Abstract: A propulsion system assembly includes an open propulsor rotor, an open guide vane structure and a nose cone. The open propulsor rotor is configured to rotate about an axis. The open guide vane structure is aft of the open propulsor rotor along the axis. The nose cone is forward of the open propulsor rotor along the axis. The nose cone includes a forward tip end, an aft base end, a stationary section and a rotating section. The aft base end is adjacent to the open propulsor rotor. The stationary section projects axially along the axis from a junction between the stationary section and the rotating section to the forward tip end. The rotating section projects axially along the axis from the junction between the stationary section and the rotating section to the aft base end. The rotating section is configured to rotate with the open propulsor rotor about the axis.

Abstract: A fluid cooler for installation in a bypass duct of a turbofan gas turbine engine and associated methods are provided. The fluid cooler includes an inlet duct, a heat exchanger and an outlet duct. The inlet duct includes an inlet protruding into the bypass duct to receive a portion of the bypass air into the inlet duct. The heat exchanger is in fluid communication with the inlet duct. The heat exchanger facilitates heat transfer between a fluid and the portion of bypass air received into the inlet duct. The heat exchanger defines a general flow direction for the portion of bypass air that is different from the main flow direction of bypass air inside the bypass duct. The outlet duct conveys the portion of bypass air from the heat exchanger back to the bypass duct.

Abstract: A cooling system for a compressor casing of an turbofan engine includes a cooling conduit extending between an inlet in fluid communication with a bypass duct of the turbofan engine and an outlet in fluid communication with an outer surface of the compressor casing. A shroud of the compressor is mounted to the compressor casing. A protrusion is disposed about an opening to the inlet and protrudes radially outwardly into the bypass duct A valve in selective fluid communication with the inlet of the cooling conduit is operable to selectively inject a flow of high pressure air from a high pressure air source towards the inlet of the cooling conduit to modulate a flow of bypass air entering the cooling conduit.

Abstract: A welding system includes a collaborative robot, a robot controller, a welding torch having an end located at a tool center point (TCP), a welding power supply, and a teach pendant. The teach pendant includes a UI application configured for programming welding points and parameters. In a first operation mode, the UI application displays the plurality of welding points in a list that includes a highlighted closest welding point having a three-dimensional position that is closest to the TCP. The highlighted closest welding point automatically updates upon manual movement TCP. In a second operation mode, the list includes a highlighted selected welding point, and the UI further displays a selector button that shows a straight line distance of the TCP to a three-dimensional position of the highlighted selected welding point. Activation of the selector button causes the TCP to move to the position of the highlighted selected welding point.

Abstract: Correlated sets of historical meteorological data and terrain data are obtained for at least one geographical area. A data model is derived based on the basis of the correlated sets, by training the data model. The trained data model is adapted to identify coherence between meteorological data and terrain data relating to the same geographical area. Meteorological data and terrain data related to the renewable energy site are fed to the trained data model, the terrain data having a higher resolution than the meteorological data. Using the trained model, meteorological data related to the renewable energy site with increased resolution is estimated by downscaling the meteorological data. The estimated meteorological data with increased resolution for the renewable energy site is then used for planning a layout of the renewable energy site.

Abstract: A floating hybrid tidal/wave/wind energy harvesting system is described, wherein the system is based on vertical axis turbines for synergized tidal, wave and wind energy production. The system is self-starting and can continuously, and simultaneously, harvest wind and tidal energy in a wide range of wind and tidal current speeds.

Abstract: Example apparatus, systems, and methods for rapid active clearance control of inter-stage and mid-stage seals are disclosed. An example apparatus to control clearance for a turbine engine comprises a case surrounding at least part of the turbine engine and defining an opening therethrough; a nozzle, the nozzle including a reference pressure sensor and a static pressure sensor on a tip of the nozzle; an actuator including a multilayer stack of material, a rod coupled to the first actuator and coupled to the nozzle through the opening in the case, the rod to move the nozzle based on contraction or expansion of the multilayer stack of material; and a controller to calculate and set the clearance between the rotor and the nozzle by supplying an electrical current to the multilayer stack to cause the multilayer stack to at least one of expand or contract.

Abstract: A propulsion mechanism for an unmanned aerial vehicle (UAV) is disclosed. The propulsion mechanism includes one or more blades configured for rotation by a motor and a hub configured for coupling to the motor. The hub includes a spring plate assembly. The spring plate assembly includes a hub plate that includes a mating portion, a pressure plate that includes a keyhole that receives the mating portion of the hub plate to couple the hub plate to the pressure plate, and a biasing member configured to be disposed along a shaft of the motor between the motor and the pressure plate. The one or more blades are coupled to the hub between the hub plate and the pressure plate. Additionally, the biasing member is configured to increase friction between the one or more blades and hub plate.

Abstract: An airfoil of a turbine blade or a turbine vane includes a coolant flow cavity formed in an interior of the airfoil, an insert section inserted into the coolant flow cavity and having a plurality of cooling holes, and a cooling structure arranged between an outer surface of the insert section and an inner surface of the coolant flow cavity, wherein the cooling structure includes a support part disposed in close contact with the outer surface of the insert section and having a plurality of impinging air-jet holes in fluid communication with the plurality of cooling holes, and a cooling fin connected between a distal side of the support part relative to a center of the airfoil and the inner surface of the coolant flow cavity.

Abstract: Techniques for conducting an air flow simulation for a wind turbine include importing a file containing a digitized representation of a three-dimensional blade geometry, extracting from the file, blade constructive parameters, and calculating a low-order air flow past a wind-turbine that includes the blade, based on a Blade Element Momentum Theory (BEMT) to determine sectional angle of attack and free-stream velocity, boundary layer transition, and acoustic noise results. The techniques also include performing air flow simulation for a given number of blade sections, and generating virtual microphone rings. The process also includes computing noise spectra at the virtual microphone rings and blending the noise spectra generated and generating synthetic noise signals from each section by inverse Fourier transform of the noise spectra and converting the noise spectra into an audio track.

Abstract: An impeller for a disc pump has a drive disc having a connector adapted to join with a shaft of the disc pump, and a driven disc affixed to the drive disc so as to define a space therebetween. The drive disc has a face facing a face of the driven disc. The drive disc extends in generally parallel relationship to the driven disc. At least one of the faces of the drive disc and the driven disc has an undulating surface thereon. A plurality of posts are affixed to the face of the drive disc and the driven disc. Each of these posts has an airfoil-shaped cross-section in a plane parallel to the face of the drive disc and the driven disc.

Abstract: A fan frame, a fan module, and an electronic device are proposed. The fan module includes a plurality of fan frames and a plurality of fan blades. The fan frames are connected to each other along a connecting direction. Each of the fan frames includes a body, a first frame and at least two positioning members. The first frame is connected to one end of the body and includes a first connecting part, at least two positioning holes and a second connecting part. The at least two positioning holes are spaced apart from each other on the first connecting part. The second connecting part is opposite to the first connecting part. The at least two positioning members are spaced apart from each other on the second connecting part. The fan blades are respectively disposed in the fan frames.

Abstract: An airfoil includes a high pressure surface and a low pressure surface that are 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 camber line extends between the leading edge and the trailing edge and a camber angle is defined as a plurality of camber-angle distributions that extend between the leading edge end and the trailing edge. The plurality of camber-angle distributions include a uniform portion that extends from the leading edge to a forced non-equilibrium boundary layer diffusion (FNBD) feature. The uniform portion includes a non-dimensionalized camber-angle unit that is constant the FNBD feature includes a rapidly increasing camber-angle that is 0.2 non-dimensional camber-angle units higher than the non-dimensionalized camber-angle of the uniform portion.

Abstract: An apparatus includes an optical sensor and at least one controller operably coupled to the optical sensor. The optical sensor is configured to detect a time of arrival (TOA) of a blade while operating in a TOA mode. The at least one controller is configured to determine that conditions on a tip of the blade are subject to icing while the optical sensor is operating in the TOA mode. The at least one controller is also configured to control the optical sensor to operate in a deicing mode to increase power of the optical sensor and heat the tip of the blade.

Abstract: A rotor stage for a gas turbine engine is provided that includes first and second rotor blades, a disk, and a seal member. The rotor blades each have an airfoil, an attachment section, a neck section, and a platform. The disk has forward and aft axial end surfaces, an outer radial surface that extends between the forward and aft axial end surfaces, and disk slots configured to receive rotor blade attachment sections. In a rotor stage assembled state, the attachment sections are fully received in the disk slots, and adjacent rotor blade platforms, and the outer radial surface of the disk form a tab slot. In the assembled state, a central segment of the seal member is engaged with a platform channel disposed at a platform lateral edge surface, and an axial locator tab of the seal member is disposed in the at least one tab slot.

Abstract: A rotor system design can reduce blade-wake interaction by staggering the vertical mounting position of the rotor blades on a hub. By staggering the vertical position, as the hub turns, the turbulent air impingement on subsequent rotor blades can be reduced. By reducing the turbulence on subsequent rotor blades the drag and noise is reduced. In rotor systems with an even number of blades, opposing rotor blade pairs can be mounted at the same vertical distance which can be different from other opposing rotor blade pairs. In rotor systems with an odd number of rotor blades, the rotor blades can be mounted at a fixed or variable vertical distances from the preceding blade so each rotor blade travels in a different tip path plane. Other techniques for reducing the wake vortices impingement can include mounting opposing blades at a dihedral/anhedral angle with respect to subsequent rotor blades.

Abstract: The present invention discloses a neural network-based NARMA-L2 multivariable control method, which includes: deriving a NARMA-L2 multivariable control law of a nonlinear discrete system; using neural networks to offline identify nonlinear functions in the control law; designing the controller with the control law, designing a closed-loop control system for a certain type of turbofan engine, and adding the function of making the online update of neural network errors on the basis of this to correct the controller parameters, and studying the tracking performance of the control system. Aimed to minimize the quadratic performance index for the errors of the engine's high-pressure rotating speed and pressure ratio, by using neural networks in combination with the deduced NARMA-L2 multivariable control law, the present invention has designed a dual-variable controller, calculated the engine's control variables and controlled the fuel flow of the engine and the critical interface area of the exhaust nozzle.

Abstract: A propeller for an aircraft propulsion assembly extending longitudinally along an axis X. The propeller comprising a propeller cone, blades, a guide member extending longitudinally along the axis X and rotating as one with the propeller cone, the guide member being mounted outside the propeller cone in such a way as to form between them a guide path, the guide member having an upstream opening configured to convey a flow of air in the guide path and a downstream opening in such a way as to remove the flow of air downstream, the guide member having through-orifices through which extend the blades of the propeller and compressor vanes, which rotate as one with the propeller cone and which are positioned in the guide path in such a way as to generate an accelerated air flow.

Abstract: A system, relating to the technical field of hydroelectric power generation, is provided which includes a turbine device, a power generating device and a rooftop water tank. A water inlet is provided at the top of the rooftop water tank. The turbine device includes a turbine housing provided above the water inlet with a water outlet being provided at the bottom of the turbine housing. A turbine is provided inside the turbine housing with a turbine rotating shaft passing through the turbine housing. One end of the turbine rotating shaft is transmittingly connected to an input shaft of the power generating device. A high-pressure nozzle is fixedly disposed on a sidewall of the turbine housing.

Abstract: Temporary enclosure (1) for at least a part of a rotor blade connected to a wind power plant having a tower and a rotor top part, the enclosure (1) having a framework (2); one or more walls (3); a roof (4); said roof extends from said wall towards said blade; said framework (2) stretching said walls (3) said that a volume is enclosed below the roof (4) wherein said framework (2) includes one or more frame parts (5), a connection (6) for connection of the one or more frame parts (5) and an activation means (7) for activation a change in the framework (2) whereby the volume enclosed by the enclosure (1) change.