Abstract: An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and pressure and suction sides that join the leading end and the trailing end. The airfoil wall includes a wishbone-shaped fiber layer structure that has a pair of arms that merge into a single leg. The pair of arms are formed by first and second S-shaped fiber layers each of which is comprised of a network of fiber tows. The first and second S-shaped fiber layers merge to form the single leg. The single leg comprises fiber tows from each of the first and second S-shaped fiber layers that are interwoven, and the single leg forms at least a portion of the trailing end of the airfoil wall.

Abstract: Disclosed herein is a method of reinforcing a composite comprising determining a location of a first cooling hole in a plurality of plies; where a cooling gas is transported through the cooling hole; disposing a z-fiber in the plurality of plies at a location proximate to where the first cooling hole will be located; where the z-fiber enters the plurality of plies at either an upper surface or a lower surface; and where the z-fiber traverses a portion of the plurality of plies in the z-direction proximate to the first cooling hole; and traverses the plurality of plies in an x or y direction further away from the first cooling hole; where the z-direction is in the thickness direction of the plurality of plies and where the x and y-direction are perpendicular to the z-direction.

Abstract: Disclosed herein is a composite comprising a ceramic matrix composite comprising a ceramic matrix and ceramic fibers; and one or more sacrificial fibers woven into the ceramic matrix composite; where the sacrificial fibers are operative to undergo oxidation or melting upon being subjected to an elevated temperature; and wherein the sacrificial fibers leave cooling holes in the composite preform upon being subjected to oxidation or melting.

Abstract: An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

Abstract: An airfoil includes an airfoil section defining suction and pressure sides and leading and a trailing ends, the airfoil section being formed of a fiber-reinforced composite comprised of fiber plies, the fiber plies including at least one core fiber ply defining a tube that circumscribes an internal cavity and an overwrap fiber ply that wraps around the at least one core fiber ply, and aft of the internal cavity the overwrap fiber ply on the pressure side including first fingers and the overwrap ply on the suction side including second fingers, the first fingers being interdigitated with the second fingers to form an interlocked joint in the trailing end.

Abstract: An airfoil incudes an airfoil section that defines an internal cavity. The airfoil section is formed of a fiber-reinforced composite that is comprised of fiber plies. The fiber plies include core fiber plies and an overwrap fiber ply that wraps around the core fiber plies. The core fiber plies are arranged as first and second tubes. each of the first and second tubes defines a plurality of windows therein. The windows of the first tube align with the windows of the second tube so as to form radially-spaced ribs that extend across the internal cavity. At least one of the first or second tubes has at least one tab that is radially between the radially-spaced ribs. The at least one tab interlocks the first and second tubes.

Abstract: An airfoil includes an airfoil section that is formed of a fiber-reinforced composite that has fiber plies. The fiber plies include at least one overwrap fiber ply, first and second support fiber plies, and a serpentine fiber ply. The overwrap fiber ply circumscribes an internal cavity and defines first and second sides and leading and trailing ends of the airfoil section. The first and second support fiber plies define respective first and second radial tubes in the internal cavity. The serpentine fiber ply winds from the first side and around the first radial tube to the second side, then from the second side back to the first side, and then from the first side and around the second radial tube back to the second side.

Abstract: An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

Abstract: An airfoil incudes an airfoil section that defines an internal cavity. The airfoil section is formed of a fiber-reinforced composite that is comprised of fiber plies. The fiber plies include core fiber plies and an overwrap fiber ply that wraps around the core fiber plies. The core fiber plies are arranged as first and second tubes. each of the first and second tubes defines a plurality of windows therein. The windows of the first tube align with the windows of the second tube so as to form radially-spaced ribs that extend across the internal cavity. At least one of the first or second tubes has at least one tab that is radially between the radially-spaced ribs. The at least one tab interlocks the first and second tubes.

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and pressure and suction sides that join the leading end and the trailing end. The airfoil wall includes a wishbone-shaped fiber layer structure that has a pair of arms that merge into a single leg. The pair of arms are formed by first and second S-shaped fiber layers each of which is comprised of a network of fiber tows. The first and second S-shaped fiber layers merge to form the single leg. The single leg comprises fiber tows from each of the first and second S-shaped fiber layers that are interwoven, and the single leg forms at least a portion of the trailing end of the airfoil wall.

Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a composite gas turbine engine component including a first flange extending radially from a main body at a junction having an arcuate profile. An adapter ring includes a mate face dimensioned to follow a contour of the junction such that the junction sits on the mate face. A method of assembly for a gas turbine engine is also disclosed.

Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a composite gas turbine engine component including a first flange extending radially from a main body at a junction having an arcuate profile. An adapter ring includes a mate face dimensioned to follow a contour of the junction such that the junction sits on the mate face. A method of assembly for a gas turbine engine is also disclosed.

Abstract: An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

Abstract: A bracket assembly for a gas turbine engine includes a first foot that includes at least one flange fastener opening and a duct flange support surface. A second foot includes at least one body portion fastener opening and a duct body support surface. At least one leg connects the first foot relative to the second foot.

Abstract: A gas turbine engine duct assembly includes a composite duct body that includes at least one rim. A flanged bracket includes a radially extending portion that defines a flange. An axially extending portion has an inner duct rim recess for accepting a portion of the at least one rim. At least one attachment plate has a projection recess for accepting a projection on the flanged bracket and an outer rim recess for accepting a portion of the at least one rim.

Abstract: A gas turbine engine duct assembly includes a composite duct body that includes at least one rim. A flanged bracket includes a radially extending portion that defines a flange. An axially extending portion has an inner duct rim recess for accepting a portion of the at least one rim. At least one attachment plate has a projection recess for accepting a projection on the flanged bracket and an outer rim recess for accepting a portion of the at least one rim.

Abstract: A bracket assembly for a gas turbine engine includes a first foot that includes at least one flange fastener opening and a duct flange support surface. A second foot includes at least one body portion fastener opening and a duct body support surface. At least one leg connects the first foot relative to the second foot.

Abstract: The present disclosure relates generally to a manifold including a plurality of manifold channels disposed therethrough, each manifold channel including a manifold channel opening, and a seal plate, including a plurality of seal plate apertures disposed thereon, operably coupled to the manifold, wherein the seal plate includes at least one seal plate channel extending between at least two of the plurality of seal plate apertures.

Abstract: An apparatus that includes a conduit having a first end, a second end, and a longitudinal axis. The conduit may define an inner channel and may be configured to extend through a vane cavity of a vane. The apparatus may further include a damping finger that includes a first portion coupled to the conduit and a second portion diverging outward at an angled orientation from the conduit. The damping finger may be resiliently flexible and the second portion of the damping finger may be configured to contact an inner surface of the vane.