Abstract: Composite components having structurally reinforced contact interfaces are provided. In one example, the component can include an inner laminate formed of one or more inner plies having reinforcement fibers oriented along a reference direction within a matrix material. The component can also include an interface laminated positioned on the inner laminate along at least a portion of a contact surface of the component. The interface laminate is formed of one or more interface plies having reinforcement fibers oriented along a direction offset from the reference direction within a matrix material. Methods for fabricating such components are also provided.

Abstract: A system includes a robotic arm of a robotic device, an imaging device coupled to the robotic arm, and a processor configured to control movement of the robotic arm to move the imaging device along a preprogrammed measurement path of a transparency while prompting the imaging device to record images of localized portions of the transparency. The processor is configured to determine one or more localized transparency characteristics based on an analysis of the images of the localized portions.

Abstract: An apparatus and system for mechanically connecting components are provided. The apparatus includes a mechanical connecting joint that includes a first joint member formed of a material having a first coefficient of thermal expansion (CTE) value, the first joint member comprising a first sidewall, a second opposite sidewall, and a body extending therebetween. The mechanical connecting joint further includes a second joint member formed of a material having a second CTE value, the second CTE being less than the first CTE. The second joint member includes a first leg facing the first sidewall, a second leg facing the second sidewall, and a connecting member extending between the first leg and the second leg. A first gap is formed between the first joint member and the first leg and a second gap is formed between the first joint member and the second leg.

Abstract: Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine and an airfoil having a root and a tip. The root is coupled to the rotary structure and has a bulbous shape. The airfoil is formed from a plurality of composite plies, a portion of which defines at the root first and second end surfaces, which are in contact with the rotary structure and together define a chisel-shaped end of the root. In another embodiment, a rotor assembly comprises an outer rotor extending circumferentially about an axial centerline of a gas turbine engine and a composite outer rotor blade having a root and a tip. The blade root is coupled to the outer rotor and extends inward along a radial direction toward the axial centerline.

Abstract: A component for a gas turbine engine including a core and an outer enclosure. The core includes an exterior surface extending along a length between a first end and a second end and at least partially defines a cooling cavity on the exterior surface extending from the first end along at least a portion of the length. The cooling cavity is fluidly coupled to an air supply at the first end. The outer enclosure includes an outer surface. The outer enclosure is positioned outside the core and extends from the first end of the core along at least a portion of the length of the core and at least partially defines the cooling cavity.

Abstract: Airfoil assemblies for gas turbine engines are provided. For example, an airfoil assembly comprises an airfoil, an inner band defining an inner opening shaped complementary to an inner end of the airfoil, and an outer band defining an outer opening shaped complementary to an outer end of the airfoil. The airfoil inner end is received with the inner opening, and the airfoil outer end is received within the outer opening. A strut extends radially through an airfoil cavity. A first pad is defined at a first radial location within the cavity. A second pad is defined within the cavity at a second, different radial location. In some embodiments, the airfoil assembly inner band includes a first inner flange, through which the inner band is secured to a support structure, and the outer band includes a first outer flange, through which the outer band is secured to a support structure.

Abstract: Techniques are provided for protection of private keys in message signing based on elliptic curve cryptography. One method comprises obtaining a private key to generate a signature for a message; selecting a random integer as an internal private key in a predefined range based on an elliptic curve order; computing an internal public key as an elliptic curve point using a scalar multiply operation based on (i) the internal private key blinded using a random blinding value, (ii) an elliptic curve base point, and (iii) an inverse value for the random blinding value added to a result of the scalar multiply operation; generating a first signature portion based on the elliptic curve point; generating a second signature portion based on an inverse of the selected random integer generated from a message-dependent value and the first signature portion; and forming a signed message using the first and second signature portions.

Abstract: Combustor dome assemblies having combustor deflectors are provided. For example, a combustor dome assembly comprises a combustor dome defining an opening; a ceramic matrix composite (CMC) deflector positioned adjacent the combustor dome on an aft side of the assembly; a fuel-air mixer defining a groove about an outer perimeter thereof; and a seal plate including a key. The CMC deflector includes a cup extending forward through the opening in the combustor dome that defines one or more bayonets and a slot. The bayonets are received in the fuel-air mixer groove, and the seal plate key is received in the CMC deflector slot. In another embodiment, where the seal plate may be omitted, a spring is positioned between the fuel-air mixer and the CMC deflector to hold the CMC deflector in place with respect to the combustor dome. Methods of assembling combustor dome assemblies having CMC deflectors also are provided.

Abstract: Combustor dome assemblies having combustor deflectors are provided. For example, a combustor dome assembly comprises a combustor dome defining an opening; a ceramic matrix composite (CMC) deflector positioned adjacent the combustor dome on an aft side of the assembly; a fuel-air mixer defining a groove about an outer perimeter thereof; and a seal plate including a key. The CMC deflector includes a cup extending forward through the opening in the combustor dome that defines one or more bayonets and a slot. The bayonets are received in the fuel-air mixer groove, and the seal plate key is received in the CMC deflector slot. In another embodiment, where the seal plate may be omitted, a spring is positioned between the fuel-air mixer and the CMC deflector to hold the CMC deflector in place with respect to the combustor dome. Methods of assembling combustor dome assemblies having CMC deflectors also are provided.

Abstract: Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine, an airfoil having a root and a tip, and a pin extending through the root. The root is coupled to the rotary structure and has a bulbous shape, and the airfoil is formed from a plurality of composite plies. The pin defines both a planar first surface and a planar second surface on a pin body having a generally circular cross-section. Further, the pin includes a first end and a second end that contact the rotary structure. The first and second surfaces together form a point that is oriented toward the tip of the airfoil. In one embodiment, the rotary structure is an outer rotor of an interdigitated rotor assembly and the airfoil extends radially inward.

Abstract: A system architecture and related methods for controlling and/or modifying the content presented by a web site on one or more web pages. The system and methods enable an administrator or manager to efficiently update, revise, or otherwise maintain the content presented to a viewer on a web page, where such content may be subject to change or variation based on data related to the operation of a business for which the web site or web page is presented. The architecture, coupled with the methods for content or user interface representation and manipulation, enable a website administrator, manager, or other party to more efficiently control the content presented to a viewer of the site or page, where the viewer may be a customer or employee of a business.

Abstract: Turbine nozzle sections and airfoils having trailing edge segments are provided. In one embodiment, a turbine nozzle section comprises an inner band defining a pocket; an outer band defining an opening therethrough; and an airfoil radially extending from the inner band to the outer band and including pressure and suction sides. The airfoil has a body segment including a cavity and a plurality of ejector apertures defining a passageway from the cavity to an outer surface of the airfoil, and a trailing edge segment including an inner end and an outer end. The body segment defines a projection projecting inwardly from the suction side, and the trailing edge segment defines a notch opening toward the suction side. The projection is received within the notch. The inner end of the trailing edge segment is received within the inner band pocket, and the outer end is positioned within the outer band opening.

Abstract: A method of forming a composite component. The method includes laying up a plurality of composite plies to form a composite ply core. Another step of the method includes partially processing the composite ply core to form a green state core. The method further includes machining a cooling cavity on an exterior surface of the green state core. Additionally, the method includes inserting a filler material within the cooling cavity. A further step includes wrapping composite plies around the green state core and filler material to secure the filler material and form an outer enclosure. In one step, the method includes processing the green state core and outer enclosure to form the composite component.

Abstract: A component for a gas turbine engine including a core and an outer enclosure. The core includes an exterior surface extending along a length between a first end and a second end and at least partially defines a cooling cavity on the exterior surface extending from the first end along at least a portion of the length. The cooling cavity is fluidly coupled to an air supply at the first end. The outer enclosure includes an outer surface. The outer enclosure is positioned outside the core and extends from the first end of the core along at least a portion of the length of the core and at least partially defines the cooling cavity.

Abstract: A shroud assembly for a gas turbine engine including a plurality of rotor blades. The shroud assembly includes a plurality of tip shrouds, a plurality of flanges, and a plurality of first compressible elements. Each of the plurality of tip shrouds includes an outer band. Further each of the plurality of tip shrouds is coupled to one of the plurality of rotor blades at a tip end. Each of the plurality of flanges extends radially outward from one of the plurality of tip shrouds. Each of the plurality of first compressible elements is coupled to at least one of the plurality of flanges or one of the plurality of tip shrouds and oriented in a first circumferential direction. Further, each of the plurality of first compressible elements is oriented toward an adjacent tip shroud such that the tip shrouds mechanically engage to form a circumferential shroud.

Abstract: An expandable sleeve is used for providing support to an obturation member. The expandable sleeve and the obturation member form a hydraulic isolation in a casing. The expandable sleeve has preferably a small thickness or cross-section, which can allow for a large flow-through inner diameter after expansion. Also, the expandable sleeve is preferably short. Thus, mill-up operations that are performed when the expandable sleeve is no longer in use can be expedited or even eliminated in some cases.

Abstract: Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped complementary to each fairing outer end and has forward and aft ends. The inner and outer bands are each a single piece structure. Each fairing inner end is received within one of the plurality of inner pockets, and each fairing outer end is received within one of the plurality of outer pockets. Some embodiments also comprise an inner ring positioned against the inner band to close the inner pockets.

Abstract: Modular doors are disclosed. A disclosed example apparatus includes a door frame for insertion into a door opening of a support structure. The door frame includes a first side member to be parallel with a plane of the door opening when the door frame is inserted into the door opening, and a second side member angled from the first side member at a bend. The second side member has a first side to face the support structure when the door frame is inserted into the door opening. The second side member has a second side opposite the first side to face the door opening when the door frame is inserted into the door opening.

Abstract: Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine, an airfoil having a root and a tip, and a pin extending through the root. The root is coupled to the rotary structure and has a bulbous shape, and the airfoil is formed from a plurality of composite plies. The pin defines both a planar first surface and a planar second surface on a pin body having a generally circular cross-section. Further, the pin includes a first end and a second end that contact the rotary structure. The first and second surfaces together form a point that is oriented toward the tip of the airfoil. In one embodiment, the rotary structure is an outer rotor of an interdigitated rotor assembly and the airfoil extends radially inward.

Abstract: Rotor assemblies and methods for manufacturing airfoils for rotor assemblies are provided. For example, a rotor assembly comprises a rotary structure extending circumferentially about an axial centerline of a gas turbine engine and an airfoil having a root and a tip. The root is coupled to the rotary structure and has a bulbous shape. The airfoil is formed from a plurality of composite plies, a portion of which defines at the root first and second end surfaces, which are in contact with the rotary structure and together define a chisel-shaped end of the root. In another embodiment, a rotor assembly comprises an outer rotor extending circumferentially about an axial centerline of a gas turbine engine and a composite outer rotor blade having a root and a tip. The blade root is coupled to the outer rotor and extends inward along a radial direction toward the axial centerline.