Abstract: Methods of bonding first structures to second structures are disclosed wherein the first and second structures are fabricated materials having different physical characteristics. For example, the first structure may be a composite fan blade and the second structure may be a composite or metallic rotor, both for use in gas turbine engines. The method includes providing the first and second structures and plating or otherwise coating a portion of the first structure with a metal to provide a metal-coated portion. The method includes applying at least one intermediate material onto the metal-coated portion of the first structure. The method further includes bonding the metal-coated portion of the first structure and the intermediate material to the second structure. The bonding is carried out using a relatively low-temperature process, such as liquid phase bonding, including TLP and PTLP bonding. Brazing is also a suitable technique, depending on the materials chosen for the first and second structures.

Abstract: The present disclosure relates generally to a turbine engine case assembly, the turbine engine case assembly including a fan case including an outer frame encircling an axis, the outer frame including an outer frame exterior surface and an outer frame interior surface, at least two mounts disposed on the outer frame exterior surface, wherein the at least two mounts are circumferentially spaced along the outer frame exterior surface, and a compliant attachment device operably coupled to the at least two mounts.

Abstract: A spinner for a gas turbine engine is disclosed. The spinner may include a body extending between a first and second end comprised of a cured chopped unidirectional fiber pre-impregnated material. The body may have a generally conical shape and may further be plated with a metal or metal alloy.

Abstract: A compliant attachment for an organic matrix composite component that is configured to interface with a mating component is disclosed. The compliant attachment may comprise an inner surface configured to bond to an interfacing surface of a body portion of the organic matrix component, and an outer surface configured to interface with the mating component. The compliant attachment may have a coefficient of thermal expansion intermediate between a coefficient of thermal expansion of the body portion of the organic matrix composite component and a coefficient of thermal expansion of the mating component.

Abstract: A spinner for a gas turbine engine comprises an outer shell for defining an airflow path when mounted in a gas turbine engine. An inner surface is provided with a plurality of webs. A gas turbine engine and a fan section for a gas turbine engine are also disclosed.

Abstract: The present disclosure relates to composite airfoils bonded to a metallic root. A composite body (510) may be formed with a metallic co-molded detail (520). The co-molded detail (520) may be transient liquid phase (TLP) bonded to an attachment feature (530). The attachment feature (530) may allow the composite body (510) to be attached to a rotor (200). The airfoil (500) may also have a metallic edge (550) which is TLP bonded to the composite body (510) via a co-molded edge (540).

Abstract: Methods of bonding first structures to second structures are disclosed wherein the first and second structures are fabricated materials having different physical characteristics. For example, the first structure may be a composite fan blade and the second structure may be a composite or metallic rotor, both for use in gas turbine engines. The method includes providing the first and second structures and plating or otherwise coating a portion of the first structure with a metal to provide a metal-coated portion. The method includes applying at least one intermediate material onto the metal-coated portion of the first structure. The method further includes bonding the metal-coated portion of the first structure and the intermediate material to the second structure. The bonding is carried out using a relatively low-temperature process, such as liquid phase bonding, including TLP and PTLP bonding. Brazing is also a suitable technique, depending on the materials chosen for the first and second structures.

Abstract: The present disclosure relates to composite airfoils bonded to a metallic root. A composite body (510) may be formed with a metallic co-molded detail (520). The co-molded detail (520) may be transient liquid phase (TLP) bonded to an attachment feature (530). The attachment feature (530) may allow the composite body (510) to be attached to a rotor (200). The airfoil (500) may also have a metallic edge (550) which is TLP bonded to the composite body (510) via a co-molded edge (540).

Abstract: A composite component includes a plurality of layers. A fracture region includes at least one fracture inducing layer in an overlapping relationship with at least one of the plurality of layers.

Abstract: A plated tubular lattice structure is described. The plated tubular lattice structure may comprise a backbone structure which may include a plurality of axial posts and a plurality of pyramidal structures extending laterally from the axial posts and connecting the axial posts at nodes. The plated tubular lattice structure may further comprise a metal plating layer plated on an outer surface of the backbone structure.

Abstract: An industrial product comprising a polymer substrate formed in a shape of the industrial product, and a metallic plating layer plated on at least one surface of the industrial product is described. The industrial product may be nuclear waste equipment, industrial equipment exposed to saline, a satellite or satellite component, or heating, ventilation, air-conditioning and refrigeration (HVACR) equipment.

Abstract: A plated polymer component is disclosed. The plated polymer component may comprise a polymer substrate having an outer surface, and a metal plating deposited on the outer surface of the polymer substrate. The plated polymer component may further comprise an adhesion promoter at an interface between the polymer substrate and the metal plating.

Abstract: A compliant attachment for an organic matrix composite component that is configured to interface with a mating component is disclosed. The compliant attachment may comprise an inner surface configured to bond to an interfacing surface of a body portion of the organic matrix component, and an outer surface configured to interface with the mating component. The compliant attachment may have a coefficient of thermal expansion intermediate between a coefficient of thermal expansion of the body portion of the organic matrix composite component and a coefficient of thermal expansion of the mating component.

Abstract: A composite component includes a plurality of layers. A fracture region includes at least one fracture inducing layer in an overlapping relationship with at least one of the plurality of layers.

Abstract: A method for creating a laminate design geometry for a composite component according to an exemplary aspect of the present disclosure includes, among other things, defining a spatial volume of a solid defined between a plurality of external surface boundaries, defining an offset boundary spaced by an offset value from one of the plurality of external surface boundaries to define a region in which a ply is to be received, defining a partitioning boundary dividing the region into a ply portion and a resin portion; and repeating the steps of defining an offset boundary and defining a partitioning boundary by defining an offset boundary from any one of the plurality of external surface boundaries and the offset boundary in a previous iteration of defining an offset boundary.

Abstract: The present disclosure relates generally to a turbine engine case assembly, the turbine engine case assembly including a fan case including an outer frame encircling an axis, the outer frame including an outer frame exterior surface and an outer frame interior surface, at least two mounts disposed on the outer frame exterior surface, wherein the at least two mounts are circumferentially spaced along the outer frame exterior surface, and a compliant attachment device operably coupled to the at least two mounts.

Abstract: A plated polymer test specimen for measuring strain imparted to the plated polymer test specimen includes a polymeric substrate including a top, a bottom, a pair of opposing edges and a pair of opposing end edges, the top and bottom being plated with top and bottom metal layers respectively, the side edges and the end edges being at least substantially free of plating. The substrate includes two spaced-apart holes that extend through the top metal layer, substrate and the bottom metal layer. Alternatively, the substrate may comprise a composite layup structure. A method for testing the strain imparted to a plated polymer test specimen is also disclosed.

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract: Aviation components comprising a polymeric substrate having an outer surface wherein a metal is plated onto the outer surface to form a plated layer are disclosed. A method to make aviation components comprising a polymeric substrate having an outer surface and where a metal is plated onto the outer surface is disclosed. An over-plated heating element for shedding ice from an aircraft component having a polymeric substrate with a pocket to receive a heating element, a metal deposited onto the substrate, a heating element positioned within the pocket and a covering layer deposited onto the heating element and the plated layer is disclosed.

Abstract: Plated polymeric articles having a composite layup structure and method of making the same are disclosed. A plated polymeric article comprises a composite layup having first and second polymer layers. The plated polymeric article further comprises a first metal plated onto the polymer. Additionally, methods for fabricating a plated polymeric article are disclosed. A composite layup is provided and compression molded into a desired shape having an outer surface. The outer surface of the article is prepared to receive a catalyst and then is activated with the catalyst. A first metallic layer is then plated onto the outer surface.