Abstract: The invention relates to a wind turbine (100) having a rotor (102) rotatable about a vertical axis of rotation (104) having a rotating hub (3) and a plurality of rotor blades disposed along an outer periphery of the rotor (102), each of which have a lower segment (4) and an upper segment (5) attached to an upper distal end of the lower segment (4). The lower proximal ends of the lower segments (4) of the rotor blades are each attached to the rotating hub (3). To form a particularly stable and lightweight platform for the rotor (102) or rotor blades, it is proposed that the lower segments (4) of the rotor blades form an inverted pyramid in conjunction with the hub (3), guy wires (7) and bracing wires (8), wherein the guy wires (7) interconnect first attachment points (6) in the area of the distal ends of the lower segments (4) and the bracing wires (8) connect the first attachment points (6) to the hub (3).

Abstract: One feature pertains to an acoustic attenuation device. The acoustic attenuation device comprises a fan assembly, the fan assembly including at least one fan module that directs airflow in at least one direction, wherein the at least one fan module includes a top surface and a bottom surface, a plurality of air deflectors mounted to the top surface and the bottom surface of the at least one fan module, wherein the plurality of air deflectors include a plurality of surfaces, and wherein at least one of the plurality of surfaces is an angled surface that redirects the airflow 90-degrees, and acoustic attenuating foam, wherein the acoustic attenuating foam has a two-dimensional (2-D) surface and is applied to interior surfaces of the plurality of surfaces.

Abstract: An impeller for a pump is disclosed herein. The impeller can include a hub having a fixed end and a free end. The impeller can also have a plurality of blades supported by the hub. Each blade can have a fixed end coupled to the hub and a free end. The impeller can have a stored configuration and a deployed configuration, the blades in the deployed configuration extending away from the hub, and the blades in the stored configuration being compressed against the hub.

Abstract: The gas turbine intake can have a swirl housing having an inlet portion fluidly connecting an exhaust conduit, an annular outlet defined around a central axis and fluidly connecting a turbine gas path, a swirl path extending circumferentially around the central axis from the inlet portion to a circumferential outlet, the circumferential outlet fluidly connected back into the inlet portion, and vanes located in the swirl housing, the vanes circumferentially interspaced from one another relative the central axis and located radially inwardly from the swirl path relative the central axis, the swirl path being free of the vanes.

Abstract: Methods and systems for manipulating surface topology of additively manufactured fluid interacting structures, such as additively manufactured heat exchangers or airfoils, and associated additively manufactured articles, are disclosed. In one aspect, an article which interacts with a fluid is imparted with surface topology features which affect performance parameters related to the fluid flow. The topological features may be sequenced, combined, intermixed, and functionally varied in size and form to locally manipulate and co-optimize multiple performance parameters at each or selectable differential lengths along a flow path. The co-optimization method may uniquely prioritize selectable performance parameters at different points along the flow path to improve or enhance overall system performance.

Abstract: A set of compression stage(s) of a turbomachine, forming an annular fluid passage and comprising at least one annular stator platform and/or at least one annular rotor platform having an outer longitudinal profile inclined (ISi/IRi) inwards and upstream with respect to a nominal profile of the fluid stream, where the inclination (ISi/IRi) of the outer longitudinal profile of the or each of the annular platforms, relative to the nominal profile of the fluid stream, oscillates along the circumference of the annular platform or platforms, between a maximum value in front of the blades of the annular platform and a minimum value between each pair of adjacent blades of the annular platform.

Abstract: Flow control devices and structures for turbomachines. In some examples, the flow control devices and structures include various arrangements of flow guiding channels, partial height vanes, and other treatments located on one or both of a shroud and hub side of a turbomachine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.

Abstract: A gas turbine engine article includes a substrate that has a pre-bond surface that includes a serpentine groove. A coating is disposed on the pre-bond surface and mechanically interlocks with the serpentine groove.

Abstract: An aircraft defining a longitudinal direction and a lateral direction is provided. The aircraft includes: a fuselage; an engine mounted at a location spaced from the fuselage of the aircraft, the engine comprising a plurality of rotor blades; and a fuselage shield attached to or formed integrally with the fuselage at a location in alignment with the plurality of rotor blades along the lateral direction, the fuselage shield comprising a first layer defining a first density and a second layer defining a second density, the first density being different than the second density.

Abstract: A blower includes a first tower and a second tower spaced apart from each other each having discharge ports that face each other. A gate is movably installed in at least one of the first tower or the second tower to protrude into and out of the space between the first and second towers to change a flow of air discharged out of the discharge ports. A guide motor may be configured to move the gate. The discharge ports may be provided at a rear side of the space to discharge air toward a front of the space, while the gate may be moved to cover the front side of the space to guide air upward.

Abstract: A secondary flow suppression structure includes: a turbine rotor blade including an outer shroud; a turbine stator vane located rearward of the turbine rotor blade and including an outer band; a seal surface facing the outer shroud at a radial outside of the outer shroud; a fin projecting from the outer shroud toward the seal surface; and a cavity formed between the seal surface and the turbine stator vane, formed in an annular shape extending in a circumferential direction, and provided with an opening portion opening radially inward on a virtual surface of the seal surface extending rearward. A front end of the outer band is positioned at the same height as the virtual surface in a radial direction, or positioned radially inward of the virtual surface.

Abstract: A blower includes a lower case provided with an inlet; a first tower that extends upward from the lower case and is formed with a first outlet; a second tower that extends upward from the lower case and is provided with a second outlet; a fan that is rotatably disposed on the lower case; a first air flow converter that is disposed at the first tower; and a second air flow converter that is disposed at the second tower, each of the first air flow converter and the second air flow converter including: a guide board that is disposed inside the first tower or the second tower or protrudes through a first wall or a second wall; an upper gear that rotates in engagement with an upper portion of the guide board; a lower gear that rotates in engagement with a lower portion of the guide board; a shaft that is connected to each of the upper gear and the lower gear to rotate together; and a motor that is connected to one of the upper gear and the lower gear to provide a driving force.

Abstract: A propulsion system includes a drive shaft, a fan, a fan shaft, and a reduction device coupling the drive and fan shafts. The reduction device includes a first reduction stage and a second reduction state, and include a sun gear, centered on an axis of rotation of the drive and fan shafts and driven in rotation by the drive shaft, a ring gear, coaxial with the sun gear and that drives the fan shaft in rotation about the axis, and planet gears distributed circumferentially about the axis between the sun and ring gears, each planet gear including a first portion which is meshed with the sun gear and a second portion which is meshed with the ring gear, a diameter of the first portion being different from a diameter of the second portion, and an oil transfer bearing positioned between the fan and the reduction device.

Abstract: A method of determining the location and size of a crack in a blade includes measuring a time of arrival of a tip of the blade at an angular position in a rotation, using the time of arrival to calculate a displacement of the tip of the blade, and using the displacements to calculate a first vibration condition and a second vibration condition for the blade.

Abstract: Embodiments of bladed rotors and methods for manufacturing bladed rotors are provided herein. The method for manufacturing bladed rotors includes providing a workpiece including a first rotor blade segment. The first rotor blade segment includes a first platform portion on a radially outward end portion of the first rotor blade segment. Further, the method includes forming a second rotor blade segment, by additive manufacturing, removing a side portion of the first platform portion, and removing a side portion of the second rotor blade segment, whereby a second platform portion remains on a radially outward end portion of the second rotor blade segment.

Abstract: A rotor blade for a wind turbine, comprising a rotor blade root for fixing the rotor blade to the hub of a wind turbine, an inner blade portion which extends from the rotor blade root in the direction of a longitudinal extension of the rotor blade, and a rear edge segment for increasing the depth of the rotor blade in the profile depth direction in the region of the inner blade portion, wherein the rear edge segment is fixed to the inner blade portion and has an edge facing the inner blade portion. A cover lip is proposed which overlaps with the edge and is arranged in a transition region from the inner blade portion to the edge of the rear edge segment.

Abstract: Disclosed is a wind turbine blade comprising a first blade section and a second blade section connected to the first blade section. The wind turbine blade comprises a first down conductor for conducting lightning current to ground. The blade further comprises one or more lightning receptors at or in proximity of an external surface of the wind turbine blade. A smallest distance from a first lightning receptor of the one or more lightning receptors to an interface between the first blade section and the second blade section may be less than or equal to a chord length of a chord of the wind turbine blade at the interface between the first blade section and the second blade section.

Abstract: The invention relates to a fluid pump device, in particular for the medical application, with a compressible pump housing and rotor, as well as with an actuation means which runs in the sleeve and on whose end the fluid pump is arranged. In order to utilize all possibilities of a space-saving arrangement of the respective pump housing of the rotor, which is compressible per se, and as the case may be, a bearing arrangement, the mentioned elements are displaceable to one another in the axial direction compared to an operation position. In particular these elements may be end-configured by way of an axial movement of the drive shaft after the assembly.

Abstract: Sealing ring for a wheel of an aircraft turbomachine turbine, the ring having an annular body extending around an axis of revolution and including an outer surface and an inner surface which is coated with an annular layer of an abradable material, the ring further including an annular wall extending around the annular body and at a radial distance from the body, the annular wall including openings through which cooling air flows by impact on the outer surface, wherein the body and the wall are integrally formed.

Abstract: A pericritical fluid system for a thermal management system associated with a turbine engine may include one or more sensors configured to generate sensor outputs corresponding to one or more phase properties of a pericritical fluid flowing through a cooling circuit of the thermal management system, and a controller configured to generate control commands configured to control one or more controllable components of the thermal management system based at least in part on the sensor outputs. The one or more sensors may include one or more phase detection sensors, such as an acoustic sensor.