Abstract: A method of manufacturing an erosion-shielded turbine blade includes providing a turbine blade for use with a rotary machine. The turbine blade includes an airfoil extending between a root and a tip. The airfoil includes a pressure side and an opposite suction side, and each of the pressure and suction sides extends between a leading edge and a trailing edge. The method also includes printing a green body part by an additive manufacturing process by selectively depositing a binder solution across a particulate erosion-resistant material, and sintering the green body part to produce a post-sintering erosion shield that includes densified erosion-resistant material. The method also includes coupling the erosion shield to the leading edge of the turbine blade.

Abstract: A method of forming an erosion shield for a turbine blade includes depositing a layer of filler material defining an upper surface. The method also includes depositing a layer of erosion-resistant material across the upper surface of the layer of filler material. An interface is defined between the layer of filler material and the layer of erosion-resistant material and has a shape of the upper surface. The method also includes machining the layer of filler material to produce the erosion shield. The erosion shield has the layer of erosion-resistant material, the machined layer of filler material, and the interface defined therebetween. An inner surface of the erosion shield is defined by the machined layer of filler material that is sized and shaped for attaching to a leading edge of the turbine blade. Each of the interface and the inner surface extend a length of the erosion shield.

Abstract: Methods, apparatus, systems, and articles of manufacture to provide damping of an airfoil are disclosed. An example airfoil is disposed in a flow path, the airfoil including a shell defining an exterior surface of the airfoil and forming a cavity in an interior surface of the airfoil, and a lattice damper disposed in the cavity, the lattice damper to reduce vibrational loads exerted on the airfoil.

Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine; a fan including a plurality of fan blades rotatably driven by the turbomachine; a nacelle surrounding at least in part the plurality of fan blades of the fan; and a clearance control system including a control ring positioned at least partially within the nacelle, coupled to the nacelle, or both for control of a clearance gap between the plurality of fan blades and the nacelle.

Abstract: Methods for manufacturing dual phase soft magnetic components include combining a plurality of soft ferromagnetic particles with a plurality of paramagnetic particles to form a component structure, wherein the plurality of soft ferromagnetic particles each comprise an electrically insulative coating, and, heat treating the component structure to consolidate the plurality of soft ferromagnetic particles with the plurality of paramagnetic particles.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for a variable bleed valve assembly. An example variable bleed valve assembly a variable bleed valve (VBV) door corresponding to a bleed port and a first unison ring, the VBV door coupled to the first unison ring, the first unison ring to move in a circumferential direction between a first position and a second position causing the VBV door to move between the first position and the second position.

Abstract: Methods, apparatus, systems, and articles of manufacture to provide damping of an airfoil are disclosed. An example airfoil is disposed in a flow path, the airfoil including a shell defining an exterior surface of the airfoil and forming a cavity in an interior surface of the airfoil, and a lattice damper disposed in the cavity, the lattice damper to reduce vibrational loads exerted on the airfoil.

Abstract: Airfoil vibration damping apparatus are disclosed. An example apparatus includes a metallic airfoil including a cavity, and a dilatant material disposed in the cavity to dampen vibrations of the metallic airfoil.

Abstract: A system for an outlet guide vane assembly and method of assembly thereof are provided herein. The outlet guide vane assembly generally includes a composite outlet guide vane that includes a monolithic body extending in an axial direction from a base to a top, as well as an anchor bracket. At least one of the base and the top includes a bulbous profile having a thickness in a radial direction that is greater than a thickness of the monolithic body in the radial direction, where the radial direction is orthogonal to the axial direction. The anchor bracket generally includes an anchor base, an engagement slot, and at least one side structure defining the engagement slot.

Abstract: Methods, apparatus, systems, and articles of manufacture for deicing fan blades are disclosed. An example apparatus to de-ice a fan blade includes a fan cone including a cavity to hold pressurized hot air, the fan cone including a fan disk in the cavity, the fan disk coupled to the fan blade, and a dovetail seal coupled to the fan disk, the dovetail seal including at least one first hole, wherein the at least one first hole corresponds to at least one second hole in a root of the fan blade.

Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane, and an edge guard attached thereto. The edge guard may include a heating conduit disposed within at least a portion of the edge guard. An anti-icing system for a plurality of fan blades or outlet guide vanes may include a fluid supply pathway configured to supply heating fluid to respective ones of a plurality of heating conduits within the edge guards attached to respective ones of a plurality of fan blades and/or to a plurality of outlet guide vanes. The heating fluid may include bleed air from a core air flowpath. A method of inhibiting icing on an airfoil may include flowing a heating fluid into a heating conduit disposed within an edge guard attached to the airfoil and heating the edge guard with the heating fluid.

Abstract: Blades including integrated damping structures are disclosed herein. An airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis comprising an airfoil body including a first face, a second face and a recessed portion formed in the second face, and an airfoil cap having a first surface, the airfoil cap disposed within the recessed portion, the first surface substantially flush with the second face.

Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane formed of a first material, and an edge guard disposed about an edge of the fan blade. The edge guard may include a matrix composite that has a toughness that is greater than a toughness of the first material. The airfoil may include a fan blade or an outlet guide vane. The first material of the airfoil may include a metal alloy and/or a matrix composite. A method of manufacturing an airfoil for a fan section of a turbine engine may include manufacturing an edge guard, attaching the edge guard to the airfoil.

Abstract: An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane, and an edge guard attached thereto. The edge guard may include a heating conduit disposed within at least a portion of the edge guard. An anti-icing system for a plurality of fan blades or outlet guide vanes may include a fluid supply pathway configured to supply heating fluid to respective ones of a plurality of heating conduits within the edge guards attached to respective ones of a plurality of fan blades and/or to a plurality of outlet guide vanes. The heating fluid may include bleed air from a core air flowpath. A method of inhibiting icing on an airfoil may include flowing a heating fluid into a heating conduit disposed within an edge guard attached to the airfoil and heating the edge guard with the heating fluid.

Abstract: A ceramic matrix composite (CMC) component and method of fabrication including a plurality of counterflow elongated functional features. The CMC component includes a plurality of longitudinally extending ceramic matrix composite plies forming a densified body and a plurality of elongated functional features formed therein the densified body. Each of the plurality of functional features is configured longitudinally extending and in alignment with the plurality of ceramic matrix composite plies. Each of the plurality of elongated functional features includes an inlet configured in cross-ply configuration. The plurality of elongated functional features are configured to provide a flow of fluid from a fluid source to an exterior of the ceramic matrix composite component. The plurality of functional features are configured in alternating flow configuration.

Abstract: An industrial asset item definition data store may contain at least one electronic record defining the industrial asset item. An automated support structure creation platform may include a support structure optimization computer processor. The automated support structure optimization computer processor may be adapted to automatically create support structure geometry data associated with an additive printing process for the industrial asset item. The creation may be performed via an iterative loop between a build process simulation engine and a topology optimization engine.

Abstract: A method, medium, and system to receive a specification defining a model of a part to be produced by an additive manufacturing (AM) process; execute an AM simulation on the model of the part to determine a prediction of thermal distortions to the part; execute a topology optimization (TO) to create TO supports that counteract the predicted thermal distortions; generate at least one rule-based support based on a geometry of the part to interface with the part at one or more regions other than the TO supports; combining the TO supports and the at least one rule-based support to generate a set of hybrid supports; save a record of the set of hybrid supports; and transmit the record of the set of hybrid supports to an AM controller to control an AM system to generate a support structure for an AM production of the part.

Abstract: A nested lattice structure for use in a damping system for a turbine blade includes a first lattice structure including: a first outer passage including a hollow interior; a second outer passage including a hollow interior; and an outer node including a hollow interior and forming an intersection of the first outer passage and the second outer passage. The nested lattice structure includes a second lattice structure nested within the hollow interior of the first lattice structure. The second lattice structure includes: a first inner passage; a second inner passage; and an inner node forming an intersection of the first inner passage and the second inner passage. Each of the first inner passage, the second inner passage, and the inner node are nested within the respective first outer passage, the second outer passage, and the outer node.

Abstract: A method and system to receive a specification defining a model of a part to be produced by an additive manufacturing (AM) process; define a design space to enclose the part and a support structure for the part, the support structure to support the part and printed with the part during the AM process; execute an iterative topology optimization(TO) based at least in part on the specification for the part and the defined design space, to generate a TO support structure that counteracts predicted gravity-based distortions during the AM process; save a record of the generated TO support structure; and transmit the record of the TO support structure to an AM controller, the AM controller to control an AM system to generate an instance of the part and the TO support structure based on the record.

Abstract: A nested lattice structure 29 for use in a damping system includes a first lattice structure 26 including: a first outer passage 30 including a hollow interior 45; a second outer passage 32 including a hollow interior; and an outer node 42 including a hollow interior and forming an intersection of the first outer passage 30 and the second outer passage 32. The nested lattice structure 29 includes a second lattice structure 28 nested within the hollow interior of the first lattice structure 26 including: a first inner passage 44; a second inner passage 46; and an inner node 50 forming an intersection of the first inner passage 44 and the second inner passage 46. Each of the first inner passage 44, the second inner passage 46 and the inner node 50 are nested within the respective first outer passage 30, the second outer passage 32 and the outer node 42.