Abstract: A method for coating a fiber tow includes moving a fiber tow across a wedge to separate the fiber tow into a plurality of sub-tows, and coating the plurality of sub-tows.

Abstract: A hollow vane assembly including an open body including an interior; at least one cover support structure formed in said open body proximate the interior; a cover brazed to the open body to form at least one flow passage; and the open body and the cover configured as two piece substantially symmetrical halves.

Abstract: A combustor panel is disclosed herein. The combustor panel includes a top side, a bottom side opposite the top side, a feature coupled to the top side and extending orthogonally away from the top side, the feature defining a first space on the bottom side beneath the feature, a first plurality of cooling holes extending in a first direction from the top side to the bottom side, a second plurality of cooling holes extending in a second direction from the top side to the bottom side, the second direction being rotated about 1° to about 60° counter-clockwise from the first direction, and a third plurality of cooling holes extending in a third direction from the top side to the bottom side, the third direction being about rotated 1° to about 60° clockwise from the first direction.

Abstract: A turbine engine including one or more conduits is disclosed herein. At least one conduit of the turbine engine includes a first end coupled to the turbine engine, a second end, and a body extending from the first end to the second end, the body including an interior surface and an exterior surface, wherein at least one of the interior surface or the exterior surface includes a protrusion configuration.

Abstract: A method for repairing a stator stage is disclosed herein. The method includes receiving a stator stage including a plurality of stator vanes disposed between an outer diameter and an inner diameter, analyzing the stator stage for defects, determining there is a first defect in a first segment of a the stator stage, the first segment including at least one of a first portion of the outer diameter, a first portion of the inner diameter, or a first stator vane, removing the first segment from the stator stage forming a void in the stator stage, manufacturing a second segment that is the same size as the first segment, attaching the second segment to the stator stage to fill the void, performing a blending process on the stator stage including the second segment to smooth the plurality of stator vanes including the second stator vane.

Abstract: A method of repairing a stator stage is disclosed herein. The method includes receiving a stator stage including a plurality of stator vanes disposed between an outer diameter and an inner diameter, analyzing the stator stage for defects, determining based on the analysis that there is a first defect on an edge of a first stator vane of the plurality of stator vanes, removing a portion of the first stator vane including the first defect to form a first scallop on the edge of the first stator vane, repairing the first stator vane including filling the first scallop to fill the first stator vane to its original size and shape creating a repaired portion, and performing a blending process to the stator stage including the first stator vane and the repaired portion to smooth the plurality of stator vanes.

Abstract: An inspection system for in-situ identification of defects associated with a component of an assembled engine is provided. The system includes an inspection device and a controller. The controller is configured to generate, via the inspection device, one or more first signals in proximity to the component; receive, via the inspection device, data associated with the one or more first signals; and apply an inspection process to the data to determine whether the component includes a defect.

Abstract: A method for repairing a component without further damaging the component is provided. A magnetic field is applied to the component via an induction coil thereby causing a temperature of the component to increase. Responsive to the component reaching a desired temperature, the component is repaired via a direct energy deposition process.

Abstract: An X-ray tomography sample changing hardware including a support bracket configured to attach to an X-ray tomography support; a mounting arm attached to the support bracket, the mounting arm having a beam, at least one slot formed in the beam, the at least one slot including a mouth configured to receive a sample stage; the sample stage including a body having an axis with an upper portion and a lower portion axially opposite the upper portion; the lower portion configured to mate with a receiver on a sample manipulator for an X-ray tomography machine; and multiple chambers formed in the body and aligned axially between the upper portion and the lower portion, each of the multiple chambers including a mounting feature configured to support a part within each of the multiple chambers.

Abstract: A component of an aero-propulsion apparatus, wherein the component includes a material and has a surface, and a thin film on the surface, wherein the thin film is configured to undergo a detectible change in properties when exposed to a temperature exceeding a threshold temperature. Methods are also disclosed.

Abstract: A hybrid shroud impeller including a hub having a first and a second axial end; the hub including an outer surface formed radially opposite a hub bore; a full blade extending radially from the outer surface; a splitter blade extending radially from the outer surface adjacent to the full blade; a bleed feature formed in a casing; a partial shroud integrally formed with a portion of the full blade and the splitter blade opposite the outer surface of the hub; a flow path formed between the outer surface of the hub, a shroud inner surface of the partial shroud and a blade surface of each of the full blade and the splitter blade; and the flow path extending from an inlet proximate the first axial end and an outlet proximate the second axial end; the partial shroud extends from the inlet to the bleed feature.

Abstract: A process for a laser plume interaction for a predictive defect model for multi-laser additive manufacturing of a part including executing computational fluid dynamics modeling of a gas flow in an additive manufacturing machine manufacturing chamber; approximating a laser plume relative to a melt pool on a powder bed disposed on a build plate within the manufacturing chamber; executing a space-time analysis to identify a laser plume interaction; creating a plume interaction zone map; feeding the plume interaction zone map prediction into a multi-laser defect model; and predicting defect location and density to accumulate lack-of-fusion risk as a function of part placement, orientation, and scan strategy.

Abstract: A process for uncertainty quantification for a predictive defect model for multi-laser additive manufacturing of a part including executing computational fluid dynamics modeling of a gas flow in an additive manufacturing machine manufacturing chamber; assigning a spatter particle size, velocity and direction relative to a melt pool on a powder bed disposed on a build plate within the manufacturing chamber; executing computational fluid dynamics post processing for spatter particle tracking; predicting a spatter particle landing pattern; feeding the spatter particle landing pattern prediction into a defect model; producing a layer thickness map, the layer thickness map configured to demonstrate a location of locally thicker layers on the part; and predicting defect location and density to accumulate lack-of-fusion risk as a function of part placement, orientation, and scan strategy.

Abstract: An analysis tool for multi-laser additive manufacturing including a build file module; a preprocessor in operative communication with the build file module; a prime module in operative communication with the preprocessor; and a defect code module in operative communication with the prime module.

Abstract: A system for determining rotor-dynamic orbit information including an engine case supporting at least one engine stage, each at least one engine stage including a rotor having blades; at least one blade tip sensor operatively coupled to the engine case and in operative communication with the blades; at least one compensation sensor in operative communication with the at least one blade tip sensor; and an orbit controller in operative communication with the at least one blade tip sensor and the at least one compensation sensor.

Abstract: A layout for asymmetric trip strips including a flow passage having a lower wall and an upper wall opposite the lower wall, each of the lower wall and the upper wall including an inner surface, the flow passage having a passage inlet and a length L and a diameter d; multiple skewed trip strips extending from at least one inner surface of the lower wall or the upper wall; and at least one periodic reflection of the skewed trip strips along the flow passage downstream of the passage inlet at a frequency with a length-to-diameter ratio of L/d?20.

Abstract: A vortex restart structure including a flow passage having a first wall and a second wall opposite the first wall, each of the first wall and the second wall including a parting surface; multiple flow turbulators extending from at least one parting surface of the first wall or the second wall; and at least one vortex restart structure extending from at least one parting surface of the first wall or the second wall, wherein the at least one vortex restart structure extends from the parting surface into the flow passage beyond the multiple flow turbulators.

Abstract: A masking apparatus for masking a part during coating and comprising at least two sintered pieces of a mask material. The pieces have an assembled condition forming a compartment shaped to accommodate an airfoil of the part. The pieces have an average overall composition of: nickel as a largest by-weight constituent; aluminum as a second largest by-weight constituent; and chromium as a third largest by-weight constituent.

Abstract: A method for molding a ceramic core includes introducing a slurry to a mold and vibrating the mold. The slurry has: silica-containing particles; polymer fiber; and matrix precursor. The mold has an outer tool and a liner held within the outer tool. The vibrating comprises operating a plurality of vibration transducers distributed along the mold.

Abstract: An assembly for mounting an auxiliary component to an engine case for a gas turbine engine includes a support bracket and a locator comprising a fusible guide pin extending at least partially into a first aperture disposed in the support bracket, and a catcher pin extending at least partially into a second aperture disposed in the support bracket. The fusible guide pin is configured to fracture to absorb energy while the catcher pin limits system displacement during and post an overload event, thus reducing the energy transmitted to the auxiliary component (e.g., a gearbox housing).