Abstract: The present disclosure relates to a method for manufacturing a blade segment for a segmented wind turbine blade, and a resulting segment for a segmented wind turbine blade as well as the segmented wind turbine blade. In particular, the blade segment comprises a female spar part defining an inner cavity and having a longitudinal inner end and an opposite longitudinal open end towards an end face of the blade segment, a first spar cap connected to an inner surface of a first shell portion and comprising a first primary spar cap portion. The blade segment further comprises a first secondary spar cap portion affixed to a first outer surface of the female spar part. The first secondary spar cap portion is glued to the inner surface of the first shell portion and/or to the first primary spar cap portion forming a glue interface between the first secondary spar cap portion and the inner surface of the first shell portion and/or the first primary spar cap portion.

Abstract: A wingsail comprising: a first aerofoil having a leading edge at a front of the wingsail and a trailing edge behind the front edge; and a second aerofoil having a leading edge and a trailing edge, the leading edge of the second aerofoil being closer than the trailing edge of the second aerofoil to a point of maximum cross-sectional width of the second aerofoil; wherein the wingsail is configured such that the leading edge of the second aerofoil can be positioned behind the trailing edge of the first aerofoil; wherein the first aerofoil comprises: an air inlet; an air outlet; a channel inside the first aerofoil connecting the air inlet and the air outlet; wherein air flow from the air inlet is directed by the channel to the air outlet.

Abstract: An assembly is provided for an aircraft. This assembly includes a propulsion system and a control system. The propulsion system includes an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor about an axis. The control system includes a first sensor, a second sensor and a controller in signal communication with the first sensor and the second sensor. The first sensor is configured to provide first sensor data indicative of a first environmental parameter. The second sensor is mounted to the propulsion system and is configured to provide second sensor data indicative of a second environmental parameter. The controller is configured to monitor and/or control operation of the propulsion system using the first sensor data. The controller is also configured to monitor the first sensor data using the second sensor data.

Abstract: The invention relates to a rotor for a fluid pump, in particular for use in the medical sphere, the rotor being compressible for bringing to the place of use and thereafter being expandable. The compressibility is assisted by the provision of cavities, in particular also production of the rotor at least partially from a foam.

Abstract: The present application discloses a maglev air compressor, which includes a compressor housing, a motor stator, a rotor, a first impeller assembly and a second impeller assembly subjectable to an axial magnetic force and a control module. The compressor housing, the motor stator and the rotor are sleeved sequentially, both ends of the rotor are rotatably connected to an inside of the compressor housing through a maglev bearing group, the first impeller assembly and the second impeller assembly are fixedly oppositely installed on the both ends of the rotor. The maglev bearing group includes: a first thrust bearing piece generating a first axial magnetic force to the first impeller assembly, and, a second thrust bearing piece generating a second axial magnetic force to the second impeller assembly.

Abstract: Fire retardant engine casing apparatus are disclosed. An example engine casing includes an inner shell circumferentially surrounding blades of a fan, a compressor, or blades of a turbine, the inner shell including perforations to receive acoustic waves, an outer shell positioned around the inner shell, a fire retardant material between the inner shell and the outer shell, and a screen positioned between an outer radial end of the perforations and the fire retardant material.

Abstract: A fan blade, a fan and a fan lamp. The fan blade includes: a blade root; a blade tip; a leading edge, which connects the blade root to the blade tip and is located on a windward side; and a trailing edge, which connects the blade root to the blade tip and is located on a leeward side, wherein the leading edge is configured in a wavy shape from the blade root towards the blade tip, the trailing edge is configured in an arc shape, and the distance between the leading edge and the trailing edge increases first and then decreases from the blade root towards the blade tip.

Abstract: The invention relates to a turbine engine case (1), extending around an axis, said case (1) comprising: a hub comprising an outer wall (21) and an inner wall (22) between which an annular flange (23) extends; an outer shell (3); a plurality of arms (4) which each extend between the hub and the outer shell (3); the case (1) further comprising a plurality of main stiffeners (5), each being disposed in the extension of an arm (4) between the outer wall (21) and the inner wall (22) projecting from the flange (23), each main stiffener (5) comprising two ribs (51, 52) arranged opposite one another and which move away from one another from the outer wall (21) towards the inner wall (22).

Abstract: A blade for a vertical axis wind turbine is disclosed. The blade comprises a unified skin having variable thickness, including a first skin section with greater thickness than a second skin section. The blade further includes a plurality of internal beam walls that connect a blade outside portion and a blade inside portion, with at least one beam wall positioned at a predefined distance, between 58% and 90% of the chord length, from the leading edge to enhance structural integrity. The blade additionally includes a bracketed structural member that is integrated into the thick skin section and configured to hold a nut bar, enabling secure, reinforcement-free attachment to a turbine arm. The design improves manufacturability, reduces weight, and enhances fatigue resistance under turbulent wind conditions.

Abstract: Disclosed is a refrigerable hanging ice neck collar, which includes a neck collar bracket, a heat dissipation component, a refrigeration sheet, a fan, a non-metallic shell, a cold storage material layer and an electronic control component. The neck collar bracket and the non-metallic shell are respectively elastic, and the electronic control component is used to control the cooling of the refrigeration sheet and the rotation of the fan. The fan rotates to supply air into the air duct, and the through hole in the air duct is used to connect the heat dissipation component. When the wind in the air duct passes through the through hole, it will take away part of the heat of the refrigeration sheet and dissipate heat and cool the refrigeration sheet, and the air outlet can also provide airflow to blow toward the head.

Abstract: A method and apparatus for minimizing engine weight for a turbine engine by utilizing one or more discrete protuberances disposed on an engine component wall. The wall can have a nominal thickness to decrease engine weight while the protuberances can provide increased discrete thicknesses for providing one or more cooling holes. The increased thickness at the protuberances provides for an increased thickness to provide sufficient length to increase cooling hole effectiveness.

Abstract: A plenum assembly for a compressor has a plenum housing defining a radially inward entry to a compressor and an outer circumference, and at least two open areas in the outer circumferences which are defined by at least two plenum flanges; an inlet duct connected to a first plenum flange of the at least two plenum flanges; and a panel having a flow control feature, wherein the panel is connected to a second plenum flange of the at least two plenum flanges.

Abstract: The present invention relates to a spar cap for a wind turbine blade and a method for manufacturing said spar cap. The spar cap comprises: a plurality of reinforcing fibre layers comprising unidirectionally oriented reinforcement fibres, wherein the plurality of reinforcing fibre layers are arranged such that the spar cap tapers in thickness towards a first longitudinal end, and a number of first fibre skin layers arranged on a first surface of the plurality of reinforcing fibre layers, and a number of second fibre skin layers arranged on a second surface of the plurality of reinforcing fibre layers, such that the plurality of reinforcing fibre layers are arranged between the number of first fibre skin layers and the number of second fibre skin layers.

Abstract: A method forming a wind turbine blade includes forming a first shell of the wind turbine blade, the first shell having a first exterior side surface, a first interior side surface, and a first mating side surface connecting the first interior and first exterior side surfaces to one another, forming a second shell of the wind turbine blade, the second shell having a second exterior side surface, a second interior side surface, and a second mating side surface connecting the second interior and second exterior side surfaces to one another, and connecting the first and second mating side surfaces to one another to form the wind turbine blade. The first and second shells include date palm tree material and epoxy.

Abstract: Systems and methods for fluid flow control are provided. A coarse valve and a fine valve are connected in parallel in a conduit. A coarse valve controller controls the coarse valve in a feedback loop in which an error signal is feedback to the coarse valve controller and a coarse valve setting is an output of the coarse valve controller. The error signal is a difference between the property of the fluid flow and a set point. The coarse valve controller operates as a proportional-integral controller. A fine valve controller controls the fine valve in the same feedback loop as the coarse valve controller. The fine valve controller has a center-seeking control scheme and operates as a proportional controller or a proportional-integral controller depending on whether the coarse valve setting is in a saturation range.

Abstract: A wind turbine comprising a tower, a nacelle arranged on the tower, a generator, and a rotor comprising at least one rotor blade, wherein the wind turbine comprises vortex generators arranged on an outer surface of the tower, wherein the vortex generators have a fin extending from the outer surface of the tower, and wherein the fin has a height extending perpendicularly from the surface of the tower and a fin chord extending parallel to the surface of the tower. The fin chord has a curvature such that a first end of the fin chord has a smaller angle to the horizontal than the opposite second end of the fin chord.

Abstract: A cyclonic particle separator may include a housing including a cylindrical sidewall having a plurality of flow entry ports. A cover member closes a first end of the cylindrical sidewall, and a mounting member having a flow exit opening defined therethrough is at a second end of the cylindrical sidewall. At least one particle exit passage is defined in the housing. Each of the plurality of flow entry ports includes a flow directing surface angled to direct a gas flow from upstream of the housing to enter the housing in a tangential direction relative to the cylindrical sidewall, causing a cyclone vortex. The cyclone vortex acts to separate particles from the gas flow.

Abstract: A tool (14) for reducing vibrations in wind turbine blades at scheduled standstill for example during turbine installation or service, the tool comprising an elongate flow-disrupting flexible sleeve (15) for fitting over a blade tip and extending part-way along its length having a tip end which in use overlies a blade tip with a first edge which in use overlies a blade leading edge; and at the opposite edge a longitudinal slit, with tensioning bands (26) provided on the sleeve at opposite edges adjacent the slit for tensioning the sleeve in the longitudinal direction.

Abstract: A Savonius wind turbine has been noted in the past to have the capability to perform more efficiently than other drag-type vertical axis turbines when built according to certain parameters. The previous literature has missed seeing the ratio of the shaft diameter to the available space for wind to pass through in the center as the crucial relationship on which other improvements in this type of turbine can be built. The chord diameter and overlap distance all depend on the size of the central shaft and its ratio to the inner endpoints of the overlapping semicircular blades. The ratios for maximal efficiency are presented here. These efficient ratios also depend for their execution on the turbine rotating at an ideal tip speed ratio.

Abstract: A gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis is provided. The gas turbine engine includes: a fan rotatable about the longitudinal axis; a turbomachine; and a housing surrounding the turbomachine and having an upper outer surface portion and a lower outer surface portion, the housing defining a first distance extending radially from the longitudinal axis to a first point located at the upper outer surface portion, the housing further defining a second distance extending radially from the longitudinal axis to a second point located at the lower outer surface portion, and the second distance is greater than the first distance.