Abstract: A for capital management with custom assemblies and schedulable cost lines. This method and system allow a user to offset intervals for the recurring costs associated with the replacement or repair of capital assets (e.g., doors, electrical, heating, ventilation, air conditioning (HVAC), furnishing, mechanical, roofing, plumbing, windows, etc.) in a building and maintain ongoing interval periods for further estimates ongoing basis upon industry estimates of the useful those assets.

Abstract: A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

Abstract: A bladed disk preform system is provided. Multiple sheets are formed or provided. Each of the sheets may include multiple ceramic fibers. Slots may be cut in each of the sheets before or after forming. The slots extend from an outer edge of the sheets inward toward a center of the sheets. The sheets are stacked on top of each other to form a bladed disk preform. The bladed disk preform is porous. The bladed disk preform may include a plurality of blade portions extending outward from a root portion. Each of the slots is positioned between adjacent blade portions.

Abstract: A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

Abstract: A turbine vane comprising ceramic matrix composite materials. The turbine vane includes an vane support core, an airfoil, and a pair of end walls that are spaced apart from one another to define a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

Abstract: A ceramic matrix composite (CMC) is formed using a three-dimensional (3-D) woven preform by removing the set of sacrificial fibers from the 3-D woven preform and allowing a metal or metal alloy infiltrate the 3-D woven preform. The 3-D woven preform is formed by a method that includes providing a woven layer comprising a first set of ceramic fibers oriented in a first (x) direction woven with a second set of ceramic fibers oriented in a second (y) direction; stacking a plurality of woven layers on top of each other, said woven layers providing a two-dimensional (2-D) preform; weaving a set of sacrificial fibers in a third (z) direction with the 2-D preform, said weaving providing the 3-D woven preform; and shaping the 3-D woven preform into a predetermined shape.

Abstract: A turbine vane comprising ceramic matrix composite materials. The turbine vane includes an vane support core, an airfoil, and a pair of end walls that are spaced apart from one another to define a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

Abstract: A bladed disk preform system is provided. Multiple sheets are formed or provided. Each of the sheets may include multiple ceramic fibers. Slots may be cut in each of the sheets before or after forming. The slots extend from an outer edge of the sheets inward toward a center of the sheets. The sheets are stacked on top of each other to form a bladed disk preform. The bladed disk preform is porous. The bladed disk preform may include a plurality of blade portions extending outward from a root portion. Each of the slots is positioned between adjacent blade portions.

Abstract: A ceramic matrix composite (CMC) is formed using a three-dimensional (3-D) woven preform by removing the set of sacrificial fibers from the 3-D woven preform and allowing a metal or metal alloy infiltrate the 3-D woven preform. The 3-D woven preform is formed by a method that includes providing a woven layer comprising a first set of ceramic fibers oriented in a first (x) direction woven with a second set of ceramic fibers oriented in a second (y) direction; stacking a plurality of woven layers on top of each other, said woven layers providing a two-dimensional (2-D) preform; weaving a set of sacrificial fibers in a third (z) direction with the 2-D preform, said weaving providing the 3-D woven preform; and shaping the 3-D woven preform into a predetermined shape.