Abstract: An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.

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: 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: A vehicle port door includes a housing and an interlocking linkage assembly. The interlocking linkage assembly is pivotably connected to the housing.

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: 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: A tool for expanding a liner in a wellbore includes a cone assembly that is moveable between a retracted position and an extended position. The tool also includes a jack assembly that is operable by fluid pressure to move the cone assembly from the retracted position to the extended position. The fluid pressure is also applied to expansion cup seals to generate axial load that urges the cone assembly to move through the expandable liner and radially expand of the expandable liner. A latch assembly axially fixes the liner while the cone assembly moves to the extended position. Once the cone assembly is fully moved to the extended position, the latch assembly releases the liner, allowing the cone assembly to move through the liner and radially expand the liner.

Abstract: A rotor blade for a gas turbine engine includes a structural member formed from a metallic material. The structural member, in turn, includes a base portion, a spar, and a tip cap, with the base portion at least partially forming a root of the rotor blade and a shank of the rotor blade. Furthermore, the structural member includes a fairing formed from a composite material. The fairing is, in turn, coupled to the structural member such that the fairing forms at least a portion of an airfoil of the rotor blade and a platform of the rotor blade. Additionally, the fairing including a first fairing panel and a second fairing panel in contact with the first fairing panel at a first split line and a second split line.

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: A string includes a pipe that is connected to an expansion mechanism and a retrieval tool that is connected to the pipe above the expansion mechanism. The retrieval tool includes a carrier that can selectively latch on an expandable liner and one or more actuators. The retrieval tool can ensure latching of the carrier while the expandable liner is above the Blow-out Preventer. The retrieval tool can prevent accidental latching of the carrier on the expandable liner during the expansion of the liner. By manipulating the pipe, the retrieval tool can force the carrier's release from the expandable liner.

Abstract: A rotor assembly for a gas turbine engine includes a shaft and first and second annular drum segments coupled to the shaft. Furthermore, the rotor assembly includes an annular flange positioned between the first and second annular drum segments along the axial centerline, with the annular flange coupled to the first and second annular outer drum segments. Additionally, the rotor assembly includes a blade having a shank section and an airfoil section. The shank section is, in turn, coupled to the annular flange such the airfoil section extends inward along the radial direction toward the axial centerline and into a hot gas path of the gas turbine engine.

Abstract: An inspection system for detecting optical defects in a transparency includes a first rounded array of first elongated light elements, and a second rounded array of second elongated light elements. The second rounded array is positionable radially outboard of the first rounded array. The inspection system further includes a light-element-moving system configured to radially translate at least the first elongated light elements. The inspection system also includes an image recording device positionable on a side of the transparency opposite the first and second rounded arrays and configured to record images of the transparency during radial translation of at least the first elongated light elements during backlighting of the transparency. The inspection system includes a processor configured to analyze the images recorded during radial translation of at least the first elongated light elements, and detect optical defects in the transparency based on analysis of the images.

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: Expansion and movement joints are disclosed. An example apparatus includes a collar having a first aperture extending therethrough to receive a conduit, and a guide to receive the collar, where the guide has a second aperture that defines an inner surface of the guide, and where the inner surface of the guide is larger than an outer surface of the collar to define a gap therebetween.

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: 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: A tool for expanding a liner in a wellbore includes a cone assembly that is moveable between a retracted position and an extended position. The tool also includes a jack assembly that is operable by fluid pressure to move the cone assembly from the retracted position to the extended position. The fluid pressure is also applied to expansion cup seals to generate axial load that urges the cone assembly to move through the expandable liner and radially expand of the expandable liner. A latch assembly axially fixes the liner while the cone assembly moves to the extended position. Once the cone assembly is fully moved to the extended position, the latch assembly releases the liner, allowing the cone assembly to move through the liner and radially expand the liner.

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 coolant reservoir tank includes a first compartment that is configured to receive and retain a first portion of a liquid coolant. The first compartment is configured to be in fluid communication with a first liquid cooling circuit. A second compartment is configured to receive and retain a second portion of the liquid coolant. The second compartment is configured to be in fluid communication with a second liquid cooling circuit. A dividing wall separates the first compartment from the second compartment. The coolant reservoir tank further includes a fill port.

Abstract: An inspection system for detecting optical defects in a transparency includes a first rounded array of first elongated light elements, and a second rounded array of second elongated light elements. The second rounded array is positionable radially outboard of the first rounded array. The inspection system further includes a light-element-moving system configured to radially translate at least the first elongated light elements. The inspection system also includes an image recording device positionable on a side of the transparency opposite the first and second rounded arrays and configured to record images of the transparency during radial translation of at least the first elongated light elements during backlighting of the transparency. The inspection system includes a processor configured to analyze the images recorded during radial translation of at least the first elongated light elements, and detect optical defects in the transparency based on analysis of the images.