Abstract: Tolerances of full hoop or segmented ceramic matrix composite (CMC) parts may be controlled by utilizing machining methods earlier in the fabrication process on an involute stack of plies. In an embodiment, a plurality of fabric plies having a tackifier are stacked in a partially overlapping manner to form an involute stack of fabric plies forming a hoop or portion thereof, which may have a cylindrical or conical axial profile. The inner diameter (ID) and outer diameter (OD) surfaces of the involute stack of fabric plies are then machined to remove lap joint discontinuities and/or other uneven surfaces. The machined ID and OD surfaces are then overwrapped with an inner mold layer (IML) overwrap and outer mold layer (OML) overwrap formed of one or more plies of fabric to form a preform, which may then be densified.

Abstract: An electrochemical machining electrode assembly has electrodes having electrical connections. Insulation electrically insulates the electrodes from each other. Fluid passageways are each at least partially bounded by an associated one of the electrodes and have a respective outlet. A fluid plenum is positioned to introduce an electrolyte flow to the fluid passageways.

Abstract: A ceramic-containing material, comprising one or more plies arranged in a structure having at least one internal cavity therein, at least one ply within the at least one internal cavity having at least one turbulence inducing feature, the at least one turbulence inducing feature comprises at least one fiber protruding from the surface of the at least one internal cavity.

Abstract: A retaining split ring stack for axial retention of a ceramic matric composite (CMC) gas path component includes an outer-most split ring and an inner-most split ring. The outer-most split ring is configured for retention within a diametric groove within a support structure, and includes an inner diameter with a plurality of scallops. The inner-most split ring has a smaller outer diameter, an upstream surface configured for contact with the CMC gas path component, and a downstream surface including a plurality of tabs extending therefrom and configured for engagement with respective scallops of the outer-most split ring. This configuration permits radial movement from the cooler outer-most split ring with the support structure. The inner-most split ring can then be sized to mitigate the radial deflection and hoop stress within the CMC gas path component.

Abstract: A ceramic matrix composite (CMC) component is described having a coating on a non-gaspath surface. The machinable coating contains CaAl4O7, also known as grossite or Ca-dialuminate. To enhance durability and the ability to provide a smooth surface, the machinable coating can have a relatively low-porosity, for example, a porosity of ? 25 vol. %. Also, to improve CTE match with SiC-containing materials, the machinable coating can have a relatively high CaAl4O7 content, for example ? 75 vol. % CaAl4O7. The thickness of the CaAl4O7 machinable coating can be, for example, up to about 2,500 ?m.

Abstract: An example system for analyzing a component includes a radiation source configured to transmit an input radiation beam towards a component, at least a portion of the input radiation beam passing through the component as an output beam pattern; a radiation detector configured to detect the output beam pattern; and a beam adjustment device disposed between the radiation source and the component and configured to modify a radiation intensity profile of the input radiation beam, wherein the beam adjustment device has an adjustable radiation transparency.

Abstract: A housing for internal components of an optical probe is provided. The housing includes a housing body including an outer surface and an inner surface opposite the outer surface. The housing body is elongated along a center longitudinal axis from a proximal end to a distal end. The inner surface defines and annularly surrounds a cavity that is open at the proximal end and closed at the distal end. The housing includes a purge channel that includes a gas inlet and a gas outlet. The purge channel extends axially relative to the center longitudinal axis from the gas inlet to the gas outlet. The purge channel is formed between the outer surface and the inner surface of the housing body. The gas outlet is located distally from the gas inlet and through the inner surface of the housing body. The gas outlet directs gas into the cavity toward the distal end.

Abstract: Aircraft electric motors include a rotor having a plurality of magnet segments arranged on a frame of the rotor, the rotor defining an internal cavity radially inward from the plurality of magnet segments, an output shaft operably coupled to the rotor, and a stator having a support structure and at least one winding wrapped about a plurality of stator teeth. The stator teeth include inner teeth arranged on a radially inward side of the support structure and outer teeth arranged on a radially outward side of the support structure and the stator is arranged within the internal cavity of the rotor. At least one of the inner teeth, the outer teeth, or the support structure is formed from a non-magnetic material with embedded magnetic wires.

Abstract: A method for processing a seal for a gas turbine engine includes providing a carbon fiber preform, densifying the carbon fiber preform with a carbon matrix to form a carbon/carbon composite ring, and forming a seal by cutting the carbon/carbon composite ring to form at least one seam at which opposed ends of the carbon/carbon composite ring meet.

Abstract: An example method includes obtaining one or more three dimensional computer models that model geometric and material properties of a component, and model beam properties of a beam of radiation to be applied to the component; utilizing the one or more three dimensional computer models to obtain simulated radiation imaging data, which includes simulated elastic scattering data, resulting from a simulated application of the beam having the beam properties on a plurality of discretized samples of the component, and which accounts for sequential interactions of rays of the beam with multiple ones of the plurality of discretized samples; obtaining actual radiation imaging data, which includes actual elastic scattering data, of an output beam pattern caused by application of a non-simulated beam of radiation having the beam properties to the component; and performing at least one of: determining whether an anomaly exists in a crystalline structure of the component based a comparison of the simulated elastic scatteri

Abstract: A pylon for an aircraft projects spanwise along a span line out from a base end towards a first mounting station and a second mounting station. The first mounting station is disposed a first spanwise distance along the span line from the base end. The second mounting station is disposed a second spanwise distance along the span line from the base end. The second spanwise distance is greater than the first spanwise distance. The pylon is configurable to mount to: a portion of a first propulsion system at the first mounting station, wherein the first propulsion system comprises a first propulsor rotor with a first diameter; or a portion of a second propulsion system at the second mounting station, wherein the second propulsion system comprises a second propulsor rotor with a second diameter that is greater than the first diameter.

Abstract: A method includes utilizing a learning model, which has been trained to mimic the nominal control outputs of a model predictive control, to generate a nominal control output for a system that is an aircraft system having one or more system constraints. The method also includes, based on the nominal control output, satisfying each of one or more system constraints, implementing the nominal control output; and, based on the nominal control output not satisfying one of the one or more system constraints, utilizing a safety stability filter that includes a control barrier function (CBF) portion and a control Lyapunov function (CLF) portion to modify the nominal control output and obtain a modified control output, and implementing the modified control output in the aircraft system. A system is also disclosed.

Abstract: A system for forming a braided preform includes a mandrel having a rotational axis, the mandrel being translatable along and rotatable about the rotational axis, a radial braider for winding fibers onto the mandrel to form a braided layer, an applicator for applying a polymer binder to the braided layer while mounted on the mandrel, and a debulking tool for debulking the braided layer while mounted on the mandrel.

Abstract: A gas turbine engine is provided having an axial centerline, a compressor section, a turbine section, and a combustor section. The turbine section has a turbine first vane assembly that includes an annular first vane inner radial support. The combustor section has an outer casing, an annular combustor, and a unitary inner diffuser structure. The annular combustor has an inner radial flange. The unitary inner diffuser structure includes a compressor discharge, an inner diffuser case, and a tangential onboard injector (TOBI) inseparably attached to one another. The unitary inner diffuser structure further includes an outer radial flange and a TOBI connection flange. The annular FV inner radial support, the combustor inner radial flange, and the TOBI connection flange are secured to one another.

Abstract: A method of making a ceramic matrix composite component includes arranging a plurality of ceramic-based reinforcements in an array, applying an interface coating to the ceramic-based reinforcements, applying a layer of ceramic-based matrix over the interface coating, and applying a secondary interface coating such that the secondary interface coating is separate and distinct from the layer of ceramic-based matrix. A ceramic matrix composite component is also disclosed.

Abstract: Methods are used by a thermal acoustic imaging (TAI) inspection system to identify potential defects within a component scanned, such as an engine fan blade. The inspection system generates a TAI scan having a plurality of frames. Indications are identified in at least one frame of the plurality of frames. An extractor model is applied to the plurality of frames to extract a plurality of spatial features corresponding to the indication. The plurality of spatial features is concatenated from each frame to generate a time series value of the values for the features. The plurality of spatial features is combined into multiple sequence data. The multiple sequence data includes a plurality of temporal features. The multiple sequence data is provided to train a neural network model to predict defects. For trained neural network models, the multiple sequence data is used to predict if the indication is a defect.

Abstract: A user interface for a lightweight viewer may include, among other things, a viewing window operable to display geometry established by one or more of geometric objects of a tessellated model and a plurality of notification objects of the tessellated model. The notification objects include a first statement object and an acknowledgement object linked to the first statement object. The first statement object is operable to establish a first notification screen that blocks display of the geometry in the viewing window prior to selection of the acknowledgement object but permits display of the geometry in response to selection of the acknowledgement object. A method of establishing a tessellated model is also disclosed.

Abstract: An airfoil includes an airfoil wall that has a wishbone-shaped fiber layup structure. The structure includes two arms that merge into a single leg. The single leg includes fiber tows from each of the arms that are interwoven. The single leg forms at least a portion of the trailing edge of the airfoil wall. Each of the arms includes a first section that is distal from the single leg and a second section that is proximal to the single leg. The first section defines a first thickness, the second section defines a second thickness that is greater than the first thickness, and the single leg defines a third thickness that is greater than the second thickness.

Abstract: A method for determining wear mode and surface characteristics of wear on a gas turbine engine component, comprising the steps of obtaining images of a wear scar on a gas turbine engine component; feeding the images to an image model; identifying geometry of the wear scar from the images and the image model; identifying a wear mode from the geometry of the wear scar; obtaining surface characterization of the wear scar; analyzing the surface characterization to identify tribo-layer details; identifying constituents of the tribo-layer from the tribo-layer details; and characterizing wear on the gas turbine engine component based upon the wear mode and the constituents of the tribo-layer. A system is also disclosed.

Abstract: A system includes a laser drilling apparatus having a laser to drill into coating layers of a component. The component includes cooling holes through a substrate and an existing layer. The existing coating layer is stripped from the component. The locations of the cooling holes are mapped using a coordinate measurement machine that generates a macro file of the locations. The macro file is loaded onto the laser drilling apparatus. A new coating layer is applied that covers the cooling holes. The laser drilling apparatus collects data at the locations mapped to the macro file of the component having a new coating layer. A modification is made to the locations of the at least one cooling holes based on a parameter in the collected data. The laser drilling apparatus drills using the laser at the modified locations into the new coating layer.