the at least one ceramic core, a plurality of contoured plies, each of the plurality of contoured plies formed from a second ceramic material. Each of the plurality of contoured plies partially forms the inner diameter platform, the outer diameter platform, and the airfoil of the vane. The method further includes densifying the ceramic preform with a matrix.

Abstract: The invention relates to a dispenser for transferring layers of goods from a pallet onto a receiving surface and then down a discharge conveyor. The dispenser incorporates a vertically movable platform capable of bringing a first tier of goods in alignment with a rotary table. Sweeper arm moves the goods on to the table as it rotates. Goods accumulate on the rotary table and then become guided down a discharge conveyor for further processing.

Abstract: The invention relates to a dispenser for transferring layers of goods from a pallet onto a receiving surface and then down a discharge conveyor. The dispenser incorporates a vertically movable platform capable of bringing a first tier of goods in alignment with a rotary table. Sweeper arm moves the goods on to the table as it rotates. Goods accumulate on the rotary table and then become guided down a discharge conveyor for further processing.

Abstract: A configurable wall is disclosed. In an example, the configurable wall includes a first hollow-formed module having an outer layer selected to portray a material of manufacture which is substantially different than a material with which the first hollow-formed module is manufactured. The wall also includes a second hollow-formed module having an outer layer selected to compliment the outer layer of the first hollow-formed module. The wall also includes an interconnect to secure the first module and the second module together.

Abstract: A cell for the electrowinning of aluminum from molten salts has a cell bottom lining consisting partly of a refractory mass (4 ) and partly of carbon bodies (5). At least 30% and preferably 50% or more of the cell bottom area is occupied by the refractory mass (4). The carbon bodies (5) are level with the refractory mass (4) or are recessed therein.

Abstract: A cell for the electrowinning of aluminum from molten salts has a cell bottom lining consisting partly of a refractory mass (4) and partly of carbon bodies (5). At least 30% and preferably 50% or more of the cell bottom area is occupied by the refractory mass (4). The carbon bodies (5) are level with the refractory mass (4) or are recessed therein.