Abstract: A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order. A fan defining a fan axis and comprising a plurality of fan blades is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.

Abstract: A method includes: receiving a query from a computing device accessed by a recipient; accessing an identifier, associated with an advertisement card, including a pointer to an electronic document associated with the advertisement card and a recipient code associated with the recipient; accessing a set of recipient profiles associated with target recipients of a set of advertisement cards.

Abstract: A method includes: receiving a query from a computing device accessed by a recipient; accessing an identifier, associated with an advertisement card, including a pointer to an electronic document associated with the advertisement card and a recipient code associated with the recipient; accessing a set of recipient profiles associated with target recipients of a set of advertisement cards.

Abstract: One variation of a method includes, at a transceiver installed at a location: retrieving a device identifier of a device proximal the transceiver; rendering a QR code defining the device identifier and a location identifier associated with the location; in response to scanning of the QR code by a recipient via the device, triggering the device to navigate to a webpage including a prompt to enter a set of contact information; and linking the location identifier, the device identifier, and the set of contact information to a recipient profile. The method further includes: receiving a request for content associated with an advertising campaign for presenting to the recipient; selecting a subset of keywords, from a set of keywords defined for the advertising campaign, based on the location identifier; and generating a unique set of content based on the subset of keywords and the set of contact information.

Abstract: A seat assembly may include a seatback, a seat base, and/or a retractable cover assembly connected to the seat base. The retractable cover assembly may include a retractable cover that is selectively connectable to the seatback. The retractable cover assembly may include a housing mounted to an underside of the seat base. The seat base may be configured to rotate relative to the seatback between a seating position and a storage position. The retractable cover may be selectively connectable to the seatback at least when the seat base is in the seating position. The retractable cover may be selectively connectable to a second seatback of a second seat at least when the seat base is in the storage position.

Abstract: A vehicle having at least one cargo pod. The cargo pod may be rolled into and out of a cargo area of the vehicle. The cargo pod may include at least one battery. The battery may be selectively connectable to a vehicle power network. The battery may be disposed proximate a base of the cargo pod.

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: A method includes: receiving a query from a computing device accessed by a recipient; accessing an identifier, associated with an advertisement card, including a pointer to an electronic document associated with the advertisement card and a recipient code associated with the recipient; accessing a set of recipient profiles associated with target recipients of a set of advertisement cards.

Abstract: An airfoil assembly defines an axial direction, a radial direction, and a circumferential direction, and includes an airfoil and an outer band disposed on an outer end of the airfoil in the radial direction. The outer band includes an outer attachment structure configured to secure the outer band to an outer support structure on an outer side of the outer band.

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: A seat assembly may include a seatback frame, a primary carrier, an airflow duct, and a plurality of airflow outlets. The primary carrier may be connected to the seatback frame. The airflow duct may be defined at least partially by the primary carrier. The plurality of airflow outlets may extend through the primary carrier to an external surface and may be in fluid communication with the airflow duct.

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 seat assembly may include a seatback frame, a primary carrier, an airflow duct, and a plurality of airflow outlets. The primary carrier may be connected to the seatback frame. The airflow duct may be defined at least partially by the primary carrier. The plurality of airflow outlets may extend through the primary carrier to an external surface and may be in fluid communication with the airflow duct.

Abstract: A method for manufacturing a seat cushion receives data of a specific occupant. A seat cushion is designed from the occupant data. The seat cushion is provided with a cellular structure from the occupant data. Another method for manufacturing a seat cushion receives boundary conditions for a seat cushion. Applicable mechanical properties are determined for the boundary conditions of the seat cushion. Applicable thermal properties are determined for the boundary conditions of the seat cushion. A seat cushion is designed with a varying cellular structure to satisfy the applicable mechanical properties and the applicable thermal properties.

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: 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: Methods and systems are provided, which convert spent electrolyte from aluminum-air batteries into high purity alumina (HPA) and useful co-products such as fertilizer(s) and/or feed supplement(s). Aluminum tri-hydroxide (ATH) having potassium (K) and/or sodium (Na) impurities, e.g., from spent electrolyte, may be dissolved in strong acid to form an acidic ATH solution having pH<4. Consecutively, the acidic ATH solution may be neutralized to pH>4 to precipitate ATH while retaining dissolved K/Na in the neutralized solution. The dissolving and the neutralizing may then be repeated with the precipitated ATH until a specified purity level of the precipitated ATH is reached. Using appropriate bases to neutralize the acidic ATH solution, e.g., ammonia and/or choline, yields useful co-products such as ammonium nitrate (with nitric acid as the strong acid) and choline chloride (with hydrochloric acid as the strong acid), respectively.

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.