Abstract: A selective oxide-forming alloy, a coating formed from, and a machine component including the coating are provided. The selective oxide-forming alloy includes between atomic percent and 26 atomic percent silicon (Si), between 21 atomic percent and 27 atomic percent titanium (Ti), between 30 atomic percent and 39 atomic percent aluminum (Al), between 2 atomic percent and 10 atomic percent hafnium (Hf), and a balance of niobium (Nb).

Abstract: In an embodiment, a heat exchanger includes a monolithic body that includes a first substrate, a second substrate, a third substrate, and a plurality of partial height fins. The second substrate is arranged parallel to and spaced from the first substrate, thereby defining a first fluid flow path. The third substrate is arranged parallel to and spaced from the second substrate opposite the first substrate, thereby defining a second fluid flow path. The plurality of partial height fins extend from one of the second substrate and the third substrate toward the other of the second substrate or the third substrate, wherein a terminal edge of each partial height fin is at least partially spaced from the other of the second substrate or the third substrate.

Abstract: The subject matter of the present disclosure generally relates to techniques for neuromodulation of a tissue (e.g., an organ) that include applying energy (e.g., ultrasound energy) into the tissue to cause altered activity at a synapse between a neuron and a non-neuronal cell. In one embodiment, the energy is applied to cause competing or opposing effects for bi-directional control of physiological processes.

Abstract: A turbine engine stage includes a plurality of airfoils extending between an inner band and an outer band. Each airfoil in the plurality of airfoils can have an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge. An intervening flow passage is defined between two adjacent airfoils in the plurality of airfoils.

Abstract: A robotic assembly configured to service an engine, wherein the robotic assembly includes an environmental capture device configured to provide information associated with an environment in which the engine is disposed to one or more computing devices, and wherein the one or more computing devices are configured to use the information to inspect the engine before and after repair operations associated with the service to check for repair equipment, or parts thereof, left in the engine after the repair.

Abstract: A damping device that includes features for damping bending vibration of a shaft rotating about its axis of rotation and methods for damping bending vibration utilizing the damping device are provided. In one exemplary aspect, the damping device includes a damping disc operatively coupled with a shaft, e.g., of a turbine engine or shaft system. The damping disc is at least partially received within a chamber defined by a housing. The chamber of the housing is configured to receive a damping fluid. When the shaft is rotated about its axis of rotation, the damping disc is movable within the chamber to move the damping fluid such that the damping fluid absorbs bending vibration emitted by the shaft. The damping fluid moved by the damping disc dampens bending vibration emitted by the shaft.

Abstract: A build unit for additively manufacturing three-dimensional objects may include an energy beam system having one or more irradiation devices respectively configured to direct one or more energy beams onto a region of a powder bed, and an inertization system including an irradiation chamber defining an irradiation plenum, one or more supply manifolds, and a return manifold. The one or more supply manifolds may include a downflow manifold configured to provide a downward flow of a process gas through at least a portion of the irradiation plenum defined by the irradiation chamber, and/or a crossflow manifold configured to provide a lateral flow of the process gas through at least a portion of the irradiation plenum defined by the irradiation chamber. The return manifold may evacuate or otherwise remove process gas from the irradiation plenum defined by the irradiation chamber.

Abstract: Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle ? of at least one of the plurality of engine-mounting links.

Abstract: A turbine engine and associated methods for a combustor as shown and described. The turbine engine including a combustor with a combustor liner having dilution openings and a geometry that changes along an axial direction. The combustor further having a baffle surrounding a combustor liner defining a combustion chamber of the combustor. A method for controlling nitrogen oxides within the combustor, including injecting compressed air into the annular combustion chamber through any of the dilution openings described herein.

Abstract: A guide for cutting a dowel pin of a rotor assembly is provided. The guide includes a catch basin, including a first catch basin portion and a second catch basin portion, and a shim. The first catch basin portion and the second catch basin portion form a cutting tool receiver. The shim extends from a first edge having a cross-section that is complementary to a surface of the rotor assembly. The first catch basin portion and the second catch basin portion form a receptacle that accommodates and retains portions of a dowel pin during and after removal of the dowel pin from the rotor assembly. The cutting tool receiver is defined by a receiver edge configured to guide a cutting surface of a cutting tool through a cross-section of a dowel pin.

Abstract: A dispatch advisor to assist in selecting operating conditions of a power plant that maximizes operational revenue is described. The dispatch advisor obtains a base load map for operating the power plant to meet base load power demands. The base load map includes a primary base load operating space for attaining target plant power output and efficiency, and an expanded base load portion for attaining higher plant power output and less than optimal efficiency. Both the primary base load operating space and the expanded base load portion associate power output and efficiency values of the power plant that result from a subset of operational parameter values for operating the power plant during base load. The dispatch advisor can transform the flexible base load map into one or more visualizations describing the revenue possibilities associated with operating the power plant based on operating values and attained power output and efficiency.

Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway and another of the multiple guide vanes includes a heated fluid passageway.

Abstract: A blade is provided. The blade comprises a plurality of a first composite fiber plies and a plurality of a second composite fiber plies. Ends of the second fiber plies are staggered such that interlock between the first composite fiber plies and the second composite fiber plies is formed in a region where the second composite fiber plies end and meet with the first composite fiber plies. The blades are used for an engine of an aircraft.

Abstract: A laminate assembly includes a matrix layer and elongated, continuous strips of a conductive alloy. The matrix layer has opposite first and second sides connected by opposite first and second edges. Each of the first and second edges extends from the first side of the matrix layer to the opposite second side of the matrix layer. The elongated, continuous strips of the conductive alloy are disposed in the matrix layer between the first and second sides of the matrix layer. The elongated continuous strips continuously extend through the matrix layer from the first edge to the opposite second edge.

Abstract: A leadwire for physiological patient monitoring is provided that transfers potentials received at a chest electrode to a data acquisition device. The leadwire includes an electrode end connectable to the chest electrode and a first conductive layer extending from the electrode end. The leadwire also has a device end connectable to a data acquisition device and a second conductive layer extending from the device end. The first conductive layer is galvanically isolated from the second conductive layer such that the first conductive layer and the second conductive layer form a capacitor.

Abstract: Systems and methods of servicing engines, an exemplary method of servicing an engine, the method including receiving, by one or more computing devices, information corresponding to one or more components of the engine; determining, by the one or more computing devices, a location of the one or more components of the engine with respect to a location of an augmented reality device; and presenting, in a current field of view display of the augmented reality device, at least a portion of the information corresponding to the one or more components of the engine, wherein the portion of the information includes a rendering of the one or more components, instructions regarding operations to be performed on the one or more components, directional arrows or contextual information associated with the one or more components, or any combination thereof.

Abstract: A gearbox assembly for a turbine engine including a drive shaft and a fan shaft. The gearbox assembly includes a first gear, a second gear, and a planet pin. The first gear is coupled to the drive shaft. The second gear is supported by a planet carrier. The planet carrier is coupled to the fan shaft. Torque is transferred from the drive shaft to the fan shaft through the gearbox assembly. The planet pin is disposed within the second gear. A planet pin shape of the planet pin includes a contoured portion that is characterized by a contoured portion deflection that is greater than or equal to ?4.2e-03 inches and less than or equal to ?1.2e-05 inches.

Abstract: Systems and methods include a plurality of fuel cell stacks extended around a combustion chamber. The plurality of fuel cell stacks are distributed along a length of the combustion chamber in the axial direction. The fuel cell stacks are configured to provide output products to the combustion chamber to achieve at least one of late lean injection and a desired combustor gas concentration distribution.

Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.

Abstract: A method is disclosed and includes authenticating a first stage boot loader and authenticating a second stage boot loader in response to authentication of the first stage boot loader. The method also includes executing the second stage boot loader in response to authentication of the second stage boot loader. Executing the second stage boot loader includes loading an operating system, a first set of machine-readable instructions, and first configuration information associated with the first set of machine-readable instructions onto a non-transitory computer-readable medium, wherein the first set of machine-readable instructions and the first configuration information are associated with one or more priority partitions. Executing the second stage boot loader includes authenticating the operating system and the first set of machine-readable instructions.