Abstract: Provided is a compression system including: at least one impeller; a gear train configured to the at least one impeller; a main drive shaft configured to drive the gear train; and a housing comprising an impeller container configured to house the at least one impeller and a gear train container configured to house the gear train.

Abstract: An arrangement for extracting energy from flowing liquid, such as tidal flows, oceanic currents and water flowing in rivers. The arrangement comprises a support device (12) and a turbine device (1) which is pivotally connected to the support device (12) about a substantially horizontal axis (18). The turbine device includes at least one helical turbine (2; 4), each having an axle connected to an energy converter (22; 24). The turbine device (1) has a proximate end and a distal end, the proximate end being pivotally connected to the support device (12), and the distal end being freely movable in a substantially vertical, circular path in the flowing liquid. This enables the turbine device, in use, to adjust to an operational angle with respect to a horizontal plane. The arrangement is characterized in that the distal end of the turbine device (1) is provided with at least one transverse bar (7), stabilizing the operational angle of the turbine device (1).

Abstract: A turbocharger includes: a turbocharger main body; a bearing hole formed in the turbocharger main body; a turbine shaft rotatably inserted into the bearing hole and having a turbine wheel provided on one end and a compressor wheel provided on the other end; a turbine-side bearing part and a compressor-side bearing part rotatably supporting the turbine shaft and disposed in the bearing hole on a relatively turbine wheel side and on a relatively compressor wheel side, respectively; a cooling oil passage provided radially outside the bearing hole in the turbocharger main body and configured to cool the turbocharger main body with lubricating oil circulated inside; a first oil duct configured to guide lubricating oil after lubricating the compressor-side bearing part to the cooling oil passage; and a second oil duct configured to guide lubricating oil after lubricating the turbine-side bearing part to the cooling oil passage.

Abstract: A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.

Abstract: An inlet portion (31) of a compressor housing (30) forms part of an intake passage, and a drawing passage (35), which extends through the inlet portion (31), draws blow-by gas from outside the inlet portion (31) to inside the inlet portion (31). A throttling portion (47) is formed inside the inlet portion (31) and arranged at a joined portion of the intake passage and the drawing passage (35) so that a cross-sectional passage area at the joined portion is smaller than a cross-sectional passage area of a portion located at an intake air upstream side of the joined portion and a cross-sectional passage area of a portion located at an intake air downstream side of the joined portion.

Abstract: A cooling structure for a turbomachine. In one embodiment, the cooling structure is for a seal slot of the turbomachine. The cooling structure includes a body coupled to a surface of the seal slot. The body includes a passageway on a first surface of the body for providing a cooling fluid to the seal slot. In an other embodiment, a apparatus includes a first component and a second component adjacent the first component. The apparatus also includes a seal slot extending between the first component and the second component, and a cooling structure positioned within the seal slot. The cooling structure includes a body coupled to a surface of the seal slot. The body has a passageway on a first surface of the body for providing a cooling fluid to the seal slot.

Abstract: An air inlet silencer for turbomachines is provided. In one embodiment, the air inlet silencer includes a body, and a plurality of concentric baffles coupled to and axially surrounding the body. In another embodiment, an air inlet system for a turbomachine includes the air inlet silencer, as discussed herein, positioned within a silencer housing. The air inlet system may also include a deflector positioned within the silencer housing adjacent the air inlet silencer. In a further embodiment, a turbomachine includes a turbine coupled to a compressor, and an air inlet system, as described herein, coupled to the compressor.

Abstract: A modular fan housing configured to hold an array of motors and fans is provided. The modular fan housing is configured for use in an air-handling system that delivers air to a ventilation system for at least a portion of a building. The fan housing comprises a plurality of modular units configured to be stacked adjacent to one another in at least one row or column to form an array. The modular units each include an interior surface and have a front end and a back end that define a chamber. The chambers are configured to receive the motors and fans. Sound attenuation layers extend along at least a portion of the interior surface of the corresponding chambers. The sound attenuation layers are positioned between at least some of the adjacent chambers.

Abstract: A gas turbine engine includes a fan section, a turbine section coupled to the fan section through a geared architecture, a first member supporting the geared architecture, and a second member supporting the first member relative to an engine static structure. The first member and the second members are spaced apart from one another at a location. A damper includes opposing ends and extending between the first member and the second member at the location for limiting relative movement between the first member and the second member. A fan drive gear system and a method are also disclosed.

Abstract: A propulsion device is disclosed which is capable of lifting and/or propelling a person or an aircraft, such as a helicopter or airplane, through the air.

Abstract: An exemplary variable vane actuation system for a gas turbine engine includes a vane arm attachable to a vane stem and configured to rotate the vane stem about a radially extending axis. The vane arm includes a claw feature to be press-fit onto the vane stem.

Abstract: A volute device, including: an intake passage including an inner passage and an outer passage; a gas inlet including a first gas inlet and a second gas inlet; and a gas outlet. The gas inlet is disposed at one end of the intake passage, and the gas outlet is disposed at the other end of the intake passage. A first inner passage and a first outer passage communicate with the first gas inlet to suck gas in a semicircle of a circumference direction at between 0° and 180°. A second inner passage and a second outer passage communicate with the second gas inlet to suck gas in another semicircle of the circumference direction at between 180° and 360°.

Abstract: According to an aspect of the disclosure, an annular seal generally includes a hollow member having two ends and an inner surface. The hollow member has a number of depressions formed in and extending around its inner surface. Each of the depressions having a depth that is a function of its distance from one of the two ends.

Abstract: The present invention relates to a turbine assembly with a basically hollow aerofoil, having at least a cavity with an inner wall and having at least an aperture providing access to the cavity, and at least a first impingement device arrangeable within the cavity. The at least first impingement device is self-locking, resilient and preloadable and has at least one locking element to lock the at least first impingement device in place in the cavity via a force fit between the at least one locking element and the inner wall of the cavity wherein the locking element of the at least first impingement device is embodied as a protrusion extending in an assembled state of the at least first impingement device in the cavity basically perpendicular to a surface of a side wall of the at least first impingement device in a direction towards the inner wall.

Abstract: A centrifugal fan includes a fan frame, a stator assembly and an impeller. The fan frame has a base plate portion, a cover plate portion and a lateral wall portion. The cover plate portion has an air inlet, and the lateral wall portion has an air outlet. The impeller includes a rotating member, a plurality of blades and a connection ring. The rotating member is coupled with the stator assembly. Each blade has a windward edge and a lateral edge. The windward edge faces the air inlet, the lateral edge faces the lateral wall portion, and the connection ring is arranged on the windward edges of the blades. The windward edge has a first coupling edge, and the connection ring has a second coupling edge. A part of the windward edge between the first coupling edge and the lateral edge extends downwards in a curved manner, forming a truncating portion.

Abstract: A statorless or nozzleless axial turbine for a turbocharger has an axial turbine wheel that receives a swirling flow of exhaust gas substantially in an axial direction. The turbine includes a sector-divided turbine housing defining a plurality of separate exhaust gas inlets each for receiving a separate exhaust gas stream from an internal combustion engine, the sector-divided turbine housing further defining a plurality of separate angular sector passageways each of which occupies a fractional part of a circumference surrounding the turbine wheel, each angular sector passageway being supplied with exhaust gas by a respective one of the plurality of exhaust gas inlets. The turbine housing assembly defines a separate sector outlet for each angular sector passageway. The turbine housing assembly can include a separately formed heat shroud, and the sector outlets can be formed at least in part by the heat shroud.

Abstract: An assembly for a turbine engine includes a stator vane arrangement and an anti-rotation lug that is rotatably connected to a turbine engine case. The stator vane arrangement includes a platform, an airfoil and an anti-rotation slot. The platform extends circumferentially around an axial centerline and is engaged with the case. The airfoil extends radially from the platform and is arranged circumferentially around the centerline. The slot extends radially into the platform, and is mated with the lug. The lug is configured with a substantially equilateral polygonal geometry.

Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.

Abstract: A system for detecting a defect in a hollow blade includes a pressure sensor mounted within a cavity of the hollow blade, wherein the pressure sensor measures a pressure within the cavity and provides an output indicative of measured pressure; and a controller to receive the output from the pressure sensor, wherein the controller indicates a defect in the hollow blade based upon the received output.

Abstract: A gas turbine engine includes a rotor having at least one rotor bore cavity and a heat exchanger. The heat exchanger is fluidically connected to a conditioning air source and to the rotor bore cavity for flowing air from the conditioning air source to the rotor bore cavity. The heat exchanger is also fluidically connected to a hot fluid source and a cool fluid source for selectively heating and cooling conditioning air flowing to the rotor bore cavity.

Abstract: A method for operating a horizontal axis wind turbine is provided, the wind turbine including: a rotor including a rotor blade, wherein the rotor is rotatably coupled to a nacelle, and the rotor is rotatable about a horizontal rotor axis extending through the nacelle, and the nacelle is rotatably coupled to a tower, the nacelle rotatable in a yaw plane about a yaw axis. The method includes determining a wind direction; determining a yaw angle setting, wherein the yaw angle setting deviates from an alignment of the rotor axis and the wind direction in the yaw plane; yawing the nacelle to the yaw angle setting; and operating the wind turbine for example to generate electricity.

Abstract: A wind turbine control system comprising a thrust sensor and a braking system. The system allows an increase in wind speed to be detected instantaneously and corrective action to be initiated. The system comprises additional features such as deceleration control.

Abstract: The present invention relates a wind turbine comprising a wind turbine tower with a nacelle provided on the top to which a rotor hub with one or more wind turbine blades is rotatably mounted so that they form a rotor plane. A floating foundation having a upper section is mounted to the bottom of the wind turbine tower, wherein the foundation has a buoyant body configured to be installed at an offshore position having a water depth of about 40 m or more. The wind turbine blade comprises an inner blade section coupled to an outer blade section by a pitch junction in which a pitch mechanism is coupled to a pitch control system configured to regulate the pitch of the outer blade section relative to the inner blade section at wind speeds above a first wind speed. This allows the pitching to be used to counteract the tilting of the wind turbine caused by the different thrusts acting on the structure.

Abstract: A propeller assembly comprises two or more blade elements each comprising two or more blade element portions arranged sequentially radially along the blade element. Each of the two or more blade element portions that are radially equi-positioned along corresponding ones of the two or more blade elements together form a blade element portion array. Each of the two or more blade element portions comprise at least one heating element with each one of the at least one heating elements that is located in a correspondingly radially positioned blade element portion being connected to one another to form a heating element array. The two or more heating element arrays are adapted to sequentially heat respective ones of the two or more blade element portion arrays so as to de-ice the blade elements.

Abstract: Multiple horizontal axis type rotors are coaxially attached along the upper section of an elongate torque transmitting tower/driveshaft, The tower/driveshaft projects upward from a cantilevered bearing means, and is bent downwind, until the rotors become sufficiently aligned with the wind to rotate the entire tower/driveshaft, Power is drawn from the shaft at the base. Surface mount, subsurface mount, and marine installations, including a sailboat, are disclosed. Blade-to-blade lashing, and vertical axis rotor blades may also be included. Vertical and horizontal axis type rotor blades may be interconnected along the length of the tower/driveshaft to form a structural lattice, and the central shaft may even be eliminated. Aerodynamic lifting bodies or tails, buoyant lifting bodies, buoyant rotor blades, and methods of influencing the tilt of the rotors, can help elevate the structure. This wind turbine can have as few as one single moving part.

Abstract: The present invention relates to various types of power generation apparatuses and ship propelling apparatuses including a buoyancy body as well as wing portions thereto, which include wing frames with a multistage, lattice web structure foldable and rollable wings which are connected to the wing frames, wherein the power generation apparatus includes a submersible buoyancy body which has one closed end and the other open end as well as a buoyancy space formed therein, a rotary body which is rotatably connected inside the submersible buoyancy body and has a first wing portion mounted on the other end thereof, and a power generation means which is disposed between the submersible buoyancy body and the rotary body to generate electricity.

Abstract: A heli-hoist pad (18) that is incorporated into a wind turbine nacelle (12) in a manner that is optimized for helicopter approach and positioning of the heli-hoist pad (18), such as by being located within a recess (20) in an upper surface (28) of the wind turbine nacelle (12). Heat exchangers (50) may also be positioned within the free flow of wind outside of a nacelle (12) in manners that provide for serviceability while also allowing for optimal positioning of a heli-hoist pad (18).

Abstract: This invention is a Vertical Axis Turbine with blades [0012] which are continuously, accurately, and positively re-positioned during the rotation of the turbine shaft [0017] allowing the turbine to be more effective at transferring the kinetic energy in the moving air\water “flow” to the turbine shaft, it also allows for the turbine to have ancillary benefits that include: dynamic braking during emergency situations, high torque pitch setting for starting at low wind speeds, over speed control, and a zero torque setting. The blade positioning system is comprised of common Industrial Control System components, used to accurately, positively, and independently position turbine blades to be continuously at the optimum angle with respect to the flow direction.

Abstract: The present application relates to the compressor drum of an axial turbomachine. The drum includes a wall of revolution that forms a hollow body. The wall includes two annular retaining surfaces of the blades which mate with corresponding retaining surfaces of the said blades. These surfaces are generally directed away from one another to form a profile which diverges as its distance radially from the outer surface of the wall increases. The retaining surfaces of the drum may be formed on an outer annular body or on inclined annular flanges.

Abstract: The invention provides a hub for a wind turbine, the hub comprising a continuous shell being assembled from at least two shell parts. To improve stiffness of the hub, a plate element is attached within blade flanges of the assembled hub. Due to the combination between shell parts and a plate element, manufacturing and transportation is facilitated while strength and rigidity is ensured.

Abstract: A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.

Abstract: The purpose of the invention is to provide a rotor blade support structure, wherein the concentration of stress near the rotor blade groove in which the rotor blade is embedded is limited even as increase in production cost is limited. A rotor blade support structure, in which rotor blades (30) are embedded in rotor blade grooves (10) provided on a rotor disc (1), wherein the rotor blade groove (10) is provided with circular direction grooves (13) that extend more in the circular direction of the rotor disc than upward from the bottom (14), and shaft center direction grooves (15) that are provided on the end faces (1a, 1b) of the rotor disc (1) in the center of the bottom (14) in the circular direction of the rotor disc and that extend towards the rotor disc shaft center.

Abstract: A gas turbine engine rotor includes a hub having a slot. A blade includes a root received in the slot. An under-root area is provided between the root and the fan hub in the slot. A spacer includes first and second portions that cooperate with one another to provide an adjustment feature with discrete height settings. The adjustment feature provides different radial heights of the spacer. The spacer is arranged in the under-root area beneath the root.

Abstract: A sheath for a fan airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side includes a solid portion to wrap around the airfoil leading edge; a first wing attached to the suction side of the airfoil; and a second wing attached to the pressure side of the airfoil. At least one of the first wing and the second wing extends at least about 35% of the chord of the airfoil.

Abstract: A casting core (200) for a twisted gas turbine engine blade, including: an airfoil portion (202) having: an airfoil base end (208), an airfoil tip end (210), a concave side exterior surface (212), a convex side exterior surface (214), a leading edge (204), and a trailing edge (206). The airfoil portion is twisted in a radial direction from the airfoil base end to the airfoil tip end. The airfoil portion includes a first void (220) between the concave side exterior surface and the convex side exterior surface and extending radially to define the shape of a rib of an airfoil to be cast around the core. A first leading edge surface and a first trailing edge surface of the void are twisted from the airfoil base end to the airfoil tip end.

Abstract: A particular arrangement of vortex generators for an airfoil is described. The vortex generators are provided in pairs, preferably on a wind turbine blade, wherein by arranging the vortex generators according to specified characteristics, a surprising improvement in blade performance is provided over the prior art systems.

Abstract: A gas turbine engine blade (20), including: an airfoil (24) including a pressure side exterior surface (34), a suction side exterior surface (36), and a first rib (130) spanning between the pressure side exterior surface and the suction side exterior surface. The airfoil (24) is twisted from a base end (30) of the airfoil to a tip end (32) of the airfoil. The first rib is twisted from a base end of the first rib to a tip end of the first rib. The pressure side exterior surface, the suction side exterior surface, and the first rib are cast as a monolith.

Abstract: A wind turbine includes a tower having an interior, an exterior, a lower end and an upper end; a nacelle coupled to the tower adjacent the upper end and movable to define at least two yaw positions of the nacelle; a rotor coupled to the nacelle; and an access apparatus disposed about the tower adjacent the upper end thereof, the access apparatus defining a passageway into the nacelle that is exterior of the tower, and the access apparatus providing access to the nacelle in the at least two yaw positions of the nacelle. A method for transporting equipment and personnel to the nacelle using the access apparatus is disclosed. A method for assembling a wind turbine having such an access apparatus is also disclosed.

Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls. A turbulence promoter extends from the outer wall adjacent to the bend in the downstream portion.

Abstract: A turbine blade for a turbomachine has an outer wall which delimits an inner cavity. Cooling fluid flows in the inner cavity. A through duct is arranged in the outer wall through which the cooling fluid flows from the inner cavity to an outside of the turbine blade. The through duct is inclined with respect to a trailing edge of the turbine blade, wherein a marginal portion of an entrance of the through duct is designed on an upstream side to be sharp-edged in relation to other marginal portions of the entrance such that a separation zone of a cooling fluid flow is formed in the through duct. A pair of swirls builds up in the through duct, wherein velocity vectors of the cooling fluid flow between the swirl centers point toward a downstream side of the through duct.

Abstract: A gas turbine engine component subjected to a flow of high temperature gas includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe, a second lobe and a transition region. The first lobe diverges longitudinally and laterally from the metering section and has a first shape. The second lobe is generally opposite the first lobe and diverges longitudinally and laterally from the metering section and has a second shape different from the first shape. The transition region is positioned between the first and second lobes and includes a downstream end adjacent the outlet.

Abstract: A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one row of holes selected from the group consisting of a first row, a second row, a third row and a fourth row, with the first, second, third and fourth rows of holes respectively including the holes numbered PA-1 to PA-10, PB-1 to PB-3, HA-1 to HA-9, and SA-1 to SA-8 located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.

Abstract: A turbine blade for a gas turbine engine with an airfoil portion defined by a perimeter wall surrounding at least one enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the at least one enclosure and a gaspath of the gas turbine engine. The plurality of cooling holes includes at least one row of holes selected from the group consisting of a first row, a second row, a third row and a fourth row, with the first, second, third and fourth rows of holes respectively including the holes numbered PA-1 to PA-10, PB-1 to PB-3, HA-1 to HA-9, and SA-1 to SA-8 located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.

Abstract: A mesh (35) of cooling channels (35A, 35B) with an array of cooling channel intersections (42) in a wall (21, 22) of a turbine component. A mixing chamber (42A-C) at each intersection is wider (W1, W2)) than a width (W) of each of the cooling channels connected to the mixing chamber. The mixing chamber promotes swirl, and slows the coolant for more efficient and uniform cooling. A series of cooling meshes (M1, M2) may be separated by mixing manifolds (44), which may have film cooling holes (46) and/or coolant refresher holes (48).

Abstract: A pump system comprises an electric motor, a pump, a converter and a controller. The electric motor has a rotational output shaft that is rotatable in a first rotational direction and an opposite second rotational direction. The pump has a linearly displaceable input shaft that is movable in a first linear direction and an opposite second linear direction. The converter couples the output shaft to the input shaft such that rotation of the output shaft in the first rotational direction translates the input shaft in the first linear direction, and rotation of the output shaft in the second rotational direction translates the input shaft in the second linear direction. The controller repeatedly reverses rotation of the output shaft to produce reciprocating motion of the input shaft.

Abstract: There is provided a centrifugal compressor apparatus including a centrifugal compressor that centrifugally compresses a gas, an electric motor that rotatably drives the centrifugal compressor, a current detector that detects a drive current I of the electric motor, and an exhaust valve that discharges a compressed gas to a lower pressure section. The centrifugal compressor apparatus (A) detects the drive current I at a sampling cycle ts, (B) updates, as a current threshold, in real time, a value “(moving average)?n×(standard deviation)” for which a plurality of drive currents measured in a sampling period tp serves as a population, where n is a positive number in the range of 3 to 4 and, (C) determines that surging has occurred when the exhaust valve is closed and the drive current I is below the current threshold X, and (D) further opens the exhaust valve to discharge the compressed gas when determining that surging has occurred.

Abstract: A continuous run controller for a dual control compressor system includes an integrated housing containing a pilot valve and a hydraulic unloader valve. Low pressure in the hydraulic oil system opens the hydraulic unloader valve such that the suction valve unloader assembly unloads the compressor. High pressure in an air receiver of the compressor system opens the pilot valve such that the suction valve unloader assembly unloads the compressor.

Abstract: A method is used to control a torque of an electric motor of an electro-hydraulic system. The method includes selecting a value of a set point torque depending on a current pressure in a hydraulic circuit of the electro-hydraulic system. The method also includes determining a control signal for controlling the torque of the electric motor using a target torque and the set point torque.

Abstract: A micropump configured to control flow of an insulation fluid includes: a rectangular channel 370 configured to have a rectangular shape in which a movement passage of the insulation fluid; a planar electrode forming section 310 configured to be formed inside the rectangular channel and have a planar shape for applying an electric field; an inflow section 320 configured such that the insulation fluid flows in; and an outflow section 330 configured such that the insulation fluid flows out. Since an insulation fluid with low conductivity in a range of 10?10 to 10?12 S/m is transported with a simple technical structure without using a complicated component, it is possible to obtain the advantage of cost saving and application to various minute dynamics devices.

Abstract: A pump system includes a plurality of pump assemblies. Each pump assembly having a power assembly and a fluid assembly. Each power assembly of each pump assembly includes a crankshaft, an input connection, and an output connection. The input connection of one pump assembly among the plurality of pump assemblies connected to the output connection of one pump assembly among the plurality of pump assemblies; at least one lead pump assembly within the plurality of pump assemblies configured to be connected to a prime mover commonly driving the plurality of pump assemblies. Also included is a method of pumping pressurized fluid to a site.