Abstract: An apparatus a multiple layer structure having a sub-portion defining an impact zone, and having an inner composite fiber layer, an outer composite fiber layer overlying the inner composite fiber layer, and a woven glass layer, where the inner composite fiber layer, outer composite fiber layer, and the woven glass layer overly the impact zone.

Abstract: A method, medium, and system including determining a material property value to assign to each of the plurality of 3D volume elements, wherein the material property values assigned to the plurality of 3D volume elements are classified into a predetermined number of bins that correspond to a plurality of different additive manufacturing (AM) print parameter sets, generating a plurality of transfer functions to determine relationships between the material property values assigned to the plurality of 3D volume elements and a plurality of desired AM print parameter sets, automatically determining, based on the plurality of transfer functions, an assignment of one of the plurality of different AM print parameter sets to each of the plurality of 3D volume elements, and validating the determined assignments of the plurality of different AM print parameter sets for the plurality of 3D volume elements based on the plurality of transfer functions.

Abstract: An acoustic liner is provided. The acoustic liner includes a face sheet, a back sheet spaced from the face sheet, and a core layer defining a cellular structure disposed between the face sheet and the back sheet. The core layer includes a plurality of first resonant cells coupled to the back sheet. Each of the first resonant cells includes a first cell wall coupled to the back sheet along a first cell wall base edge, the first cell wall extending from the back sheet toward the face sheet, the first cell wall further coupled to the face sheet along a first cell wall top edge, wherein the first cell wall of each of the first resonant cells comprises a surface extension that extends from a surface of the first cell wall.

Abstract: A method of servicing a portion of a gas turbine engine includes inserting a rigid guide tube into an inspection port in a shroud of the gas turbine engine. The flexible guide tube is inserted into and through the rigid guide tube. The flexible guide tube is pre-shaped such that the flexible guide tube is biased towards a predetermined shape after being inserted through the rigid guide tube. A tool is pushed through the flexible guide tube such that the distal end of the tool moves out of and away from an end of the flexible guide tube. An area of interest of the gas turbine engine is then serviced with the tool.

Abstract: A combustor assembly for a gas turbine engine defining a radial direction and a circumferential direction includes a liner assembly at least partially defining a combustion chamber and including at least one liner formed of a ceramic matrix composite material and extending between a downstream end and an upstream end, the downstream end of the at least one liner defining an interface surface extending along the circumferential direction; and a seal member also formed of a ceramic matrix composite material and bonded to the interface surface of the at least one liner, the seal member defining a downstream surface for contacting an adjacent component to form a seal with the adjacent component.

Abstract: Cover plate connections for a hollow fan blade are disclosed. An example fan blade includes a hollow body including a surface defining an airfoil, the hollow body including an aperture extending through the surface, a cover plate, and at least one connection element to couple the cover plate to the surface such that the cover plate encloses the aperture.

Abstract: A rake arm assembly mountable to a build table having an upper surface and an opposite lower surface is provided. The rake arm assembly includes a rake arm body extending in a direction transverse to a working axis and positionable at the upper surface of the build table, a first guide rail mountable to the lower surface of the build table and extending along the working axis, a first rake support member fixed to a first end of the rake arm body and movably supported on the first guide rail, a second rake support member fixed to an opposite second end of the rake arm body, and a guide pad fixed to a lower surface of the second rake support member and positionable at the lower surface of the build table.

Abstract: Part-span shrouds for pitch controlled aircrafts are disclosed herein. An example apparatus includes a first portion extending from a first airfoil, the first portion including a first surface, the first surface being convex, a second portion extending from a second airfoil towards the first airfoil, the second portion including a second surface the first airfoil circumferentially adjacent to the second airfoil, the second surface being concave, and an interface formed by the first surface and the second surface, the interface reacting circumferential loads between the first airfoil and the second airfoil.

Abstract: The present disclosure relates to extraction of probe motion estimates from acquired ultrasound image frames. Such image-extracted probe motion data can be used alone or in combination with sensed motion data, such as acquired using an inertial measurement unit (IMU). In certain implementations, the image-extracted probe motion can be used to provide or maintain anatomic context in a sequence of images or to provide guidance to a user.

Abstract: A gas turbine engine includes a compressor section with a compressor rotor shaft assembly including a plurality of compressor rotors longitudinally spaced apart from each other via respective ones of a plurality of shaft sections of a rotor shaft, each compressor rotor of the plurality of compressor rotors having a plurality of rotor vanes extending radially outward therefrom and being circumferentially spaced about the compressor rotor. A stator shroud assembly has a stator shroud casing surrounding the compressor rotor shaft assembly, a compressor flow passage being defined between the compressor rotor shaft assembly and the stator shroud casing. A pressurized air source generates a flow of pressurized air to be provided to the compressor section, and a plurality of pressurized airflow nozzles are connected with the pressurized air source and provide the flow of pressurized air into the compressor flow passage to cause the compressor rotor shaft assembly to rotate.

Abstract: A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.

Abstract: A method of fabricating a component is provided. The method includes depositing particles onto a build platform. The method also includes distributing the particles to form a build layer. The method further includes operating a consolidation device to consolidate a first plurality of particles along a scan path to form a component. The component includes a top surface spaced apart from the build platform and an outer surface. The outer surface extends between the build platform and the top surface, and at least a portion of the outer surface faces a substantially particle-free region of the build platform.

Abstract: A system and method of using a tool assembly is provided. The system includes a body, a first camera and a second camera fixed to the body, and a controller. The controller is configured to receive data indicative of images of a reference feature from the first camera, determine data indicative of a first spatial position of the first camera based at least in part on the received data indicative of the images of the reference feature, and determine data indicative of a second spatial position of the second camera based on the first spatial position, a known spatial relationship between the first location and the second location, or both. Further, the controller may be configured to receive data indicative of images of a target feature using the second camera, derive dimensions of the target feature based on the images, and generate a three-dimensional representation of the target feature.

Abstract: A joined part comprises a first portion and a second portion. The first portion comprises a guide slot at least partially defined by a porous structure. A joint material is disposed within the porous structure. The second portion is disposed within the guide slot and contacts the porous structure and the joint material disposed therein to form an interfacial joint between the first portion and the second portion. A method of manufacturing the joined part includes disposing a joint material into a porous structure of a guide slot of a first portion, inserting a second portion into the guide slot, and contacting the porous structure and the joint material disposed therein to form an interfacial joint between the first portion and the second portion.

Abstract: A system for melting, sintering, or heat treating a material is provided. The system includes a cathode, an anode, and a focus coil assembly having a quadrupole magnet. The quadrupole magnet includes four poles and a yoke. The four poles are spaced apart and surround a beam cavity. Each of the four poles includes a pole face proximate the beam cavity and an end opposite the pole face. The first and third poles are aligned along an x-axis and configured to have a first magnetic polarity at their respective pole faces and a second magnetic polarity opposite the first magnetic polarity at their respective ends. The second and fourth poles are aligned along a y-axis and configured to have the second magnetic polarity at their respective pole faces and the first magnetic polarity at their respective ends. The yoke surrounds the poles and is coupled to the poles.

Abstract: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.

Abstract: Core-shell microparticles, along with methods of their fabrication and use, are provided. The core-shell microparticles may include a core comprising a first metallic material having a first chromium content and a shell surrounding the core and comprising a second metallic material having a second chromium content that is less than the first chromium content. For example, the first chromium content may be 5% by weight or greater of elemental chromium within the first metallic material.

Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.

Abstract: A sealing system for sealing between components. The sealing system includes a first component, a second component, and a seal assembly including a seal member. The first component includes a first component surface, and the second component includes a second component surface. The second component surface is oriented in a direction transverse to the first contact surface. The seal member has a plurality of contact surfaces including a first contact surface and a second contact surface. The first contact surface is configured to contact the first component surface and to slide relative to the first component surface. The second contact surface is configured to contact the second component surface and to slide relative to the second component surface. The second contact surface is oriented in a direction transverse to the first contact surface.