Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.

Abstract: A system and method for automated laser ablation includes an end effector for performing laser ablation at a location with restricted access. The systems and methods of the present disclosure specifically provide for a miniature laser end effector which may be inserted through a port or bore in order to ablate the surface of an internal component of a complex assembly. In several embodiments of the present subject matter, the end effector is mounted on a machine and coupled to a laser system.

Abstract: A method for repairing composite components includes installing a plug within a feature defined by a composite component, with the plug being formed from one or more neutral materials. Furthermore, the method includes infiltrating the composite component with an infiltrant to densify a repair region of the composite component, with the plug blocking a flow of the infiltrant into the feature. Moreover, after infiltrating the composite component, the method includes removing the plug from the feature.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.

Abstract: A method for producing a component layer-by-layer include the steps of: depositing a layer of particulate material having a first area over a build platform; applying a radiant-energy-curable binder to the layer so that a selected portion of the first area is uniformly coated with binder; selectively curing a second area of the layer smaller than the selected portion of first area, using an application of radiant energy in a specific pattern that defines the geometry of a cross-sectional layer of the component; and repeating the steps of depositing, applying, and curing for a plurality of layers until the component is complete.

Abstract: In one aspect, a method for performing in situ repairs of internal components of a gas turbine engine may generally include inserting a repair tool within an interior of the gas turbine engine such that a tip end of the repair tool is positioned within the gas turbine engine and an exterior end is positioned outside the gas turbine engine. The method may also include positioning the tip end of the repair tool adjacent to a defect of an internal component, wherein the defect defines a fillable volume along a portion of the internal component. In addition, the method may include intermixing two or more constituents of a repair agent within the repair tool at a mixing location defined within the gas turbine engine, and expelling the repair agent from the tip end such that the fillable volume is at least partially filled with the repair agent.

Abstract: A method for repairing composite components includes positioning one or more repair fiber plies relative to a repair interface of a composite component such that a butt joint is formed at the repair interface between the one or more repair fiber plies and the composite component. Furthermore, the method includes forming a cavity within the composite component such that the cavity extends through the repair interface. Additionally, the method includes installing a support member within the cavity. In this respect, the support member extends across the butt joint such that a first portion of the support member is positioned within the composite component and a second portion of the support member is positioned within the one or more repair fiber plies.

Abstract: Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

Abstract: A system and method for automated laser ablation includes an end effector for performing laser ablation at a location with restricted access. The systems and methods of the present disclosure specifically provide for a miniature laser end effector which may be inserted through a port or bore in order to ablate the surface of an internal component of a complex assembly. In several embodiments of the present subject matter, the end effector is mounted on a machine and coupled to a laser system.

Abstract: A system for forming features within composite components includes a tubular electrode extending along a longitudinal direction from a proximal end to a distal end. The distal end is, in turn, configured to be positioned relative to a machining surface of the composite component such that a spark gap is defined between the distal end and the machining surface. Furthermore, the tubular electrode further extends in a radial direction between an inner surface and an outer surface, with the inner surface defining a central passage configured to supply a dielectric fluid to the machining surface. The outer surface of the tubular electrode includes at least one a channel defined therein or a non-circular cross-sectional shape.

Abstract: Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

Abstract: A method for repairing composite components includes positioning repair material within a repair region of a composite component formed of a composite material. Furthermore, the method includes heating the repair region to a first temperature. Additionally, the method includes heating a remaining portion of the composite component to a second temperature. Moreover, the method includes melt infiltrating the repair region with an infiltrant to densify the repair material. The first temperature is at or above a melting point of the infiltrant and the second temperature is less than the melting point.

Abstract: A system and method for automated laser ablation includes an end effector for performing laser ablation at a location with restricted access. The systems and methods of the present disclosure specifically provide for a miniature laser end effector which may be inserted through a port or bore in order to ablate the surface of an internal component of a complex assembly. In several embodiments of the present subject matter, the end effector is mounted on an automated machine and coupled to a laser system.

Abstract: A method for repairing composite components includes positioning repair material within a repair region of a composite component formed of a composite material. Furthermore, the method includes filling a feature defined by the composite component with a filler material, with the filler material being a precursor to the composite material. Additionally, after filling the feature with the filler material, the method includes infiltrating the composite component with an infiltrant to densify the repair region and the filler material such that the feature is filled with new material.

Abstract: A method for repairing composite components includes installing a plug within a feature defined by a composite component, with the plug being formed from one or more neutral materials. Furthermore, the method includes infiltrating the composite component with an infiltrant to densify a repair region of the composite component, with the plug blocking a flow of the infiltrant into the feature. Moreover, after infiltrating the composite component, the method includes removing the plug from the feature.

Abstract: Methods provided for remotely stopping a crack in a component of a gas turbine engine are provided, along with methods of remotely cleaning a surface area of a component of a gas turbine engine. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; and drilling a hole into the base of the defect. An integrated repair interface is also provided.

Abstract: A robotic arm assembly includes a robotic arm, a base, and a utility member, the robotic arm extending between a root end attached to the base and a distal end including the utility member. A method for controlling the robotic arm assembly includes: determining a position of the base, the root end, or both relative to the environment; determining a task position and orientation for the utility member within the environment; determining a three-dimensional constraint of the environment; and determining a path for the robotic arm through the environment based on each of the position of the base, the root end, or both relative to the environment, the task position and orientation for the utility member within the environment, and the three-dimensional constraint of the environment.

Abstract: In one aspect, a method for performing in situ repairs of internal components of a gas turbine engine may generally include inserting a repair tool within an interior of the gas turbine engine such that a tip end of the repair tool is positioned within the gas turbine engine and an exterior end is positioned outside the gas turbine engine. The method may also include positioning the tip end of the repair tool adjacent to a defect of an internal component, wherein the defect defines a fillable volume along a portion of the internal component. In addition, the method may include intermixing two or more constituents of a repair agent within the repair tool at a mixing location defined within the gas turbine engine, and expelling the repair agent from the tip end such that the fillable volume is at least partially filled with the repair agent.

Abstract: CMC components having microchannels and methods for forming microchannels in CMC components are provided. For example, a method for forming microchannels in a CMC component comprises laying up a plurality of body plies for forming a body of the CMC component; laying up a microchannel ply on the plurality of body plies that has at least one void therein for forming at least one microchannel; laying up a cover ply on the microchannel ply to define an outer layer of the CMC component; and processing the laid up body plies, microchannel ply, and cover ply to form the CMC component. In another embodiment, the method comprises applying an additive matrix to the body plies to define at least one microchannel. In still other embodiments, the method comprises machining at least one microchannel in the plurality of body plies.