Abstract: A frame assembly includes a frame and a mounting bracket assembly. The frame includes an inner hub, an outer shell located opposite the inner hub, and a plurality of struts connecting the inner hub with the outer shell. At least one strut of the plurality of struts is a hollow strut with a radial passage extending therethrough. The mounting bracket assembly includes an inner flange located on an inner surface of the inner hub, an outer flange located on an outer surface of the outer shell, and a radial linkage connecting the inner flange with the outer flange. The radial linkage extends through the radial passage of the hollow strut.

Abstract: A method of manufacturing a composite component having an outer shell, an inner hub, and a plurality of struts connecting the outer shell and the inner hub. A plurality of outer shell preform portions having bifurcated strut portions are connected together to form an outer shell hoop preform, and a plurality of inner hub preform portions having bifurcated strut portions are connected together to form an inner hub hoop preform. The bifurcated strut portions are arranged to extend between the outer shell hoop preform and the inner hub hoop preform, and are arranged adjacent to one another to form a strut preform. A matrix material is injected into the mold tooling structure and a curing process is applied to the mold tooling structure to obtain the composite component.

Abstract: A preform for a composite airfoil of a gas turbine engine includes a first woven fabric and a second woven fabric. The second woven fabric is located opposite the first woven fabric, with a second inner surface of the second woven fabric opposing a first inner surface of the first woven fabric to form a preform gap therebetween. A first transverse woven fabric portion extends from the first inner surface towards the second inner surface, and a second transverse woven fabric portion extends from the second inner surface towards the first inner surface. The second transverse woven fabric portion is engaged with the first transverse woven fabric portion to form a joint. Each of the first woven fabric, the second woven fabric, the first transverse woven fabric portion, and the second transverse woven fabric portion is a three-dimensional woven fabric including a plurality of reinforcing fiber tows.

Abstract: An airfoil includes a non-uniform weave structure that is two-dimensional or three-dimensional, the non-uniform weave structure including a plurality of reinforcing fibers, the non-uniform weave structure having a first region with a first stiffness and a second region with a second stiffness higher than the first stiffness, wherein the plurality of reinforcing fibers include higher density fibers in the second region and lower density fibers in the first region so as to increase a stiffness of the airfoil at the second region of the airfoil in a desired orientation to achieve a desired aeromechanics response of the airfoil.

Abstract: A turbine engine for an aircraft. The turbine engine includes a vane support and a vane. The vane support has a vane-facing surface. A first hook and a second hook extend from the vane-facing surface and define a channel therebetween. The vane includes an airfoil and an outer band connected to the airfoil. The outer band is positioned in the channel to form a gap between a support-facing surface of the outer band and the vane-facing surface under assembly conditions of the turbine engine. The vane-facing surface and the support-facing surface are shaped to form a contact configuration that occurs when, under an operating condition of the turbine engine, the vane flexes and at least a portion of the support-facing surface contacts the vane-facing surface over a contacting region to eliminate the gap over the contacting region.

Abstract: A turbine engine for an aircraft. The turbine engine includes a vane support and a vane. The vane support has a vane-facing surface. A first hook and a second hook extend from the vane-facing surface and define a channel therebetween. The vane includes an airfoil and an outer band connected to the airfoil. The outer band is positioned in the channel to form a gap between a support-facing surface of the outer band and the vane-facing surface under assembly conditions of the turbine engine. The vane-facing surface and the support-facing surface are shaped to form a contact configuration that occurs when, under an operating condition of the turbine engine, the vane flexes and at least a portion of the support-facing surface contacts the vane-facing surface over a contacting region to eliminate the gap over the contacting region.

Abstract: A method of manufacturing a woven fabric for a composite component for a turbine engine. The method includes arranging a plurality of warp fiber tows to extend in the warp direction. The plurality of warp fiber tows is arranged in a thickness direction to form a plurality of warp fiber layers and is arranged in a weft direction to form a plurality of warp fiber columns. The method also includes weaving the plurality of weft fiber tows with the plurality of warp fiber tows. The plurality of weft fiber tows includes a multi-layer weft fiber tow. The multi-layer weft fiber tow is woven with a multi-layer portion that extends two or more warp fiber layers of the plurality of warp fiber layers.

Abstract: A three-dimensional woven fabric for a composite component and methods of manufacturing such a fabric. The woven fabric has a first region, and a second region and a plurality of reinforcing fiber tows woven together in a three-dimensional pattern such that the woven fabric has a warp direction, a weft direction, and a thickness direction. The reinforcing fiber tows include a plurality of warp fiber tows and a plurality of weft fiber tows. At least a portion of the plurality of reinforcing fiber tows provided in the first region includes bulk fiber tows having a first toughness. At least a portion of the plurality of reinforcing fiber tows provided in the second region includes tough fiber tows having a second toughness. The second toughness of the tough fiber tows is greater than the first toughness of the bulk fiber tows.

Abstract: An airfoil includes a non-uniform weave structure that is two-dimensional or three-dimensional, the non-uniform weave structure including a plurality of reinforcing fibers, the non-uniform weave structure having a first region with a first stiffness and a second region with a second stiffness higher than the first stiffness, wherein the plurality of reinforcing fibers include higher density fibers in the second region and lower density fibers in the first region so as to increase a stiffness of the airfoil at the second region of the airfoil in a desired orientation to achieve a desired aeromechanics response of the airfoil.