Abstract: The present disclosure describes various embodiments of systems, apparatuses, and methods for drone-based administration of remotely located devices. One such method comprises deploying an unmanned aerial vehicle from a base station, wherein the base station assigns a maintenance order to the unmanned aerial vehicle for servicing of a remote device, traveling, by the unmanned aerial vehicle, to the location of the remote device, authenticating, by the unmanned aerial vehicle, a valid identification of the remote device; upon the remote device being authenticated by the unmanned aerial vehicle, servicing the remote device by at least charging a power supply of the remote device and transferring contents of a device log to the unmanned aerial vehicle; and after completing the servicing of the remote device; returning to the base station and transferring contents of the device log to the base station.

Abstract: A turbine blade, including a root, a vane including a leading edge and a trailing edge and a pressure-side wall and a suction-side wall, and including cooling vents at the trailing edge, this vane also including first and second serpentine circuits; each serpentine circuit including several ducts extending in the span direction, being connected to each other by angled portions; each serpentine circuit being supplied with air by its duct that is closest to the leading edge; and wherein the vents are supplied by the first and by the second serpentine circuit.

Abstract: Various embodiments include a turbine blade having an airfoil with a tip shroud having a forwardmost tip rail having one or more pressure side and suction side bevel surfaces and pressure side and suction side scallop surfaces. The surfaces have a nominal profile substantially in accordance Cartesian coordinate values of X, Y and Z set forth in various tables herein. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a tip rail length expressed in units of distance. The X, Y and Z values are connected by smooth continuing arcs that are joined smoothly with one another to form the nominal profile that defines the suction side scallop surface, the pressure side scallop surface, the suction side bevel surface, or the pressure side bevel surface.

Abstract: A turbine rotor blade includes a blade body and a tip shroud on a tip of the blade body. The tip shroud has a contact block configured to face a tip shroud of an adjacent turbine rotor blade, and the contact block includes a base material, an oxidation resistant coating on the surface of the base material, and a hard wear resistant coating on the surface of the oxidation resistant coating.

Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (?) with the heated surface.

Abstract: An airfoil for a turbine engine, the airfoil having an outer wall defining an interior and a camber line extending through the airfoil, and at least one cell located within the interior. The at least one cell can include a forward portion and an aft portion with respect to the camber line. The forward portion and the aft portions can be connected by side portions. A braided fabric can be provided on at least one of the forward or aft portions, while a braided fiber can be provided on at least one of the side portions.

Abstract: The invention relates to a movable turbomachine blade comprising at least one cooling circuit comprising at least one cavity extending radially between the root and the tip, at least one air intake opening at a radial end of the cavity, a plurality of first discharge slots arranged to open out along the trailing edge between the root and the tip, and a plurality of second discharge slots separate from the first discharge slots and arranged along the trailing edge between the root and the tip, the second discharge slots being offset axially upstream relative to the first discharge slots and each of the first discharge slots being radially offset relative to each of the second discharge slots, with no overlap between the first and second discharge slots.

Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.

Abstract: This steam valve includes a valve casing, a valve body, a valve stem, an actuator, a heat buffer member, a link mechanism, and a link base. The heat buffer member includes: a heat buffer plate separated toward a leading end side from the valve casing in an axial direction in which the valve stem extends; and a support column that fixes the heat buffer plate to the valve casing so as to be incapable of relative movement. The actuator includes: an actuator casing; and an actuator rod that extends in the axial direction from in the actuator casing and that moves in the axial direction with respect to the actuator casing. The link base is fixed to the heat buffer member and extends from the heat buffer member in an axial perpendicular direction that is perpendicular to the axial direction. The actuator casing is fixed to the link base.

Abstract: An appliance includes a tub defining a wash chamber, and a centrifugal pump in fluid communication with the wash chamber. The centrifugal pump includes a motor housing, a motor disposed in the motor housing, and a fluid impeller coupled to the motor. A diffuser housing assembly includes a first diffuser housing portion and a second diffuser housing portion. The first diffuser housing portion includes a groove and the second diffuser housing portion includes an extrusion. A diffuser vane is positioned on the motor housing. The diffuser vane engages in the groove of the first diffuser housing portion. The extrusion of the second diffuser housing portion encloses the diffuser vane into the diffuser housing assembly.

Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.

Abstract: A turbine blade in a gas turbine engine includes an airfoil extending in a radial direction. The airfoil has an outer wall delimiting an airfoil interior. The outer wall includes a pressure sidewall and a suction sidewall joined at a leading edge and a trailing edge in a longitudinal direction. A turbulator is disposed in the airfoil interior. The turbulator includes a first row having at least two turbulator ribs spaced apart in the longitudinal direction. The turbulator includes a second row extending in the radial direction from the first row and having at least two turbulator ribs spaced apart in the longitudinal direction.

Abstract: A turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.

Abstract: A propeller control system of an air mobility is configured to insert a movable part forming a propeller into a fixed part in a situation where the air mobility is stored and crashes, thereby reducing an entire length of the propeller. As a result, an entire size of the air mobility is reduced when the air mobility is stored, which may prevent secondary accidents caused by fragments generated by contact of the rotated propeller with the ground in the situation where the air mobility crashes.

Abstract: The present disclosure relates to supporting structures for a central frame of a direct-drive wind turbine and methods for managing such structures. A supporting structure is configured to assume a deployed configuration and a stowed configuration. In the stowed configuration, the supporting structure has a shape and size such that the supporting structure can be introduced into the central frame from an outside. In the deployed configuration, the supporting structure has one or more increased dimensions with respect to the stowed configuration, and comprises a working platform.

Abstract: A tip shroud, comprising a plurality of tip shoes encircling a rotor assembly, in a turbine may deform due to thermal gradients experienced during operation of the turbine. Accordingly, a tip shoe is disclosed that utilizes an internal cooling cavity to supply coolant throughout the interior of the tip shoe, as well as to the slash faces of the tip shoe. In addition, features are described that increase the surface area exposed to the coolant, while remaining suitable for additive manufacturing.

Abstract: The disclosure relates to a high-speed radial fan and to a rotor assembly (10) for a high-speed radial fan, comprising a bearing tube (20) which is axially open in the interior and in which a shaft (40) carrying a fan wheel (30) is mounted with a rotor (50), wherein the rotor (50) of the rotor assembly (10) is mounted in a cylindrical separating can (3).

Abstract: A stator vane formed of CMC has a radially outer platform and a radially inner platform attached to an airfoil. There are a pair of flanges on a side of each of the radially inner platform and radially outer platform which is remote from the airfoil. A first of the pair of flanges is associated with the suction side of the airfoil and a second of the pair of flanges is associated with the pressure side of the airfoil. The flanges extend in a generally axial direction. The first of the pair of flanges extend over at least a majority of the suction side measured between the leading and trailing edge of the airfoil and the second of the pair of flanges extend over at least a majority of the pressure side measured between the leading and trailing edges of the airfoil.

Abstract: The present disclosure provides an air combat maneuvering method based on parallel self-play, including the steps of constructing a UAV (unmanned aerial vehicle) maneuver model, constructing a red-and-blue motion situation acquiring model to describe a relative combat situation of red and blue sides, constructing state spaces and action spaces of both red and blue sides and a reward function according to a Markov process, followed by constructing a maneuvering decision-making model structure based on a soft actor-critic (SAC) algorithm, training the SAC algorithm by performing air combat confrontations to realize parallel self-play, and finally testing a trained network, displaying combat trajectories and calculating a combat success rate. The level of confrontations can be effectively enhanced and the combat success rate of the decision-making model can be increased.

Abstract: A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.