Abstract: One of spacing between the base-side first tooth and the base-side second tooth or spacing between the base-side second tooth and the base-side third tooth is greater than spacing between the tip-side first tooth and the tip-side second tooth.

Abstract: A vane assembly includes an airfoil extending from a platform. The platform has a flange that extends radially outward and circumferentially across the platform. A vane cover is arranged adjacent the platform that defines an impingement gap between the platform and the vane cover. The vane cover has a wall that defines a slot. The flange is arranged at least partially within the slot.

Abstract: Turbomachine hollow blade (11) comprising at least one vane (14) having lateral walls (15) which are intended to guide a flow in a flow path around the vane and which are fixed to a first platform (12) at a first longitudinal end of the vane (14), the vane (14) further comprising an internal cavity between the lateral walls (15), which cavity is intended for passing a vane-cooling fluid, with a fluid inlet opening (19) opening through said first platform (12), characterized in that a gyroid surface network (18) fills at least part of the cavity, being arranged therein so as to guide the cooling fluid, and is in contact with at least part of the lateral walls (15).

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: A turbine blade includes: an airfoil portion extending in a blade height direction and having a pressure surface and a suction surface each of which extends between a leading and trailing edges; a shroud portion disposed on a blade tip side of the airfoil portion; a fillet portion formed by a curved surface and connected to an end portion of the shroud portion on a side of the airfoil portion; at least one first cooling hole extending along the blade height direction within the airfoil portion; at least one cooling cavity disposed at least partially within the shroud portion and communicating with the at least one first cooling hole; and a second cooling hole connected to the at least one cooling cavity and opening to a surface of the shroud portion. The airfoil portion has a reference airfoil in which a maximum blade thickness is minimum at a reference position.

Abstract: A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to receive a nominal command reference from the main processing unit, determine a series of cumulating command references based at least in part on the nominal command reference; and output a series of cumulating control commands to the controllable component. The series of cumulating control commands may be based at least in part on the series of cumulating command references.

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: Disclosed is a remote control smart blower. More particularly, the remote control smart blower includes a blower chamber (100) compressing external air flowing inside and discharging the compressed air; and a blower controller chamber (200) forming a predetermined-high partition with the blower chamber (100) and being able to operate and monitor in real time the power and operation status of a blower (110) disposed and fixed in the blower chamber (100), in which a manager can check the operation status of the blower (110) installed and fixed at a site and control and manage the blower (110) in real time using an exclusive terminal not only at the site, but regardless of the distance due to the blower controller chamber (200), whereby safety of operation and ease of management of the blower (110) are maximized.

Abstract: A fixture system for rail transport of wind turbine blades upon a consist of flatcars using a root-support fixture, a blade-support fixture, and first and second guide post that intermittently engage the tip-end portion of the wind turbine blade to limit lateral movement thereof, such that movement of the consist around a curved railway section urges the wind turbine blade against the first or second guide posts, which urges the wind turbine blade to urge the blade-support fixture to move laterally, thereby laterally reorienting the blade upon the consist.

Abstract: A neck fan includes an arc-shaped shell configured to hang around user's neck and at least four fan assemblies arranged in the shell. The shell includes a first part and a second part. Each of the first part and the second part defines an accommodating space, air inlets and air outlets communicated with the accommodating space, at least one partition is arranged in the accommodating space and configured to divide the accommodating space into at least two accommodating parts arranged along an extension direction of the shell. Each of the fan assemblies is arranged in one of the at least two accommodating parts and is configured to direct air into the one of the at least two accommodating parts through corresponding air inlets and to direct air out of the one of the at least two accommodating parts through corresponding air outlets.

Abstract: A wind turbine with a nacelle with a nacelle floor is thus provided. The wind turbine further has an aerodynamic rotor with at least two rotor blades. The wind turbine further has a tower, on which the nacelle is arranged. At least one first and second opening are provided in the nacelle floor. The first opening is used to transport first components of the wind turbine, and has corresponding first dimensions. The second opening has second dimensions, and is used to transport a transformer into the nacelle. The transformer has a floor that closes the second opening when the transformer has been conveyed through the second opening into the nacelle and mounted in the nacelle.

Abstract: A ceramic matrix composite airfoil includes a high-pressure surface and a low-pressure surface connected at a leading edge and a trailing edge. The high-pressure surface and the low-pressure surface extend from a first end to a second end. A leading edge cooling passage includes an inlet portion, a midspan portion and an outlet portion. A cross-sectional flow area of the midspan portion is less than a cross-sectional flow area of either the inlet portion or the outlet portion.

Abstract: A propeller fan includes a shaft portion disposed on a rotation axis, and a blade disposed on an outer peripheral side of the shaft portion and including a leading edge and a trailing edge. The blade includes a negative pressure surface in which a plurality of recesses are formed, and the plurality of recesses include a first recess and a second recess disposed on the trailing edge side than the first recess in a circumferential direction about the rotation axis as a center. The first recess has a depth larger than a depth of the second recess.

Abstract: A cooling system includes a nozzle guide vane endwall. The nozzle guide vane endwall includes a first wall and a second wall. The first wall includes a first opening that extends completely through the first wall into a primary flow path of a high-pressure turbine. The second wall includes a second opening that extends completely through the second wall into an inner passageway of the nozzle guide vane endwall. The inner passageway is configured to direct a cooling fluid to the first opening and/or the second opening. The first and second opening are configured to receive a plug or a probe.

Abstract: A side channel compressor for compressing gas includes a housing, which forms a side channel, and an impeller drive arranged in the housing. The housing forms a feed channel fluidically connected to the side channel for feeding gas to the side channel and a discharge channel for discharging gas out of the side channel that is fluidically connected to the side channel. The feed channel branches into two separate channel arms each extending along a channel arm center axis. The housing is subdivided along a separating plane into first and second housing parts which sealingly lie against one another. The discharge channel is passed through between the two channel arms and either a first or second discharge channel part of the discharge channel, opens out on a connecting surface of the first or second housing part forming a gas outlet opening arranged apart from the separating plane.

Abstract: A turbine blade for a gas turbine engine includes a plurality of cooling holes positioned adjacent a tip of the turbine blade. The plurality of cooling holes are oriented at specific angles to produce film-cooling of the turbine blade tip to improve durability and performance of the turbine blade. Further, the plurality of cooling holes are positioned at specific locations to improve film-cooling of the turbine blade while reducing negative impacts on performance of the turbine blade.

Abstract: A turbomachine includes a housing having an inlet and an outlet. A shaft is rotationally disposed in the housing. The shaft is rotatable about a longitudinal axis. An impeller is coupled to the shaft between the inlet and the outlet and rotates with the shaft. The impeller includes a single impeller inlet and an impeller outlet, a first set of vanes disposed on a first side of the impeller, and a second set of vanes disposed on a second side of the impeller. A passage is formed through a thickness of the impeller. The passage facilitates transmission of fluid from the first side of the impeller to the second side of the impeller such that fluid is supplied to the first set of vanes and the second set of vanes via the single impeller inlet. Transmission of fluid through the impeller reduces net axial thrust imparted to at least one of the impeller and the shaft.

Abstract: This present disclosure relates generally to propulsion systems and, more particularly, to adaptive ducted fan propulsion systems for use with aircraft such as unmanned aerial vehicles. Embodiments of ADF systems in accordance with the present disclosure feature automatic, fast operation, increase the intake section of the air mass fed to a propeller, and can increase thrust by 35%-40% as compared to existing ducted fans.

Abstract: Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to engage with the baffle and define radially extending channels therebetween. First and second forward radially extending rails are segmented in the radial direction and a showerhead radial channel is defined along the leading edge. Pressure and suction side radial flow channels are defined between an interior surface of the airfoil body, an exterior surface of the baffle, and radially extending rails. An aft channel is defined between an interior surface of the airfoil body along pressure and suction side walls, an interior rib, exterior surfaces of the baffle, and the radially extending rails.

Abstract: A rotor shroud for a rotary machine in a cabin air compressor includes a disk portion centered on a central axis of the rotor shroud, a frustoconical portion extending from the disk portion, a flared portion extending from the frustoconical portion, and a variable lattice structure in an interior of the rotor shroud. The variable lattice structure includes a first region of the rotor shroud having a first lattice structure and a second region of the rotor shroud having a second lattice structure. The second lattice structure of the second region is denser than the first lattice structure of the first region. The second region is a deflection region, a stress region, or an energy containment region of the rotor shroud.