Abstract: A fan module includes a hub, a plurality of fan blades, and a ring frame. The hub is configured to rotate about a central axis. The plurality of fan blades surround the hub. Each of the plurality of fan blades includes a first end portion connected to the hub and a second end portion opposite to the first end portion. The ring frame is connected to the second end portion of each of the plurality of fan blades. The ring frame includes a first surface facing the plurality of fan blades and a second surface opposite to the first surface, and the first surface is a curved surface.

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.

Abstract: A fan device includes a hub and a plurality of fan blades. Each of the fan blades includes a driving surface, and the driving surface includes a first tooth column and a second tooth column. The first tooth column includes a plurality of first skin-tooth units. Each of the first skin-tooth units includes a first body. A first middle ridge and two first side ridges protrude from a surface of the first body, and a groove is formed between two adjacent first skin-tooth units. The second tooth column includes a plurality of second skin-tooth units. Each of the second skin-tooth units includes a second body and an extension element. A second middle ridge and two second side ridges protrude from a surface of the second body, and the extension element is located in the groove and includes an extension rib.

Abstract: This composite material blade, which is formed using a composite material including reinforcing fibers and resin, and which has a positive pressure surface and a negative pressure surface, is provided with a ventral part, being the part on the positive pressure surface side in a blade thickness direction, which is the direction joining the positive pressure surface and the negative pressure surface, a dorsal part, being the part on the negative pressure surface side in the blade thickness direction, and a metal shield portion which is provided on the leading edge side, being the upstream side in a flow direction in which a fluid flows, wherein: the metal shield portion includes a main body portion provided on the leading edge side, and an embedded portion which is provided on the trailing edge side, being the downstream side in the flow direction, of the main body portion, and which is provided between the ventral part and the dorsal part; and the plate thickness of the metal shield portion in the blade thick

Abstract: A turbine section for a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first outlet, and a second turbine with a second inlet. The turbine section includes an inter-turbine duct extending from the first outlet to the second inlet and configured to direct a flow along a flow direction. The inter-turbine duct is defined by a hub and a shroud. The turbine section includes at least a first splitter blade positioned between the hub and the shroud. The first splitter blade includes a pressure side, a suction side, and at least one vortex generating structure having a leading end opposite a trailing end positioned on the suction side such that a first angle is defined between the vortex generating structure and the flow direction. The vortex generating structure extends in a radial direction from the suction side toward the hub.

Abstract: A turbo compressor housing includes a main compressor housing body and an outside portion between an air intake inlet and the main compressor housing body. The outside portion is configured to adapt the turbo compressor housing to interchangeably connect with one of (1) a hose and (2) a V-band connection and flange such that in a first configuration the hose is connected to the outside portion and in a second configuration the V-band secures the flange to the outside portion.

Abstract: Methods and systems are provided for a swirl generating device upstream of a compressor including a method, a system, and an apparatus for actuating the swirl generating device, which is located in a ring-shaped duct, adjust a swirl of air flowing through the ring-shaped duct to the compressor in response to engine operating conditions.

Abstract: A direct mold includes a plank frame and a mold surface body held in shape by the plank frame. The plank frame is made of a plurality of planar panels that are aligned transversely to the longitudinal extension of the rotor blade and are arranged spaced with respect to each other in the direction of the longitudinal extension of the rotor blade. The panels of the plank frame have recesses, into which the mold surface body is inserted and which reproduces in its sequence in the plank frame mainly a progression of a contour of a part of a rotor blade profile. The mold surface body has a layer structure that includes a support layer and a sandwich layer. The support layer is made of rails that are aligned in the longitudinal direction of the rotor blade in a manner bridging the distances between the panels.

Abstract: This supercharger for a motorcycle is driven by power of a crankshaft of a combustion engine, and compresses intake air to be supplied to the combustion engine. The supercharger has an impeller of a centrifugal type, and an intake air control valve is disposed on the upstream side of the impeller of the supercharger with respect to a flow direction of the intake air. The intake air control valve is disposed so as to face a suction port of the supercharger in the flow direction of the intake air. The intake air control valve adjusts the amount of the intake air flowing into the impeller, and in addition, provides a preswirl to the intake air flowing into the impeller.

Abstract: A compressor (2) characterized by being equipped with: a rotary shaft (12); multiple impellers attached to the rotary shaft; a main flow path that guides a fluid from the prior-stage impeller to the latter-stage impeller; a chamber (31) that forms a circle centered around the axial line and connects to the main flow path; a suction nozzle (32) that guides the fluid from the outer circumferential side toward the inner circumferential side in the chamber; multiple movable vanes provided in the main flow path at intervals in the circumferential direction of the axial line and capable of moving and thereby adjusting the flow volume of the fluid passing through the main flow path; and a drive mechanism (42) that is provided at one side in the circumferential direction of the suction nozzle (32) within the chamber (31), and that changes the angle of the multiple movable vanes.

Abstract: A fan and an electronic apparatus are disclosed. The fan comprises a housing and a blade wheel. The housing is shaped as a hollow column, a thickness of the housing is less than a preset thickness, a radial air inlet and an air outlet are disposed in a side of the housing, and the blade wheel is mounted in the housing and shaped as a cylinder. The housing is also provided with an axial air inlet disposed in at least one bottom surface of the housing so that air can enter the housing from the bottom surface by rotating the blade wheel. The heat dissipation performance of the fan is improved, the present invention solves the technical problem in the prior art that thinning of the fan in the super-thin electronic apparatus will lead to reduction in heat dissipation performance, and achieving technical effects that the electronic apparatus has high heat dissipation performance while super thinning the electronic apparatus.

Abstract: A centrifugal fan includes a fan frame and a fan impeller received in the fan frame. The fan frame has at least one air inlet and at least one air outlet respectively formed on two sides of the fan frame. The fan impeller has a hub, an extension section outward extending from the hub and multiple blades disposed on the extension section. Each blade has a front end and a rear end. The rear ends of the blades are annularly arranged to together define a virtual geometrical configuration. A flow guide space is defined between the virtual geometrical configuration and the hub. A chord length is defined between the front and rear ends of the blade. The flow guide space has a width larger than or equal to the chord length so as to thin the centrifugal fan and enhance the performance thereof.

Abstract: A hybrid drive engine uses air foil shaped disks of a first configuration for a compressor portion thereof and air foil shaped disks of a second configuration for a turbine portion thereof, whereby the disks exhibit aerodynamic effects of lift. Particularly, the compressor disks are configured to cause aerodynamic lift off of a periphery of the disks, while the turbine disks are configured to cause aerodynamic lift off of an inner hole of the disks. The aerodynamic nature of the disks cause each disk thereof to form two opposing airfoil shapes either head to head or trailing edge to trailing edge across the through hole.

Abstract: An inlet connection piece for an axial compressor, particularly for a turbocompressor, includes an inlet housing (1) in which is arranged a bearing housing (2) with a bearing (3), particularly a radial and/or axial bearing, for a rotor. The bearing housing (2) is connected to the inlet housing (1) by an inlet strut (4) which is connected to the inlet housing in a front cross section. The center of the bearing (3) is arranged axially in the flow direction of a fluid to be compressed behind the area center of the front cross section by at least 0.1-times, particularly at least 0.15-times, particularly at least 0.2-times, particularly at least 0.25-times, the chord length of the front cross section. In addition or alternatively, a fluid passage (5, 6) is formed in the inlet strut (4), and at least portions of this fluid passage (5, 6) form an acute angle with a normal plane relative to the longitudinal axis of the inlet connection piece.

Abstract: A fan structure includes a fan rack including an accommodation open chamber, a center base suspended at the center of the bottom side of the accommodation open chamber and a plurality of connection ribs radially connected between the center base and the inner perimeter of the fan rack, and a fan including a fan body made from a hard plastic or rubber material and rotatably mounted at the center base of the fan rack and a soundproofing molding made from a flexible plastic or rubber material and directly molded on the fan body. Thus, during rotation of the fan to induce currents of air, the flexible material property of the soundproofing molding reduces air resistance and wind noise.

Abstract: A fan includes a casing having an air inlet and an air outlet, an impeller housing located within the casing, an impeller located within the impeller housing for generating an air flow along a path extending from the air inlet to the air outlet through the impeller housing, a motor housing connected to the impeller housing, and a motor located within the motor housing for driving the impeller. A bellows support is provided for mounting the impeller housing within the casing. The bellows support is disposed on a seat connected to the casing. The bellows support extends about the impeller housing and forms a seal between the impeller housing and the casing.

Abstract: A filter frame is removably attachable to a box fan. The filter frame is adapted for receiving a standard HVAC-style filter for removing contaminants from air flow induced by the fan. In this manner, a cost-effective means for filtering a flow of air is provided for residential and commercial settings. The filter frame is adaptable to a variety of standard box fan types of different styles and dimensions. The frame is configured to accommodate standard filters, such as those readily available from retail hardware stores and home centers.

Abstract: A free stream fluid kinetic energy conversion device combines a large diameter freewheeling primary rotor with small diameter secondary power takeoff rotors placed within the lift induced blade tip vortices of the primary rotor. This enables use of high rotational speed generating units and avoids diseconomy of scale in gearbox expense. The device partially recovers otherwise lost blade tip vortex energy. The freewheeling primary rotor transmits no reaction torque to the support structure. Resilient buoyant tether deployment accommodates transient eddy induced structural loads.

Abstract: A disclosed stator vane assembly includes a plurality of stator vane elements supported within a case about an axis. Each of the plurality of stator vane elements includes a platform having a recess on a first side and a tongue on a second side. The tongue overlaps a recess of an adjacent one of the plurality of stator vane elements with at least one of the recess and the tongue includes a crowned surface forming a seal.

Abstract: In one exemplary embodiment of the present invention, a compressor housing for a forced induction system of an internal combustion engine is provided. The compressor housing includes a compressor inlet passage in fluid communication with a compressor volute configured to house a compressor wheel, the compressor inlet passage comprising a wall that is shared with the compressor volute. The compressor also includes a compressor outlet in fluid communication with the compressor volute, the compressor outlet being configured to direct a compressed gas to an intake manifold of the internal combustion engine.

Abstract: A purpose of the invention is to reduce size and weight and to make assembly easier while maintaining high response performance or the like required for a turbocharger for an automobile. A rotor blade upstream flow channel space s2 of a cylindrical portion 22 is gradually reduced from an upstream side toward a downstream side in a swirling direction of exhaust gas e in accordance with a reduction in volume of a scroll chamber s1. That is, a back plate 24 is formed so as to swell out to a rotor blade side gradually from the upstream side toward the downstream side in the swirling direction of the exhaust gas e in accordance with the reduction in volume of the scroll chamber s1. The swelling portion of the back plate 24 approaches a rotor blade 16 beyond a communication portion d, and reaches a position adjacent to a leading edge 16a of the rotor blade 16 at a termination end thereof. Therefore, the flow channel space s2 disappears substantially at this termination end.

Abstract: A propulsion system for a supersonic aircraft includes an engine, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the compression surface towards the engine, and a plurality of vortex generators positioned upstream of the engine. The vortex generators have a height such that when the supersonic aircraft is flown at a predetermined speed, the plurality of vortex generators create a plurality of vortices that propagate partially outside of a boundary layer formed proximate a surface of a supersonic inlet. The vortices cause a high-velocity portion of the airflow to move towards a portion of the engine having a higher sensitivity to changes in stagnation pressure and a low-velocity portion of the airflow to move away from the portion of the engine having the higher sensitivity to changes in stagnation pressure prior to the airflow reaching a face of the engine.

Abstract: A turbine assembly mounted to a pump rotor via mounting bolts. The turbine includes fins extending therefrom for pumping gasses and suspended particles from a semiconductor processing chamber. The tops of the bolts are recessed from the top surface of the turbine in a bolt cavity having an open end. A cap member is mounted over and seals the open end of the bolt cavity via a center bolt. The cap member has a shaped upper surface (conical, parabolic, squared, rounded) for deflecting particles away from the center of the turbine and toward the turbine's fins. The cap member's upper surface can include particle deflecting features such as fins, channels or asymmetric shapes to enhance particle deflection as the cap member rotates.

Abstract: The present invention provides a turbofan and a graphics card with the turbofan. The turbofan comprises: a turbofan assembly which admits air in an axial direction and dispenses air in a radial direction; an inlet fan assembly disposed at an inlet of the turbofan assembly and disposed coaxially with the turbofan assembly: and a driving means for driving the turbofan assembly and the inlet fan assembly to rotate. The turbofan provided by the invention gathers the ambient air to the inlet through the inlet fan assembly disposed at the inlet of the turbofan assembly, so as to change a negative pressure state at the inlet. Consequently, the cooling efficiency of the turbofan is improved effectively and the noise of the turbofan is reduced.

Abstract: A variable geometry turbine comprises a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet; wherein the annular inlet is divided into at least three axially offset annular inlet portions by two or more axially spaced annular baffles disposed between the first and second inlet sidewalls; inlet vanes extending axially into at least one of the inlet portions and defining circumferentially adjacent inlet passages; and wherein each of at least two of said baffles extends radially inboard of inlet vanes which extend into at least one of the inlet portions axially adjacent the respective baffle, and wherein a distance between an inner diameter of a first baffle of said at least two of said baffles and a trailing edge of a radially innermost vane in one of

Abstract: Transition ducts, hot gas path assemblies, and turbomachines are provided. A hot gas path assembly includes an outer support ring, an inner support ring, and a transition duct coupled to the outer support ring and the inner support ring. The transition duct includes a conduit defining a passage extending between an inlet and an outlet. The inlet and the outlet are generally aligned along a longitudinal axis. The transition duct further includes an airfoil disposed within the conduit and configured to alter a hot gas flow direction.

Abstract: A system includes an inducer assembly configured to receive a fluid flow from compressor fluid source and to turn the fluid flow in a substantially circumferential direction into the exit cavity. The inducer assembly includes multiple flow passages. Each flow passage includes an inlet configured to receive the fluid flow and an outlet configured to discharge the fluid flow into the exit cavity, and each flow passage is defined by a first wall portion and a second wall portion extending between the inlet and the outlet. The first wall portion includes a first surface adjacent the outlet that extends into the exit cavity.

Abstract: A turbocharger (15) with variable turbine geometry, having a blade bearing ring arrangement (1) which has a blade bearing ring (2) and a disk (3) which is fixed to the blade bearing ring (2) so as to create a flow duct (4), having guide blades (5?) mounted in the blade bearing ring (2), and having a spacer device (5) which is arranged between the blade bearing ring (2) and the disk (3) so as to set a defined width (B) of the flow duct (4). The spacer device (5) is formed as an inlet guide grate (6) which has movable inlet guide blades (8) which are arranged in each case on a spacer pin (7) which is fixed with its first end (7A) to the blade bearing ring (2). Also, a method for producing a blade bearing ring arrangement (1).

Abstract: The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means.

Abstract: A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.

Abstract: The invention relates to a diagonal fan for gaseous media, with a diagonal impeller (26) having a carrier plate (33) with several vanes (36) arranged thereon, with a guide device (28) that is connected downstream to the diagonal impeller (26) for increasing the pressure of the medium, and with a cover plate (40), which encloses the carrier plate (33) radially and which extends, at least in sections, axially along the carrier plate (33), wherein a gap (43) is formed between the vane ends (37) of the vanes (36) on the carrier plate (33), which extend towards the cover plate (40), and wherein the vane ends (37) of the vanes (36) on the carrier plate (33) and a peripheral face (39) of the cover plate (40), which is allocated to the vane ends (37), can be positioned axially relatively to one another for adjusting a gap width S of the gap (43) with at least one axial adjustment unit (61) (see FIG. 1 for this).

Abstract: A stator of an electric motor or generator comprises a core formed of ferromagnetic material having a plurality of teeth arranged circumferentially about an axis. In one aspect of the invention, at least one retaining member connects the end portions of at least two of the teeth to each other in a manner inhibiting relative movement between said tooth end portions. By inhibiting relative movement between said tooth end portions, vibration is reduced. Vibration can also be reduced by welding interior surfaces of a core to each other. Reducing the vibration reduces the noise emissions of the stator during operation.

Abstract: An aircraft turbine casing configured to carry a set of ring sectors that partly delimits a conduit inside which a gas flow passes through the turbine, including a dynamic mechanism adjusting radial position of ring sectors, an upstream radial lug that connects an upstream end of each ring sector to the casing, and a downstream radial lug that connects a downstream end of each ring sector to the casing. The upstream lug is made as a single piece with the casing and is directly connected to the upstream end of each ring sector.

Abstract: A wind power generation system includes a wind power generation system with turbofans. The system includes an air supply funnel, composed structure of turbofan, several generator components, a control device and an air passage well. The air supply funnel is configured to rise the wind which enters into the wind power generation system, and further wind which is risen drives the composed structure of turbofan to rotate, the operating gear ring connected to the composite structure of turbofan rotating with it; and then drives small gear in generator component which engages with the operating gear ring to rotate in high speed. The generator begins to generate electricity when required rotary speed of the electric generating sets is achieved.

Abstract: The axial compressor has a two-stage guide vane cascade at the discharge-side end of the rotor. The guide vanes of the second stage of the cascade are staggered in the circumferential direction in relation to the guide vanes of the first stage in such a way that vortex streamers created by the guide vanes of the first stage cannot impinge upon the guide vanes of the second stage.

Abstract: A gas turbine according to the invention includes a seal housing in which a leaf-shaped seal is provided and a detection end space, a gas introduction path, and a gas discharge path are also formed. The detection end space is formed at a position on the outside in a radial direction from a leaf-shaped seal, and the gas introduction path has an introduction port formed at a position further on the downstream side than the leaf-shaped seal and also has a radially extending portion extending toward the outside in the radial direction from the introduction port and an axially extending portion extending in the direction of an axis from an end portion of the radially extending portion and reaching the detection end space.

Abstract: A fan assembly is adjustable between two suction modes by alternating the position of the fan assembly on a flat surface, such as a table top. The fan assembly has two separate suction openings, one smaller than the other, which are selectively sealed by the flat surface. The suction openings are bounded by planar edges of an air guide that protrudes outward from a fan casing of the assembly. In one position, a first suction opening is unobstructed by the flat surface while the second suction opening is either partially obstructed or substantially sealed by the flat surface. In another position, the second suction opening is unobstructed by the flat surface while the first suction opening is substantially sealed by the flat surface.

Abstract: A slim fan includes a casing, a fan module and a ring cover. The casing includes an upper casing which has an opening, and a lower casing. The fan module includes a plurality of fans annularly disposed in the opening, and each of the fans has a first side and a second side opposite to each other. The ring cover is connected to the first side of the fans and exposed out of the opening. The height of the fans is equal to that between the upper casing and the lower casing.

Abstract: A regenerative blower includes an annular housing assembly that surrounds a rotating impeller and defines a toroidal flow channel, an inlet to admit fluid to the toroidal flow channel, an outlet to discharge fluid from the toroidal flow channel, a low fluid-pressure region of the toroidal flow channel proximate to the inlet, and a high fluid-pressure region of the toroidal flow channel proximate to the outlet. A non-contact interaction between concentric surface contours of the impeller and the housing assembly form opposed concentric fluid pathways between the impeller and the housing assembly from the high to low fluid-pressure regions of the toroidal flow channel. The opposed concentric fluid pathways are so convoluted as to restrict fluid from flowing therethrough from the high fluid-pressure region of the toroidal flow channel to the low fluid-pressure region of the toroidal flow channel.

Abstract: The aerodynamically shaped, symmetrical cross-sectional profile for the struts or the fairing (7) of struts and service lines in the bypass duct and the core-flow duct of a turbofan engine is defined by a course of the local thickness (T) and a position of maximum thickness (PMT) on both sides over the central chord (C) extending from the leading edge (LE) to the trailing edge (TE) of the strut or fairing (7). In order to avoid flow separations the course of the local thickness (T) between the position of maximum thickness (PMT) and a trailing-edge position (PTE), which is at 95 percent of the chord length, has a first turning point (WP1) with a trailing-edge thickness (TET) and a subsequent second turning point (WP2).

Abstract: An inducer with an exterior housing and/or interior hub that incorporates grooves or vanes that are helical in nature and in counter rotation with respect to the rotation of the blades of the inducer, which grooves or vanes capture fluid rotating with the inducer blades and use that rotation to guide the fluid up along paths formed by the grooves or vanes and into an impeller, pump or other device.

Abstract: The present teachings relate to an air feed device with at least one impeller; with at least one housing that at least partially surrounds the impeller, with at least one intake opening for inward suction of air into an operating space of the impeller, with at least one opening to blow out air from the operating space of impeller. Provision is made that the air feed device has at least one additional through-passage opening for air.

Abstract: Provided is an exhaust pump that is suitable for enhancing durability, processability of connecting opening portions in a pump production stage, and evacuation performance.

Abstract: An air-extracting type heat dissipating apparatus includes a frame, a fan body, a plurality of air-inhaling holes and a plurality of air-exhaling holes. The side portion of the frame has an accommodating space. The fan body is disposed in the frame and has a first side and a second side. The air-inhaling holes are disposed on the side portion of the frame in corresponding to the accommodating space. The air-exhaling holes are disposed on the frame and located on the second side. An air is inhaled into the accommodating space through the air-inhaling holes, and exhaled to the first side through the air-exhaling holes, and then it is exhaled to the second side by the fan body.

Abstract: The invention extends to an air flow device for wind turbines which includes a number of flow paths which assist in the movement of air through the air flow device which assists in increasing the efficiency and power output of the wind turbine. The air flow device includes flow passages alongside a central channel which houses the wind turbine.

Abstract: A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway for a fluid flow and a plurality of interleaved blade stages and nozzle stages arranged axially along the pathway. The plurality of the blade stages includes a last blade stage at a downstream end of the pathway and a next-to-last blade stage upstream from the last blade stage. The plurality of the nozzle stages includes a last nozzle stage between the last blade stage and the next-to-last blade stage and a next-to-last nozzle stage upstream from the next-to-last blade stage. At least one of the next-to-last blade stage and the next-to-last nozzle stage includes aerodynamic elements configured to interact with the fluid flow and to define a throat distribution producing a tip strong pressure profile in the fluid flow.

Abstract: A turbomachine is provided and includes first and second endwalls disposed to define a pathway, each of the first and second endwalls including a surface facing the pathway and first and second blades extendible across the pathway from at least one of the first and second endwalls, each of the first and second blades having an airfoil shape and being disposed such that a pressure side of the first blade faces a suction side of the second blade. A portion of the surface of at least one of the first and second endwalls between the first and second blades has at least a first hump proximate to a leading edge and the pressure side of the first blade, and a second hump disposed at 10-60% of a chord length of the first blade and proximate to the pressure side thereof.

Abstract: A method and apparatus is provided for harnessing the wind energy generated by vehicles passing on a roadway. A roadway is provided with a trench extending from a surface of the roadway. The trench may be provided along an extended stretch of the roadway or as a discrete trench section spaced apart along the roadway. The trench or trench section may be provided near the middle of a lane making up the roadway such that a vehicle travelling on the roadway passes over the trench. In this manner the wind displaced by the passing vehicle is directed into the trench and experienced by a wind turbine or wind generator provided within the trench. The trench is covered by a structure configured to direct the displaced wind inside the trench. The wind turbine converts the kinetic energy of the wind into mechanical energy that is then converted into useable power.

Abstract: An inlet system, including for an auxiliary power unit includes an inlet louver mounted to an inlet duct, the inlet louver defines a multiple of vanes positioned to shield the inlet duct from fluids which fall in direction generally transverse to a free stream airflow.

Abstract: The present invention relates to a ship having a wind power generator, including: a structure installed on a deck on an upper surface of the ship; a wind-collecting tower spaced apart from the structure and installed on the deck such that the height of wind-collecting tower is lower than the height of the structure, and the width of the wind-collecting structure is smaller than the width of the structure; an air duct for conveying wind introduced from the wind-collecting tower; a turbine which rotates by the wind conveyed from the air duct; and a generator which operates in accordance with the rotation of the turbine.