Abstract: An aircraft component assembly has a structural body and a thermal management de-icing system for minimizing or preventing ice build-up on leading edges of the body. The system includes a supply line for flowing heated fluid to the leading edges and a cooling device that interposes the supply line to prevent overheating of the leading edges thus protecting bodies that may be made of composite materials that are more susceptible to heat.

Abstract: A ceramic turbine engine exhaust component, such as a ceramic matrix composite (“CMC”) exhaust center body may be positioned around a metallic attachment ring. The attachment ring may have a greater coefficient of thermal expansion than the CMC center body. A plurality of bolts radially-spaced around the circumference of the attachment ring may be inserted through apertures in the center body with a sliding fit, and may be coupled to the attachment ring. The bolts may slide within the apertures, allowing the attachment ring to thermally expand without applying extra loads on the exhaust center body due to the expansion.

Abstract: Aspects of this disclosure relate to a method of manufacturing wallboard which includes providing a first layer of facing material, creasing the first layer facing material intermittently to create a series of creased portions, providing a gypsum slurry on the first layer of facing material and providing a second layer of facing material over the gypsum slurry. Further, creasing the first layer of facing material intermittently can include intermittently creasing the first layer of facing material in a substantially linear fashion extending in a first direction of the first layer of facing material so that the first layer of facing material exhibits a linear series of creased portions extending in the first direction of the first layer of facing material and a series of portions that are not creased extending in the first direction of the first layer of facing material.

Abstract: A ceramic turbine engine exhaust component, such as a ceramic matrix composite (“CMC”) exhaust center body may be positioned around a metallic attachment ring. The attachment ring may have a greater coefficient of thermal expansion than the CMC center body. A plurality of bolts radially-spaced around the circumference of the attachment ring may be inserted through apertures in the center body with a sliding fit, and may be coupled to the attachment ring. The bolts may slide within the apertures, allowing the attachment ring to thermally expand without applying extra loads on the exhaust center body due to the expansion.

Abstract: An aircraft component assembly has a structural body and a thermal management de-icing system for minimizing or preventing ice build-up on leading edges of the body. The system includes a supply line for flowing heated fluid to the leading edges and a cooling device that interposes the supply line to prevent overheating of the leading edges thus protecting bodies that may be made of composite materials that are more susceptible to heat.

Abstract: Aspects of this disclosure relate to a method of manufacturing wallboard which includes providing a first layer of facing material, creasing the first layer facing material intermittently to create a series of creased portions, providing a gypsum slurry on the first layer of facing material and providing a second layer of facing material over the gypsum slurry. Further, creasing the first layer of facing material intermittently can include intermittently creasing the first layer of facing material in a substantially linear fashion extending in a first direction of the first layer of facing material so that the first layer of facing material exhibits a linear series of creased portions extending in the first direction of the first layer of facing material and a series of portions that are not creased extending in the first direction of the first layer of facing material.

Abstract: Aspects of this disclosure relate to a method of manufacturing wallboard which includes providing a first layer of facing material, creasing the first layer facing material intermittently to create a series of creased portions, providing a gypsum slurry on the first layer of facing material and providing a second layer of facing material over the gypsum slurry. Further, creasing the first layer of facing material intermittently can include intermittently creasing the first layer of facing material in a substantially linear fashion extending in a first direction of the first layer of facing material so that the first layer of facing material exhibits a linear series of creased portions extending in the first direction of the first layer of facing material and a series of portions that are not creased extending in the first direction of the first layer of facing material.