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 gas turbine engine is provided. The gas turbine engine includes a case having a wall that provides a manifold cavity, the wall including an aperture and a bore; a tube assembly with a flange that provides a fluid passage aligned with the aperture; a mixing feature arranged in the manifold cavity and including a plate with a hole; and an insert having a body and a head, the body received in the hole and sealed in the bore, the head capturing the plate against the wall. The mixing feature is configured to divert a flow of cooling fluid in at least a counterclockwise direction improving jet mixing and placement of the cooling fluid.

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 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: 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 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: 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: 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 fuel nozzle guide assembly for a gas turbine engine is provided. The fuel nozzle guide assembly includes a housing; a tube arranged in the housing and defining a portion of a first fluid passage therein, the first fluid passage configured to include a first fluid, wherein a second fluid passage is defined, in part, between an exterior surface of the tube and an interior surface of the housing, the second fluid passage configured to include a second fluid; an air inflow tube, the air inflow tube defining a central air passage and configured to include a third fluid; an air inflow assembly defining a third fluid passage and configured to include a fourth fluid; and a nozzle outlet configured to receive each of the first fluid, the second fluid, the third fluid, and the fourth fluid to cause mixing thereof.

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 stator vane assembly is disclosed herein. The stator vane assembly includes a stator box having a top side and a bottom side, a vane coupled to the top side of the stator box, and an integral seal coupled to the bottom side of the stator box, the integral seal extending away from the stator box and forming a tortuous path to prevent airflow below the stator box.

Abstract: A repair method can comprise: machining a wall of the case to remove a damaged portion of the wall, the case including a metal alloy, the case originally formed by casting; arc welding an intermediate layer of a first material to a base surface formed from the machining to form a first portion of a repaired wall; and building up, via direct energy deposition, a remainder of the repaired wall with a second material.

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: A bowed-rotor-resistant low shaft of a gas turbine engine is provided. The bowed-rotor-resistant low shaft includes a low shaft and a thermal barrier coating applied to at least a lengthwise portion of an outside diameter of the low shaft, wherein the thermal barrier coating reduces bowing of the low shaft due to latent heating effects from the gas turbine engine.

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: 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 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.