Entries |
Document | Title | Date |
20080206050 | Dual taper fan-motor assembly - A motor-driven fan assembly includes a bracket which couples to a motor assembly and includes an outlet port. A shroud assembly defines a chamber and includes an inlet port. The shroud assembly is received on a bracket and a bearing-supported shaft is driven by the motor assembly and extends through the bracket and into the shroud assembly. At least one fan is coupled to the shaft and received in the chamber. The fan includes a plurality of curved blades positioned between a frustoconical lower cap and an opposed frustoconical upper cap. Rotation of the fan by the shaft results in turbulent air flow through the fan assembly. Dust is generally prevented from settling on the fan blades during operation, thereby preventing non-uniform dust buildup or breakup which may cause excessive vibration and reduce bearing and brush life. | 08-28-2008 |
20080219842 | Turbine Part of a Turbocompressor and a Method of Avoiding Carbon Build-Up in the Turbine Part of a Turbocompressor - A turbine unit of a turbocompressor comprises a turbine wheel having blades and a flow channel for directing exhaust gas onto the turbine wheel. The turbine unit additionally comprises injection means for injecting carbon build-up preventing substance into the flow channel. | 09-11-2008 |
20080219843 | Centrifugal impeller with forward and reverse flow paths - A centrifugal impeller having an inlet and a plurality of outlets the outlets including at least one outlet in a forward direction of the Impeller and at least one outlet in a rearward direction of the impeller. A flow path distance of the outlet in the forward direction can be greater than a flow path distance of the outlet in the rearward direction in order to provide a greater pressure in the outlet having the greater flow path distance. In another embodiment, the flow path volume in the forward direction can be greater than the flow path volume in the rearward direction in order to provide a greater flow volume in the forward direction In another embodiment, the number of flow paths in the forward direction can be greater than the number of flow paths in the rearward direction in order to provide a greater flow volume in the forward direction. The impeller is also used in a gas turbine engine in which the impeller also includes a turbine blade, and the forward directing outlets deliver compressed air to a combustor while the rearward directed outlets bypass the combustor. | 09-11-2008 |
20080240914 | Intermediate casing for a gas turbine engine - An intermediate casing for use in a gas turbine engine comprises inner and outer casing walls | 10-02-2008 |
20080240915 | AIRTIGHT EXTERNAL SHROUD FOR A TURBOMACHINE TURBINE WHEEL - External shroud for a turbomachine turbine wheel, this shroud being formed of ring sectors ( | 10-02-2008 |
20080253885 | Gas turbine engine vane - A gas turbine engine vane has first and second members. The first member has a first surface section forming a suction side of an airfoil of the vane. The second surface section forms leading and trailing portions of a pressure side of the airfoil. The third surface section forms a recess between the leading and trailing portions. The second member is secured to the first member and has a first surface section forming an intermediate portion of the pressure side. a leading protrusion of the second member may be captured by a recess below a lip of the first member. | 10-16-2008 |
20080260528 | Turbocharger - The invention relates to a turbocharger comprising a turbine casing ( | 10-23-2008 |
20080310958 | EXHAUST CASING FOR A TURBOMACHINE - A turbomachine exhaust casing with connection roots between the structural arms of the casing and the annular endplates of the hub of the casing, each of said the roots having a profile that is optimized so as to reduce the level of stress in the connection portions, and thus increase the lifetime of the exhaust casing. | 12-18-2008 |
20090053055 | SEAL ASSEMBLY - A seal assembly ( | 02-26-2009 |
20090081036 | AXIAL FLOW FAN - An axial flow fan according to the present invention comprises an impeller which rotates about a central axis and including a plurality of blades, a hollow member accommodating therein the impeller, a base portion which is arranged at the hollow member and supports the base portion in a rotatable manner, a plurality of inner air guide members each connected to the base portion, and a plurality of outer air guide members each connected to the hollow member. | 03-26-2009 |
20090087310 | Device for Transducing of Power - The present invention relates to a device for transducing and/or converting of wind power into another power, for example electric power, comprising a rotor which is rotary in a tunnel tube which is mounted on the upper end of a tower the rotor having an outer ring, an inner ring and a number of blades or vanes, which extend between the rings, the outer ring having a depression extending between the edges for a belt or the like which extends to a shaft on the underside of the tunnel tube for rotation thereof on rotation of the rotor. | 04-02-2009 |
20090110551 | AXIAL FLOW FAN - The present invention provides an axial flow fan including an impeller that has a plurality of rotor vanes and is rotatable about a central axis, a motor that rotary drives the impeller, a base portion that supports the motor, a housing that has an intake vent, an exhaust vent, and an inner peripheral surface to surround the impeller and the motor, and a plurality of stator vanes that respectively connects the base portion and the housing, wherein the inner peripheral surface has a first inner peripheral surface formed to increase a distance from the central axis toward the intake vent or the exhaust vent in an axial direction, and there is formed a recess between the first inner peripheral surface and a stator vane that is included in the plurality of stator vanes and faces the first inner peripheral surface. According to the above described configuration, airflow is allowed to smoothly pass through the housing, resulting in a decrease in noise generated in the axial flow fan. | 04-30-2009 |
20090116959 | Turbo-Molecular Pump and Method of Assembling Turbo-Molecular Pump - To improve the assembling efficiency of a urbo-molecular pump having a structure in which the outside diameter of a rotor blade on the exhaust port side is smaller than the outside diameter of a rotor blade on the intake port side. | 05-07-2009 |
20090148282 | 3D CONTOURED VANE ENDWALL FOR VARIABLE AREA TURBINE VANE ARRANGEMENT - A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing. | 06-11-2009 |
20090191053 | Diaphragm and blades for turbomachinery - A diaphragm for an axial flow turbomachine, in which outer shrouds of adjacent fixed blades in a row of blades contact each other circumferentially to form a circumferentially continuous load path. Inner shrouds of the blades only contact each other on contact faces oriented to transmit loads in the radial and/or axial directions of the turbomachine. | 07-30-2009 |
20090246013 | Compact Low Noise Efficient Blower for Cpap Devices - A blower for providing a supply of air at positive pressure in the range of approximately 2 cm H | 10-01-2009 |
20090269194 | COOLING FAN - A cooling fan includes a fan housing, a base, a rotor, a stator, and a fan guard. The fan housing forms an intake and an outlet at two opposite sides thereof, respectively. The base is arranged at the outlet of the fan housing. The stator is mounted on the base. The rotor is rotatably supported by the stator. A plurality of stationary blades extends from the base to the fan housing. The fan guard attaches to the outlet of the fan housing. A cylinder is arranged at a center of the fan guard and attaches to the base of the fan housing. A plurality of guard blades extend radially and outwardly from the cylinder. Each guard blade and the nearest stationary blade define a gap therebetween along a circumference of the cooling fan. | 10-29-2009 |
20090269195 | FAN AND AIRFLOW GUIDING STRUCTURE THEREOF - A fan includes an airflow guiding structure, an impeller and a guiding ring. The outer radius of the airflow guiding structure increases gradually from the top to the bottom of the airflow guiding structure. The airflow guiding structure includes a plurality of fins and a first space for accommodating a circuit device. The impeller is disposed on the airflow guiding structure and the impeller has a hub and several axial-flow blades disposed around the hub. The guiding ring is connected with the axial-flow blades. An inlet is formed on the top of the guiding ring, and an outlet is formed between the bottom of the guiding ring and the outer surface of the sidewall of the airflow guiding structure. When the impeller rotates, the airflow enters the fan from the inlet and flows along the outer surface of the sidewall of the airflow guiding structure, then the airflow exits the fan through the outlet. The direction of the airflow passing through the outlet is different from the direction of the airflow passing through the inlet. | 10-29-2009 |
20090280008 | VORTICITY REDUCING COWLING FOR A DIFFUSER AUGMENTED WIND TURBINE ASSEMBLY - A vorticity reducing cowling for a diffuser augmented wind turbine assembly is provided. The diffuser augmented wind turbine assembly includes a shroud, a wind turbine disposed within the shroud, and a diffuser coupled to an outlet of the shroud. The wind turbine includes a wind turbine housing and a plurality of blades rotatably disposed within the wind turbine housing, wherein the plurality of blades providing a swept area. The cowling comprises a body disposed upstream of the plurality of blades. The body includes an inlet end defining a first opening, the first opening having a first area. The body includes an outlet end defining a second opening, the second opening having a second area that is less that the first area. The second area is less than the swept area of the plurality of the blades. | 11-12-2009 |
20090280009 | WIND TURBINE WITH DIFFERENT SIZE BLADES FOR A DIFFUSER AUGMENTED WIND TURBINE ASSEMBLY - A wind turbine for a diffuser augmented wind turbine assembly is provided. The wind turbine comprises a wind turbine housing, a hub mounted within the wind turbine housing, and a plurality of blades rotatably coupled with the hub and radially extending from the hub. The plurality of blades includes a first blade and a second blade, wherein the first blade includes a surface area and/or a maximum width that is greater than a surface area and/or a maximum width of the second blade to increase the efficiency of the diffuser augmented wind turbine assembly in variable speed winds. | 11-12-2009 |
20090304502 | PRE-DIFFUSER FOR CENTRIFUGAL COMPRESSOR - A diffuser system for a compressor for a gas turbine engine, the compressor having an impeller and the gas turbine engine having a combustor and a fuel injector proximate to the combustor, includes a first diffuser and a second diffuser. The first diffuser is configured to receive compressed air from the impeller. The second diffuser is coupled to receive the compressed air from the first diffuser. The second diffuser comprises a housing comprising a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The first wall or the second wall, or both, further form an opening through the first and second walls for the fuel injector to pass through when removed from the combustor. | 12-10-2009 |
20100021293 | Slotted compressor diffuser and related method - A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction. | 01-28-2010 |
20100068048 | STATOR VANE PROFILE OPTIMIZATION - An airfoil for a stator vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I is provided. The profile is carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform. | 03-18-2010 |
20100080697 | INTEGRATED GUIDE VANE ASSEMBLY - An integrated outlet guide vane assembly for turbomachinery typically includes at least one outlet guide vane and at least one bifurcation having a leading edge and a trailing edge. The turbomachinery has a central axis of rotation and a defined direction of rotation about the axis. The guide vane comprises an airfoil having a leading edge and a trailing edge and has a non-zero angle of lean in the direction of rotation and a non-zero sweep angle relative to a line perpendicular to the central axis. The leading edge of the bifurcation has a non-zero angle of lean in the direction of rotation and a non-zero sweep angle relative to a line perpendicular to the central axis. The trailing edge of the vane is faired into the leading edge of the bifurcation. | 04-01-2010 |
20100092283 | AIRFOIL SHAPE FOR A COMPRESSOR - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. | 04-15-2010 |
20100092284 | AIRFOIL SHAPE FOR A COMPRESSOR - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. | 04-15-2010 |
20100119366 | OUTLET GUIDE VANES FOR AXIAL FLOW FANS - An improved outlet guide vane system is disclosed for axial flow fans. Construction details are described which reduce losses in the end wall regions of the vanes, particularly for axial flow fans operating at low flow coefficient with strong localized swirl associated with upstream rotor tip clearance flows. In the preferred embodiment, the vane spanwise airfoil stacking line is approximately straight, while leaning circumferentially toward the incoming swirl flow over the majority of the radial span. The stacking line then curves abruptly in the opposite direction over the radially outboard spanwise portion, so as to lean away from the incoming swirl at the vane tip station. The radially outboard portion of the vanes simultaneously include a gradual increase in vane stagger angle, vane camber angle and vane chord. The vane may also include an axial sweep component. | 05-13-2010 |
20100135781 | BLADE ROW OF AXIAL FLOW TYPE COMPRESSOR - In a blade row of an axial flow type compressor in which a rotor blade row and a stator blade row are alternately arranged in an axial direction, the stator blade row | 06-03-2010 |
20100172754 | Stator Casing Having Improved Running Clearances Under Thermal Load - A turbine power generation system, comprising a stator including a shroud and a rotor rotatably situated within the shroud, wherein the shroud is structured such that the inner diameter of the inner surface of the shroud reduces when the inner surface is exposed to a thermal load. The reduction of the inner diameter allows a minimum blade-casing clearance to be achieved during steady-state operation instead of during transient operations. Blade-casing clearance is configured to be greatest at when the engine is in a cold, stationary position. The clearance is further configured to decrease as thermal load increases until a steady-state, thermal equilibrium is achieved. The clearance grows during shutdown as the stator and rotor begin to cool. | 07-08-2010 |
20100183434 | Exhaust gas turbocharger for an internal combustion engine - In an exhaust gas turbocharger for an internal combustion engine, including a turbine housing and a rotor, the housing having an exhaust gas guide section and the rotor including a turbine wheel and a shaft connected to the turbine wheel which is driven by exhaust gas, and a control device for controlling the exhaust gas flow to the turbine wheel comprising an annular guide vane structure and an axial slide supported on a contour sleeve mounted to the turbine housing remote from the rotor and extending toward the rotor and forming also the turbine exhaust gas discharge duct, the axial slide includes a cavity accommodating the guide vane structure. | 07-22-2010 |
20100196154 | TURBINE BLADE CASCADE ENDWALL - Provided is a turbine blade cascade endwall that is capable of suppressing a vortex generated on a suction surface of a turbine stator blade and that is capable of reducing secondary-flow loss due to this vortex. A turbine blade cascade endwall that is positioned on a tip side of a plurality of turbine stator blades arranged in a ring form is provided with a pressure gradient alleviating part that alleviates a pressure gradient generated in the blade height direction at a suction surface of the turbine stator blades due to a clearance leakage flow, leaking out of a gap between a tip of a turbine rotor blade located on the upstream side of the turbine stator blades and a tip endwall disposed facing the tip of this turbine rotor blade. | 08-05-2010 |
20100209238 | TURBINE VANE AIRFOIL WITH TURNING FLOW AND AXIAL/CIRCUMFERENTIAL TRAILING EDGE CONFIGURATION - An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow. | 08-19-2010 |
20100209239 | VANE - A vane for a duct, such as an exit guide vane for an exhaust duct of a gas turbine engine, comprises a vane plate, an interior strut and an internal wall disposed between the vane plate and the strut. The vane further comprises a fluid inlet in the form of a scoop arranged to direct bypass fluid from outside the duct into a gap between the vane plate and the internal wall. | 08-19-2010 |
20100215489 | DIFFUSER - A diffuser that includes a plurality of radial vanes having a blade count of between 15 and 20, a solidity of between 0.6 and 0.8, and a radius ratio of vane inlet to impeller outlet of less than 1.5. Additionally, a compressor that incorporates the diffuser. | 08-26-2010 |
20100247305 | Vane configurations for steam dryers - A vane configuration for a steam dryer according to an example embodiment of the invention may include a plurality of primary vanes arranged in a radial pattern around (and spaced apart from) a center line. Each of the plurality of primary vanes may be a primary corrugated sheet having alternating primary ridges and primary furrows. As a result, adjacent primary vanes may define a winding flow path, the flow path having an entrance and an exit relative to the center line. The cross-sectional area of the flow path may decrease, increase, or remain constant from the entrance to the exit. | 09-30-2010 |
20100247306 | GAS TURBINE ENGINE WITH 2.5 BLEED DUCT CORE CASE SECTION - A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a structural wall. | 09-30-2010 |
20100247307 | Housing for Axial-Flow Fan - A housing for axial-flow fan includes a frame, a seat and a plurality of stationary blades. The frame has an air inlet and an air outlet. The seat is received in the frame and at a position where the air outlet is formed. Two ends of each stationary blade are respectively fixed to an outer periphery of the seat and an inner periphery of the frame. Furthermore, extending directions of any two adjacent stationary blades jointly define an included angle and all of the included angles formed by all of the stationary blades are of more than two values in degrees, so that the stationary blades are not spaced with equal intervals. Consequently, while sucked air passes by the stationary blades, noises with the same tone can be suppressed effectively. | 09-30-2010 |
20100254809 | STEAM TURBINE STAGE - A stage of a steam turbine, having a rotor extending along a longitudinal axis, has a fixed stage and a movable stage arranged successively along a flow channel for feeding steam in a direction substantially parallel to the longitudinal axis; the fixed stage has an inner ring coaxial with the longitudinal axis, and a number of stator blades arranged radially about the inner ring; each stator blade is fixed to an annular top portion of the inner ring, which has a top surface facing the flow channel and crosswise to the longitudinal axis; and the movable stage has a number of rotor blades arranged radially about the rotor and fixed to the rotor. | 10-07-2010 |
20100272565 | VANE ASSEMBLY WITH REMOVABLE VANES - A vane assembly for a gas turbine engine where each vane is connected to at least one adjacent portion of at least one of the inner and the outer shrouds through a melt-weld connection. The melt-weld connection includes non-metallic heat-meltable material with a metal wire mesh layer trapped therein, the metal wire mesh being heatable to melt the heat-meltable material for formation and breakdown of the melt-weld connection. | 10-28-2010 |
20100272566 | DEFLECTOR FOR A GAS TURBINE STRUT AND VANE ASSEMBLY - A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut. | 10-28-2010 |
20100272567 | HEAT-DISSIPATING FAN HOUSING - A heat-dissipating fan housing includes a casing having a compartment with an impeller section, a stationary blade section, and an airflow concentration section arranged from an air inlet toward an air outlet spaced from the air inlet in an axial direction. A mounting portion is received in the compartment, and an impeller is rotatably coupled to the mounting portion for driving airflows. Stationary blades are interconnected between the casing and the mounting portion and are received in the stationary blade section. Each stationary blade includes a first edge facing the air inlet and a second edge facing the air outlet. The airflow concentration section is between the second edge of each stationary blade and the air outlet in the axial direction. The airflow concentration section concentrates the airflows after passing through the stationary blades. The noise is reduced, the wind pressure is increased, and less electricity is consumed. | 10-28-2010 |
20100278643 | CENTRIFUGAL COMPRESSOR VANE DIFFUSER WALL CONTOURING - Diffusion in the vane island passages of a centrifugal compressor diffuser is in part controlled by contouring the diffuser passage wall with low profile surface variations. The surface variations can be provided in the form of flow boundary disrupting protrusions disposed within the downstream portion of the vane island passages to prevent flow separation. | 11-04-2010 |
20100278644 | GAS TURBINE - A gas turbine is disclosed which includes an annular combustion chamber defined by an inner wall and an outer wall. A stator airfoil row can be defined by an annular inner stator wall and an annular outer stator wall housing a plurality of stator airfoils, and at least a rotor airfoil row defined by an annular inner rotor wall and an annular outer rotor wall housing a plurality of rotor airfoils. A gap is arranged, for example, between at least one of the inner stator wall and the inner combustion chamber wall, and the outer stator wall and the outer combustion chamber wall, upstream of said stator airfoil row. A border of at least one of the inner and outer stator wall facing the gap can be axisymmetric. A zone of at least one of the inner and outer stator wall downstream of the gap and upstream of the stator airfoils can be non-axisymmetric and defines bumps arranged to locally increase the static pressure of a fluid flow passing through said stator airfoil row to increase the uniformity of the static pressure. | 11-04-2010 |
20100284804 | Vertical submerged pump for chemical application - The present invention discloses structural improvement of the vertical submerged pump for chemical application. The present invention is focus on reducing the crystal lump generated from high speed etching process. Structural improvement includes a shaft seal device, a diffuser and an upper inner plate. The shaft seal device offer extra flow resistance to balance the differential pressure between the inner space and pump front casing, the function are prevents air bubbles be sucked into the pump, and reduces flow leakage from the front casing into inner space, also absorbs high-pressure back-flush to avoid liquid splash in dry surface of inner space of support column. The diffuser in the support column offer extra inducer function to guides the liquid from the inner space flowing out to the tank, so as to get a stable liquid level in the inner space, thereby largely reducing splashing of the liquid. And the upper inner plate blocks the residual small amount drops from liquid splashing, to minimize producing of crystals lump from high speed etching liquid. | 11-11-2010 |
20100303617 | Powerless diversion plate of a ceiling air-conditioning circulation machine - A powerless diversion plate of a ceiling air-conditioning circulation machine including a bearing block and a bearing within a circular inflow/outflow hole for installing a diversion disc. The diversion disc includes a plurality of radial separation pieces, and a plurality of conic and ring-shaped diversion pieces are concentrically and outwardly positioned around the connection shaft. Moreover, the diversion disc is separated by the ring-shaped diversion pieces and the radial separation pieces to create a plurality of air inflow/outflow zones. The bottom of the diversion disc has a downward protruding middle part and a staged structure at the rim thereof so as to form a | 12-02-2010 |
20100303618 | WIND POWER STATION WITH DARRIEUS-ROTOR - The power output of a wind power station with a Darrieus Rotor is enhanced by wind guides positioned around the Darrieus Rotor to form a wind concentrator. The wind guides include at least two parallel wind deflection plates, displaced along parallel direction with respect to each other. | 12-02-2010 |
20110038724 | Flow trim for vane-axial fans - A fan comprises a fan housing which includes a fan inlet, a motor which is connected to the fan housing, and an impeller which is removably connected to the motor. The impeller includes an impeller hub, a number of impeller blades which extend radially outwardly from the impeller hub, an impeller leading edge, an impeller trailing edge and an impeller tip. The fan housing includes an inlet shroud which is positioned over the impeller. The inlet shroud comprises an upstream end portion within which the fan inlet is formed and a downstream end portion which is removably connected to a separate portion of the fan housing. The inlet shroud further includes a first section which extends axially from the upstream end portion to approximately the impeller leading edge, a second section which extends axially from the first section to approximately the impeller trailing edge, and a third section which extends axially from the second section to approximately the downstream end portion. The second section comprises a configuration which conforms to the configuration of the impeller tip, and the third section comprises a radius which increases from approximately the upstream end of the third section to approximately the downstream end of the third section. | 02-17-2011 |
20110044809 | OPEN-BLADE ENGINE-COOLING FAN SHROUD GUIDE VANES - To make manifest the above noted desire, a revelation of the present invention is brought forth. A fan assembly ( | 02-24-2011 |
20110058940 | GAS TURBINE - A gas turbine is provided including a compressor, a combustion chamber, a guide vane row and a rotor airfoil row. The guide vane row includes a plurality of guide vane airfoils having a blade and an inner platform. The ratio between the pitch and the leading edge diameter of the guide vane airfoils is between 6.3-7.6 and the ratio between the platform length and the leading edge diameter of the guide vane airfoils is between 4.0-5.5. | 03-10-2011 |
20110081239 | FABRICATED STATIC VANE RING - A strut configuration of a static vane ring used in a gas turbine engine having an enlarged end section at least at one of the opposed ends thereof to be welded or brazed to either an outer or inner duct wall of the vane ring. The enlarged end section provides a inner corner curve with a predetermined fillet radius between the strut and the duct wall. | 04-07-2011 |
20110085902 | Low-Noise Ported-Shroud Compressor for a Turbocharger - Various embodiments of ported-shroud centrifugal compressors are described. In some embodiments a wall of a compressor housing defines a pair of bulb-shaped hollow spaces or “bulbs”, one located proximate the compressor wheel and the other spaced upstream from the wheel, and having a connection therebetween. The downstream bulb is connected to the main flow path of the compressor by a port slot through the wall. The upstream bulb is connected to the inlet area of the main flow path by a passage through the wall. The bulbs can provide acoustic wave cancellation through multiple internal reflections in various directions. In one embodiment, the upstream bulb has a second passage connected to it, facing axially upstream, for receiving a portion of the total flow in a choked-flow operating regime, and conducting that portion through the upstream bulb, through the connection to the downstream bulb, and through the port slot into the main flow path. | 04-14-2011 |
20110097205 | TURBINE AIRFOIL-SIDEWALL INTEGRATION - An arrangement for turbine bucket or nozzle airfoils that accounts for the radial variation of inlet flow angle with the boundary layer of flow adjacent to the inner and outer sidewalls. Local chambering of the airfoil sections in the region of the sidewalls provides an airfoil and fillet with an optimum shape for accommodating the radial distribution of the inlet flow angle for the working fluid in the sidewall region. | 04-28-2011 |
20110135460 | FLUID TURBINE WITH EJECTOR SHROUD - A fluid turbine comprises a turbine shroud and an ejector shroud. The turbine shroud has an axial length L | 06-09-2011 |
20110158797 | SYSTEMS AND APPARATUS RELATING TO COMPRESSOR OPERATION IN TURBINE ENGINES - A compressor of a turbine engine, the compressor including stator blades with shrouds, the shrouds being surrounded, at least in part, by rotating structure and forming a shroud cavity therebetween, the compressor including: a plurality of tangential flow inducers disposed within the shroud cavity; wherein each tangential flow inducer comprises a surface disposed on the rotating structure that is configured such that, when rotated, induces a tangential directional component to and/or increases the velocity of a flow of leakage exiting the shroud cavity. | 06-30-2011 |
20110171018 | TURBINE NOZZLE ASSEMBLY - In exemplary embodiments, a nozzle can include a first flow wall, a second flow wall and a vane disposed between the first and second flow walls, wherein the vane is mechanically coupled to the first flow wall and in contact with the second flow wall. | 07-14-2011 |
20110182726 | AS-CAST SHROUD SLOTS WITH PRE-SWIRLED LEAKAGE - A system for forming a seal slot in a shroud assembly has a first element having a longitudinally extending slot and a second element having a longitudinally extending slot for receiving a portion of the first element. The first element has a pair of opposed surfaces and the second element has a pair of opposed surfaces which are oriented at an angle to the surfaces of the first element. The second element may have a planar portion and a curved portion adjacent the planar portion for forming a slot which allows a flow of fluid to exit the slot at a desired angle. | 07-28-2011 |
20110236201 | METHOD AND APPARATUS FOR RADIAL EXHAUST GAS TURBINE - A radial exhaust gas turbine apparatus has a gas turbine engine that includes a radial exhaust diffuser section and a casing apparatus consisting essentially of polygonal walls, substantially straight plates, and substantially straight sidewalls. The casing apparatus encloses the radial exhaust diffuser section and is configured to direct at least a substantial portion of the gas exiting the radial exhaust diffuser section to an exit in the casing apparatus via an approximately involute path. | 09-29-2011 |
20110243724 | TURBINE AIRFOIL TO SHROUND ATTACHMENT - A turbine airfoil ( | 10-06-2011 |
20110250061 | STATIONARY VANE ASSEMBLY FOR A TURBINE ENGINE HAVING A REDUCED WEIGHT, AND TURBINE ENGINE COMPRISING AT LEAST ONE SUCH STATIONARY VANE ASSEMBLY - A stationary vane assembly of a turbine engine including an inner casing and a high-pressure turbine guide vane assembly including at least two angular sectors including blades, the angular sectors being fixed on the casing, each angular sector including a platform and a fastening tab. The fastening tab protrudes from the platform radially inwardly. The casing includes a first annular groove receiving the fastening tabs, radial retaining pins for the angular sectors being introduced into bores made in the casing and the fastening tabs, the axial retaining pins being axially stopped by a ring mounted in a second annular groove of the casing. | 10-13-2011 |
20110250062 | FLUID TURBINE - A fluid turbine comprises a turbine shroud and an optional ejector shroud. The turbine shroud and/or the ejector shroud are formed from a hard shell and a membrane. The hard shell forms a leading edge, a trailing edge, and an interior surface of the shroud. The membrane forms an exterior surface of the shroud. The resulting construction is lighter than previous turbine shrouds. | 10-13-2011 |
20110305565 | AXIAL FAN APPARATUS, HOUSING, AND ELECTRONIC APPARATUS - An axial fan apparatus including an axial-flow impeller, a drive unit, and a housing. The axial-flow impeller is capable of rotating and includes a plurality of blades inclined with respect to a rotational axis direction. The drive unit rotates the axial-flow impeller. The housing is mounted with the drive unit, and includes a sidewall, and a plurality of slits that circulate gas. The sidewall is provided around the axial-flow impeller. The plurality of slits are provided to the sidewall and inclined with respect to the rotational axis direction in a direction opposed to a direction in which the plurality of blades incline. | 12-15-2011 |
20120014788 | DIFFUSER USING DETACHABLE VANES - A system, in certain embodiments, includes a plurality of detachable, three-dimensional diffuser vanes attached to a diffuser plate of a centrifugal compressor. In certain embodiments, the detachable, three-dimensional diffuser vanes may be attached to the diffuser plate using threaded fasteners. In addition, dowel pins may be used to align the detachable, three-dimensional diffuser vanes with respect to the diffuser plate. However, in other embodiments, the detachable, three-dimensional diffuser vanes may include a tab configured to fit securely within a groove in the diffuser plate. In addition, the tabs of the detachable, three-dimensional diffuser vanes may include indentions that mate with extensions extending from the diffuser plate, wherein the tabs may slide into slots between the extensions and the grooves of the diffuser plate. | 01-19-2012 |
20120020779 | LOW MASS DIFFUSER VANE - A wedge-type diffuser includes a diffuser floor and a plurality of wedge-shaped vanes. The wedge-shaped vanes extend from the diffuser floor and have a top surface, a leading edge and a trailing edge. Each of the wedge-shaped vanes has a slot extending from the trailing edge toward the leading edge. | 01-26-2012 |
20120134797 | MULTI-STAGE RADIAL TURBINE - A multi-stage radial turbine that is capable of reducing the number of bearings and of improving the conversion efficiency is provided. Provided are a plurality of radial turbine rotor blades ( | 05-31-2012 |
20120148396 | FLUID-FLOW MACHINE - BLADE WITH HYBRID PROFILE CONFIGURATION - A blade for use in a fluid-flow machine, where at least one of the meridional flow line profile sections MSLi and MSLo is provided at a distance of max. 35% of the main flow path width from the respective inner and outer main flow path boundaries. The blade has in at least parts of a central area a multi-profile configuration such that at least two partial profiles ( | 06-14-2012 |
20120156028 | TURBINE NOZZLE FOR AIR CYCLE MACHINE - A turbine nozzle for an air cycle machine includes a disk section with a multiple turbine vanes which each extend for a vane height H, a throat width W defined between each of the multiple of turbine vanes, wherein a ratio W/H is 0.745-0.769. | 06-21-2012 |
20120163967 | COMPRESSOR CASING TREATMENT FOR GAS TURBINE ENGINE - An axial flow compressor for a gas turbine engine is disclosed having a casing treatment that includes a shrouded rotor and an airflow member disposed in a passage between a casing and the shrouded rotor. In one form the airflow member is stationary with the casing and in another the airflow member is coupled to rotate with the shrouded rotor. The airflow member can have an airfoil shape in some embodiments. A passage inlet that extracts working fluid and provides it to the passage can be formed between a leading edge of the rotor and a trailing edge. A passage outlet can be formed upstream of the leading edge of the rotor. | 06-28-2012 |
20120171029 | TURBINE ENGINE ROTATING CAVITY ANTI-VORTEX CASCADE - A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates. | 07-05-2012 |
20120201668 | PORTABLE IN-LINE FLUID BLOWER - A portable fluid blower with a housing having a central axis and defining a fluid flow path extending axially between an upstream inlet and a downstream outlet. A fan assembly has a rotary component that is operable to draw fluid into a first stage of the flow path and accelerate fluid incoming at the inlet radially outwardly to against a first housing surface portion that diverts the fluid to a second stage of the flow path. The second flow path stage is defined by facing second and third housing surface portions that cause the fluid to flow substantially fully axially in an annular space extending around the central axis between the first stage and a third stage. The fluid flows from the third stage to and through the downstream outlet. | 08-09-2012 |
20120224957 | Pump and Flow-Guiding Device - A flow-guiding device for an impeller radial pump is arranged radially outside the impeller and extends in a ring-shaped manner with a circumferential carrier ring on which several guide blades are arranged. These latter are formed so as to be resilient in such a manner that when there is a small fluid flow a blade angle points more in the radial direction at an angle of approximately 70° with respect to the longitudinal center axis of the pump. When there is strong fluid flow, the angle becomes smaller and the guide blades bend in a resilient manner at least in regions such that they stand at a smaller angle of between 30° and 40° with respect to the longitudinal center axis of the pump. The fluid is conveyed better in the pump chamber in this way. | 09-06-2012 |
20120243983 | HIGH CAMBER STATOR VANE - A stator vane for a compressor is described. The stator vane has an airfoil root, an airfoil tip, a leading edge, a trailing edge, an inner span region, a midspan region and an outer span region, wherein the stator vane has a normalized camber profile that increases in the outer span region in a spanwise direction towards the tip and is more than 1.4 in the outer span region. | 09-27-2012 |
20120251312 | Stator of an axial compressor stage of a turbomachine - The present invention relates to a stator of an axial compressor stage of a turbomachine featuring a radially outer blade ring forming an outer ring surface, a radially inner blade ring forming an inner ring surface, and several stator blades connected to the blade rings. It is provided that the outer ring surface and/or the inner ring surface has at least in a partial area a changing radius relative to a central axis of the stator both in the axial direction and in the circumferential direction. | 10-04-2012 |
20120301290 | RAM AIR TURBINE - A ram air turbine comprises a turbine housing which mounts a number of circumferentially spaced turbine blades that function predominantly as impulse turbine blades and a number of splitters, each located in between adjacent turbine blades, which function predominantly as a reaction turbine blade but are shorter in length than the turbine blades. The cross section of the turbine housing decreases between its forward and aft ends while the height of both the turbine blades and splitters increases in the same direction such that the tips of the turbine blades and splitters collectively form a substantially cylindrical shape. | 11-29-2012 |
20120321456 | APPARATUS AND METHODS FOR LINEAR ACTUATION OF FLOW ALTERING COMPONENTS OF JET ENGINE NOZZLE - A trans cowl for a jet engine includes a chevron coupled with a linear actuators. The chevron is movable by the linear actuator forward or aft to change a gas flow path formed by an core cowl and thrust reverser translating cowl. In a first position, the chevrons are disposed substantially parallel the gas flow path to attenuate drag and/or loss of engine thrust. In a second position, the chevrons are moved aft to project, or further project, into the gas flow path. In one embodiment, the linear actuator comprises a first component that is coupled with the outer cowl. A second component of the linear actuator is coupled with the chevron. When installed, the linear actuator can be coupled with a controller and an electrical power source. A position sensor coupled with the controller senses a position of the linear actuator and/or the chevron. | 12-20-2012 |
20130011251 | TURBINE WITH RADIAL INLET AND OUTLET ROTOR FOR USE IN BIDIRECTIONAL FLOWS - The present invention relates to a turbine which can absorb energy from bi-directional reversing flows, as is the case of ocean wave energy converters. In the periphery of the bladed rotor ( | 01-10-2013 |
20130022456 | Axial flow action turbine - Axial flow action turbine utilizing the energy of water entering axially and tangentially into a turbine runner with cylindrical hub equipped with radial oriented buckets having cross-section consisting of segments of cylindrical tube where the segments are angularly offset along the bucket's radial axis and where the water exits the turbine runner axially. | 01-24-2013 |
20130101409 | TURBINE COMPONENT INCLUDING AIRFOIL WITH CONTOUR - A turbine engine airfoil structure including an airfoil adapted to extend across a gas passage, and a platform structure defining an endwall located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. A saddle portion is associated with at least one airfoil surface of the airfoil, the saddle portion defining a contour having a first radially outer edge located on the at least one airfoil surface and a second radially inner edge located radially inwardly from the radially outer edge. The contour includes a curvature in a plane extending generally perpendicular to the at least one airfoil surface and passing through the saddle portion, the curvature being radially spaced from the endwall and defining an apex located between the radially outer and inner edges of the saddle portion. | 04-25-2013 |
20130108433 | NON AXIS-SYMMETRIC STATOR VANE ENDWALL CONTOUR | 05-02-2013 |
20130108434 | METHOD FOR MOUNTING A STATOR BLADING OF A TURBOMACHINE, AN ENGINE CASING AND A TURBOMACHINE COMPRISING AT LEAST ONE STATOR BLADING MOUNTED ON THIS ENGINE CASING | 05-02-2013 |
20130142640 | ALTERNATE SHROUD WIDTH TO PROVIDE MISTUNING ON COMPRESSOR STATOR CLUSTERS - A stator for a turbo-machine having a plurality of airfoils extending radially therefrom has a base from which the airfoils depend, and slits disposed in the base, each slit disposed adjacent a pair of airfoils, wherein a first set of adjacent slits and a distance between a second set of adjacent slits varies | 06-06-2013 |
20130142641 | TURBOMACHINE - A turbo machine is provided. The turbo machine comprises a turbo stator having a shroud, a turbo rotor having an impeller within the shroud, a brush seal between the impeller and the shroud, and at least one vane extending from the shroud toward the impeller upstream of the brush seal. | 06-06-2013 |
20130149133 | STATOR VANE SHROUD HAVING AN OFFSET - An example stator vane assembly of a turbomachine includes a shroud having a leading edge, a trailing edge, and at least one circumferential edge. The leading edge is circumferentially offset relative to the trailing edge when installed within the turbomachine. | 06-13-2013 |
20130149134 | FAN - A fan includes a stationary portion, a rotating portion, and an impeller arranged to rotate about a central axis together with the rotating portion to produce an axial air current. The rotating portion includes a rotor holder. The impeller includes a cup portion arranged to cover the rotor holder and a plurality of blades arranged on an outer circumference of the cup portion. The cup portion includes a cup cover portion arranged to extend radially outward from the central axis; a cup cylindrical portion being substantially cylindrical in shape, and arranged to extend in an axial direction from an outer edge portion of the cup cover portion; and a cup through hole arranged to extend through the cup portion at a position overlapping with a portion or boundary between the cup cover portion and the cup cylindrical portion. | 06-13-2013 |
20130149135 | STATOR VANE ARRAY - A stator vane assembly for a gas turbine engine includes circumferentially spaced vanes about a common axis. The array of vanes further includes three or more sub-arrays, which are configured such that the vane spacing in one sub-array is different from the vane spacing in the other sub-arrays. | 06-13-2013 |
20130149136 | STATIONARY BLADE CASCADE, ASSEMBLING METHOD OF STATIONARY BLADE CASCADE, AND STEAM TURBINE - A stationary blade cascade | 06-13-2013 |
20130156571 | FAN WITH FLUID DIVERSION MECHANISM - A fan with a fluid diversion mechanism includes a fan frame structure and a vane wheel, and the fan frame structure has a containing space, an air inlet and an air outlet, and the fan frame structure includes a coaming plate having a plurality of diversion components, and an opening formed at any one of the diversion components and arranged in a direction towards the air inlet, and the vane wheel is installed in the containing space of the fan frame structure, so that when the vane wheel is operated, air current produced by vanes of the fan guides the air current entered from the diversion component to an external side of a retaining platform which is a leeward side, and the air current has an effective coverage for blowing a desired heat source and improves the overall airflow and air pressure of the fan. | 06-20-2013 |
20130170977 | Gas Turbine Nozzle with a Flow Groove - The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow groove extending from the leading edge to the trailing edge. | 07-04-2013 |
20130195641 | VANE ASSEMBLY FOR AN AXIAL FLOW TURBINE - A vane assembly ( | 08-01-2013 |
20130251520 | SCALLOPED SURFACE TURBINE STAGE - A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil. | 09-26-2013 |
20130280060 | COMPRESSOR DIFFUSER HAVING VANES WITH VARIABLE CROSS-SECTIONS - A diffuser is disclosed for use with a compressor. The compressor diffuser may have a ring-shaped generally flat plate, a plurality of first vanes disposed radially around an upper surface of the plate, and a plurality of second vanes shorter than the first vanes. Each of the second vanes may be connected to the plate between adjacent first vanes. The first and second vanes may each have a high-pressure side and an opposing low-pressure side, and each may tilt towards one of its corresponding high- and low-pressure sides at a lean angle that changes along its meridional length. | 10-24-2013 |
20130294905 | FAN - A floor standing pedestal fan for creating an air current includes a base housing an impeller and a motor for rotating the impeller to create an air flow, an air outlet, and a telescopic duct for conveying the air flow to the air outlet. | 11-07-2013 |
20130315726 | TURBINE AND METHOD FOR REDUCING SHOCK LOSSES IN A TURBINE - A turbine includes a rotor and a casing that circumferentially surrounds at least a portion of the rotor. The rotor and the casing at least partially define a gas path through the turbine. A last stage of rotating blades is circumferentially arranged around the rotor and includes a downstream swept portion radially outward from the rotor. A method for reducing shock losses in a turbine includes removing a last stage of rotating blades circumferentially arranged around a rotor and replacing the last stage of rotating blades with rotating blades having a downstream swept portion radially outward from the rotor. | 11-28-2013 |
20140064951 | ROOT BOW GEOMETRY FOR AIRFOIL SHAPED VANE - A vane assembly used for controlling a turning gas flow includes multiple vanes, each of which is bowed toward a pressure side of the vane at the root of the vane. | 03-06-2014 |
20140064952 | ASSEMBLY OF AN AXIAL TURBOMACHINE AND METHOD FOR MANUFACTURING AN ASSEMBLY OF THIS TYPE - The present invention relates to an assembly of an axial turbomachine, comprising at least one outlet guide vane of a compressor and a diffuser arranged downstream of the outlet guide vane in the flow direction. It is provided that the outlet guide vane is connected to the compressor and that the diffuser is connected to the combustion chamber, without there being a direct mechanical connection between the diffuser and the outlet guide vane. The invention furthermore relates to a method for manufacturing an assembly of this type. | 03-06-2014 |
20140079543 | REGENERATIVE-TYPE FLUID MACHINERY HAVING A GUIDE VANE ON A CHANNEL WALL - Disclosed is a regenerative fluid machine having guide vanes on a flow channel wall. The regenerative fluid machine includes a circular plate-shaped impeller having a plurality of vanes radially formed on an outer circumference thereof at regular intervals, casings in which the impeller is housed, and flow channels, each of which has a suction hole and a discharge hole in opposite ends thereof, and which are circumferentially disposed within the casings so as to face the vanes. The plurality of guide vanes having an inclined angle (θ) with respect to a radial direction protrude from the flow channel wall in a rotational direction of the impeller so that a relative inflow angle (β) of the fluid introduced into the impeller grooves is increased and thus an absolute inflow angle (α) is decreased. | 03-20-2014 |
20140093368 | OUTER CASE WITH GUSSETED BOSS - An outer case employed in a gas turbine engine includes a plurality of support member bosses and a plurality of gusseted bosses. The plurality of support member bosses are disposed circumferentially around the outer case for receiving and securing support members that attach the outer case to an inner hub. The plurality of gusseted bosses are disposed circumferentially around the outer case and between the plurality of support member bosses. | 04-03-2014 |
20140133975 | Double Fan Outlet Guide Vane with Structural Platforms - The assembly has a first guide vane having a first end, a second end opposed to the first end, and a second guide vane having a first end, a second end opposed to its first end. A first end structure spans between the first guide vane first end and the second guide vane first end. A second end structure spans between the first guide vane second end and the second guide vane second end. The first guide vane, the second guide vane, the first end structure, and the second end structure are integrally formed together to form a double vane with a continuous outer surface, and a continuous inner surface. | 05-15-2014 |
20140147264 | TURBINE ENGINE STATOR WHEEL AND A TURBINE OR A COMPRESSOR INCLUDING SUCH A STATOR WHEEL - A turbine nozzle comprises a plurality of composite material vanes, each vane comprising an inner platform, an outer platform with attachment tabs on the outside, and at least one airfoil extending between the inner and outer platforms and secured thereto. The attachment tabs of the vanes are engaged on a metal assembly ring supporting all of the vanes, extending continuously along the outer platforms of adjacent vanes, and forming a distinct assembly part between the vanes and a turbine casing. | 05-29-2014 |
20140178192 | STATOR HOUSING AND METHOD THEREOF - A method for fabricating a stator including positioning a cutting device, with a diameter equal to a desired pocket diameter, with respect to pockets in a side of a housing. Each pocket has an end wall with an indentation. The method axially displaces the device to remove material from side and end walls for the pockets to form desired diameters and lengths for the pockets, while leaving a portion of the respective indentation in place. The housing includes a plurality of blades. Each pocket is arranged to receive an engagement assembly for a one-way clutch. Each pocket includes a first opening facing in a second axial direction and a second opening in communication with the first opening and at least partially facing in a circumferential direction. The first side faces the second axial direction and the side walls are in communication with the first and second openings. | 06-26-2014 |
20140212284 | HYBRID TURBINE NOZZLE - A turbine nozzle apparatus for a gas turbine engine includes: an annular inner band; an annular outer band circumscribing the inner band; a plurality of airfoil-shaped structural vanes extending between and interconnecting the inner band and the outer band; and a plurality of airfoil-shaped non-structural vanes extending between the inner band and the outer band, each non-structural vane having a root end received by the inner band and a tip end received by the outer band, such that each non-structural vane is free to move to a limited degree relative to the inner and outer bands. | 07-31-2014 |
20140255179 | LOW PROFILE VANE RETENTION - A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap. | 09-11-2014 |
20140255180 | AXIAL TURBINE - The present invention relates to an improvement of an axial turbine. Thereto, the present invention includes a submerged turbine | 09-11-2014 |
20140301838 | REPAIR OF A GAS TURBINE COMPONENT - A gas turbine component is provided having a repaired vane platform and rail region in which a portion of the vane rail having been damaged during operation is removed. A bar insert is rough machined and is secured within a groove in the rail. The bar insert and rail are finish machined to restore the platform and rail geometry to an original size and condition. | 10-09-2014 |
20140301839 | CONSTRUCTION MACHINE - An efficient and quiet construction machine has a heat exchanger in which the air flowing out from an axial flow fan avoids collision with the engine. The axial flow fan includes a plurality of blade pieces, a fan ring which guides a flow of air to the axial flow fan, a heat exchanger which is disposed on an upstream side or a downstream side of the flow of air with respect to the axial flow fan, and a structure which is disposed on the downstream side of the flow of air with respect to the axial flow fan. The fan ring includes a suction-side rounded part which reduces a flow channel on a suction side and a discharge-side rounded part which expands the flow channel on a discharge side, and each of the blade pieces is inclined at a sweep forward angle from an axial center toward a rotation direction. | 10-09-2014 |
20140308119 | HYDRAULIC MACHINERY - A hydraulic machinery | 10-16-2014 |
20140314560 | COLUMNAR AIR MOVING DEVICES, SYSTEMS AND METHOD - A columnar air moving device can comprise separately formed modular stator vanes in a stator vane assembly. The stator vanes can be arranged in a radial pattern, and can direct air in an axial direction. The modular stator vanes, as well as other components of the stator vane assembly, can be replaced, adjusted, and/or removed from the columnar air moving device. | 10-23-2014 |
20140356157 | WIND TURBINE DEVICE WITH DIVERTER PANELS AND RELATED SYSTEMS AND METHODS - A wind turbine device may include turbine blades being radially spaced and extending vertically, diverter panels being respectively adjacent and radially outward of the turbine blades, an inner support ring coupled to the turbine blades, and an axle coupled to the turbine blades. | 12-04-2014 |
20150016986 | GAS TURBINE COMPRESSOR STATOR VANE ASSEMBLY - A stator vane assembly for a compressor of a gas turbine, in particular of an aircraft engine, including a plurality of stator vanes whose airfoil sections form a stagger angle with an axis of rotation of the compressor, which stagger angle varies along a duct height of the stator vane assembly. Along the duct height from the inside to the outside, the stagger angle increases to a local maximum in a second section adjoining a first, radially innermost section, and decreases to an outer local minimum in a third section adjoining this second section and, along the duct height from the inside to the outside, the stagger angle decreases from the initial value to an inner local minimum in the first, radially innermost section and/or increases from the outer local minimum to a final value in a fourth, radially outermost section adjoining the third section. | 01-15-2015 |
20150071776 | Motor Vehicle Fan Of Reduced Axial Size - A fan for a motor vehicle includes an impeller formed by multiple blades ( | 03-12-2015 |
20150071777 | TURBINE GUIDE WHEEL - A turbine stator wheel of a gas turbine with a plurality of stator vanes spaced apart around the circumference is provided. Two adjacent stator vanes form a passage each between the suction side of the one stator vane and the pressure side of the other stator vane starting from the vane trailing edge, which includes a constant passage portion in which the passage has a substantially constant passage cross-section. The constant passage portion has an inlet area and an outlet area. Each stator vane forms on the pressure side a rear area that extends, starting from the vane trailing edge adjoining the constant passage portion as far as the inlet area of the passage portion, and on the pressure-side forms a front area that extends upstream of the rear area. Each stator vane has on the pressure side a convex pressure-side contour. | 03-12-2015 |
20150110618 | TURBINE NOZZLE HAVING NON-AXISYMMETRIC ENDWALL CONTOUR (EWC) - Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil. | 04-23-2015 |
20150118038 | VANE PACK ASSEMBLY FOR VTG TURBOCHARGERS - A vane pack assembly is provided that can remove the spacers between the upper and lower vane rings to a location outside of the exhaust flow through the vane ring. In particular, the spacers are located within the vanes. Further, the assembly can effectively retain the small blocks used in varying the angle of the vanes on their associated vane pivot posts. A vane pack with such a configuration can use inexpensive parts, eliminate the need for welding of the vane pack and/or simplify the vane pack assembly process. Further, the vane pack can be decoupled from the turbine housing, thereby avoiding problems with differential thermal expansion. | 04-30-2015 |
20150125287 | AXIAL FLOW COOLING FAN WITH CENTRIPETALLY GUIDING STATOR VANES - A generator system that includes an engine and an alternator which is driven by the engine to generate electrical power. A radiator is connected to the engine and an axial fan directs air toward the radiator to cool the radiator. A plurality of static vanes is located between the axial fan and the radiator. Each static vane includes an inner end and an outer end, the inner ends of the static vanes being joined together. The static vanes are curved in a plane orthogonal to the rotation axis in order to direct the air towards the axis, thereby counterbalancing the centrifugal forces. The static vanes may be twisted, the pitch angle increasing from 0 degree at hub to ca. 45 degrees at tip. Additionally, each static vane is attached to the shroud via a third member that extends axially, thereby allowing an axial offset between shroud and static vanes. | 05-07-2015 |
20150147169 | ADJUSTED STATIONARY AIRFOIL - A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor vane, has a decreased surface area over a portion of the airfoil chord length. The decreased surface area compressor vane operates in conjunction with a compressor blade having an increased surface area. | 05-28-2015 |
20150292342 | STATOR ASSEMBLY FOR A GAS TURBINE ENGINE - A vane cluster for a gas turbine engine includes a first end-of-cluster vane, a second end-of-cluster vane, a neighbor vane adjacent to said second end-of-cluster vane; and a multiple of base vanes between said first end-of-cluster vane and said neighbor vane. | 10-15-2015 |
20150292508 | AIR CONDITIONER - A cross-flow fan includes an impeller and a shaft. The impeller includes a plurality of support plates and a plurality of blades. The blades are different in a blade cross section orthogonal to an impeller rotational axis, and each have a plurality of regions arranged in a direction of the impeller rotational axis and a coupling portion formed so as to couple the plurality of regions to each other. A rib is formed on the coupling portion, or formed in a region adjacent to the coupling portion within a range separated away from the coupling portion by up to 20% of a length of the region adjacent to the coupling portion in the rotational axis direction. | 10-15-2015 |
20150300188 | FLOW DEFLECTOR ARRANGEMENT - A flow deflector arrangement is used in combination with a pipe arrangement secured through a component, the flow deflector arrangement comprising: a nut to secure the pipe arrangement to the component, and a shroud for attachment to the component so as to extend at least partially around the pipe arrangement when the pipe arrangement is secured to the component by the nut. The nut has an outwardly directed flange to adopt a position spaced from the component, and the shroud defines at least one deflector surface which, when the shroud is attached to the component, extends away from the component in spaced relation to the pipe arrangement. The flange and the deflector surface cooperate in deflecting a flow of fluid flowing from the component and along the outside of the pipe arrangement such that the flow is deflected generally outwardly from the pipe arrangement with a degree of swirl. | 10-22-2015 |
20150300259 | AIRCRAFT ENGINE - The invention relates to an aircraft engine having an outlet housing ( | 10-22-2015 |
20150307190 | SHROUDED ROTARY ASSEMBLY FROM SEGMENTED COMPOSITE FOR AIRCRAFT - A shrouded rotor assembly for an aircraft. The shrouded rotor assembly comprises a stator hollow structure comprises formed from a plurality of composite angular segments. Each composite angular segment includes: a core arched section of a central hub casing, a peripheral rim section of an external hollow duct and a pair of angularly opposed sliced portions, respectively for one of a pair of guide vanes. The resulting stator hollow structure is a unitary one-piece, integrating together continuously the composite angular segments. The invention typically applies e.g. to aircrafts such as rotary wing aircrafts. | 10-29-2015 |
20150315916 | PLATFORM WITH CURVED EDGES - A gas turbine engine component includes an airfoil and a platform. The airfoil has a pressure side and an opposite suction side. The platform is connected to the airfoil and has a first curved edge to the suction side of the airfoil and a second curved edge to the pressure side of the airfoil. The first and second curved edges extend along a surface of the platform having a neutral elevation with respect to a reference axisymmetrical platform surface for the gas turbine engine. | 11-05-2015 |
20150322851 | FLUID COOLED ELECTRICALLY-ASSISTED TURBORCHARGER - A fluid cooled electrically assisted turbocharger ( | 11-12-2015 |
20150330411 | Flow Rectifier for an Axial Fan - A flow rectifier ( | 11-19-2015 |
20150354580 | PLASTIC PUMP, AND METHOD FOR MANUFACTURING SAME - The present invention relates to a plastic pump and to a method for manufacturing same. The method includes: a pre-manufacturing step for pre-manufacturing an inner body and impeller formed from a fluorine resin material by means of injection molding; a body manufacturing step for manufacturing a complete body, in which the inner body is formed from a fluorine resin and the outer body is formed from a plastic material, by molding the plastic material in a first mold after fixing the pre-manufactured inner body to the first mold; a cover manufacturing step for manufacturing an impeller cover, which is formed from a plastic material, by molding the plastic material in a second mold so as to protect the manufactured impeller; and a finishing step for completing the plastic pump by sequentially assembling the manufactured complete body, the impeller, and the impeller cover. According to the present invention, only a fluid transporting path is lined with the fluorine resin and is thus not easily deformed by temperature regardless of the type of fluid and is resistant to a chemical reaction with a fluid for improved product quality and significant extension of the period over which the pump can be used. | 12-10-2015 |
20150354585 | SLIM FAN STRUCTURE - A slim fan structure includes a fan frame, a top cover closed to a top of the fan frame to define a receiving space in the fan frame, a stator assembly mounted in the receiving space, and a hub fitted around the stator assembly. The fan frame has opposite first and third sides forming an air inlet and an air outlet, respectively, and opposite second and fourth sides having a first and a second side wall formed thereon, respectively. The first side wall includes a protruded portion laterally extended toward the air inlet, and the second side wall includes a stop portion located adjacent to the air outlet. With the air inlet and the air outlet formed on two lateral sides of the fan frame, the slim fan structure has an effectively reduced overall thickness and does not produce noise during operation to largely upgrade the operational performance thereof. | 12-10-2015 |
20150354598 | SHROUDED AXIAL FAN WITH CASING TREATMENT - A fan assembly ( | 12-10-2015 |
20160017734 | AXIAL FLOW ROTATING MACHINE AND DIFFUSER - An axial flow rotating machine having: a rotor that is provided with a plurality of rotor blades; a stator provided with a plurality of stator blades; an axial flow rotating portion formed by the rotor and the stator; and a diffuser connected to the axial flow rotating portion on the downstream side of the axial flow rotating portion. The final blade portion inner-circumferential inner wall, which is a portion of the inner-circumferential inner wall of the axial flow rotating portion, is formed so that the diameter thereof at the trailing edge position of the final blade is smaller than the diameter at the leading edge position of the final blade. In addition, the diameter of all or a portion of the diffuser inner-circumferential inner wall decreases in a direction of a first side in the axial direction, the first side being the downstream side. | 01-21-2016 |
20160017740 | RIFFLED SEAL FOR A TURBOMACHINE, TURBOMACHINE AND METHOD OF MANUFACTURING A RIFFLED SEAL FOR A TURBOMACHINE - A seal of a turbomachine reduces a leakage flow between a first and second component of the turbomachine. The first component has a first surface and the second component has a second surface, wherein the first component is stiff with regard to a first force exerted perpendicularly thereto and the second component is stiff with regard to a second force exerted perpendicularly thereto. The first surface is opposite the second surface, together defining boundaries of a fluid passage for the leakage flow. The first surface has a first surface riffle. A turbomachine has a seal described above, wherein the turbomachine is a gas turbine engine. A method of manufacturing a first component of a turbomachine with a reduced leakage flow between the first component and a second component of the turbomachine includes fabrication of a first surface riffle, in particular by grinding and/or by electrical discharge machining. | 01-21-2016 |
20160017796 | GAS TURBINE ENGINE HAVING A MISTURNED STAGE - A stage of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a row of flow directing components circumferentially disposed about a centerline axis and at least one flow directing component of the row having at least one design characteristic that is dissimilar from a corresponding design characteristic of at least one other flow directing component of the row. | 01-21-2016 |
20160024933 | BLADING WITH BRANCHES ON THE SHROUD OF AN AXIAL-FLOW TURBOMACHINE COMPRESSOR - The invention relates to an axial-flow turbomachine blading comprising a semi-circular row of blades extending radially. Each blade comprises a airfoil and lateral branches or lateral legs. Each branch has an end joined to the airfoil and an end opposite the airfoil. The blading comprises a first shroud segment connected to at least two opposite ends of two adjacent branches of two adjacent blades and/or of the same blade so as to connect the airfoils to the shroud segment via the lateral branches of the airfoils. The blading also comprises a second shroud segment concentric with the first shroud segment. The segments are connected to one another via the airfoils and the branches. The blading forms a rigid casing and is provided by additive manufacturing with a titanium-based powder. | 01-28-2016 |
20160024950 | STEAM TURBINE - The invention relates to a steam turbine | 01-28-2016 |
20160032742 | STATOR SEGMENT - One exemplary embodiment of this disclosure relates to a stator segment. The stator segment includes a first circumferential end face, and a second circumferential end face. Further, the first and second circumferential end faces are misaligned relative to one another. | 02-04-2016 |
20160032927 | FAN ASSEMBLY - A fan assembly includes a body and a nozzle connected to the body. The body includes an impeller, a motor housing, and a motor located within the motor housing for driving the impeller. The impeller has a substantially conical hub connected to the motor, a plurality of curved vanes connected to the outer surface of the hub, and an annular vane connected to the base of the hub. The motor housing has an annular groove for receiving at least the tip of the annular vane, and an annular lip forming a drip edge extending about the motor housing, the annular lip defining an outer peripheral wall of the groove. | 02-04-2016 |
20160090909 | GEARED GAS TURBINE ENGINE WITH REDUCED FAN NOISE - A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean. | 03-31-2016 |
20160115972 | ROW OF AEROFOIL MEMBERS - A row of aerofoil members for an axial compressor, the row comprises a circumferentially extending endwall and a plurality of aerofoils extending radially from the endwall. The endwall is profiled to include an acceleration region and a deceleration region in a location that corresponds to a position of peak fluid pressure. The acceleration region is provided upstream of the deceleration region such that fluid flow through the compressor and adjacent the endwall is accelerated and then decelerated so as to reduce the peak fluid pressure. | 04-28-2016 |
20160130959 | GAS TURBINE ENGINE - A gas turbine engine comprising in axial flow series: a fan having a fan rotor; a series passages defined between adjacent outlet guide vanes for guiding flow from the fan; and a bifurcation. The gas turbine engine further comprises a substantially annular fluid passageway extending from the fan to the bifurcation, the outlet guide vanes being positioned within the passageway. The passageway includes a profiled region. The profiled region includes a first circumferential portion positioned adjacent a second circumferential portion, the first circumferential portion having a first average radial thickness and a second circumferential portion having a second average radial thickness, the first average radial thickness being smaller than the second average radial thickness, wherein the first circumferential portion is positioned in a region corresponding to a circumferential position of the bifurcation, and wherein the profiled region is at an axial position corresponding to the axial position of the outlet guide vanes and the first circumferential portion extends continuously over two or more of the passages. | 05-12-2016 |
20160131157 | PROPELLER PUMP FOR PUMPING LIQUID - Propeller pump for pumping liquid, including: an axially extending tubular pump housing having an inner surface, an axially extending pump core having an envelope surface, at least one axial portion of the pump core enclosed in the pump housing. The pump core includes a propeller having a hub and at least one blade, and at least one guide vane that includes an upstream leading edge and a downstream trailing edge, and that in the circumferential direction includes a pressure side and a suction side. The guide vane extends between the inner surface of the pump housing and the envelope surface of the pump core. At the leading edge of the guide vane a connection angle between the suction side of the guide vane and the envelope surface of the pump core is larger than 90 degrees. | 05-12-2016 |
20160146012 | AIRFOIL WITH STEPPED SPANWISE THICKNESS DISTRIBUTION - An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil. The airfoil has a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil. The spanwise distribution of maximum thicknesses decreases from the root to the tip. In one aspect, the spanwise distribution is stepped between a first portion extending from the root and a second portion extending to the tip. | 05-26-2016 |
20160153294 | FIRST STAGE TURBINE VANE ARRANGEMENT | 06-02-2016 |
20160160665 | GAS TURBINE ENGINE STATOR VANE ASYMMETRY - A gas turbine engine includes an array of airfoils that include first and second segments. The first segment includes a first number of airfoils that are circumferentially spaced from one another a first angular spacing. The second segment includes a second number of airfoils that are circumferentially spaced from one another a second angular spacing. A sum of the first and second number of airfoils corresponds to a total number of airfoils in the array. The first angular spacing is based upon a first effective number of total airfoils in the array that is different than the total number of airfoils. | 06-09-2016 |
20160168998 | TURBOMACHINE HAVING AN ANNULUS ENLARGMENT AND AIRFOIL | 06-16-2016 |
20160169243 | GAS TURBINE ENGINE AIRFOIL SHAPED COMPONENT | 06-16-2016 |
20160177760 | GAS TURBINE VANE | 06-23-2016 |
20160186585 | SECOND STAGE TURBINE NOZZLE WITH EROSION COATING SURFACE FINISH - A second stage turbine nozzle includes a second stage disk portion having a central axis, and a plurality of second stage vanes positioned radially around and attached to the second stage disk portion. Each second stage vane extends a vane height H away from the second stage disk portion and each second stage vane has a first end positioned at a diameter D away from the central axis. The second stage turbine nozzle also includes a plurality of second stage throats defined between radially adjacent second stage vanes. Each second stage throat has a throat width W between radially adjacent second stage vanes. The second stage turbine nozzle also includes a coating on a sidewall of each second stage vane, wherein a surface roughness of the sidewall is between 125 and 200. | 06-30-2016 |
20160186586 | FIRST STAGE TURBINE NOZZLE WITH EROSION COATING SURFACE FINISH - A first stage turbine nozzle includes a first stage hub portion extending axially along a central axis, a first stage disk portion attached to the first stage hub portion and centered on the central axis, and a plurality of first stage vanes positioned radially around and attached to the first stage disk portion. Each vane extends a vane height H away from the first stage disk portion and each vane has a first end positioned at a diameter D away from the central axis. The first stage turbine nozzle also includes a plurality of first stage throats defined between radially adjacent first stage vanes. Each first stage throat has a throat width W between radially adjacent first stage vanes. The first stage turbine nozzle also includes a coating on a sidewall of each first stage vane, wherein a surface roughness of the sidewall is between 125 and 200. | 06-30-2016 |
20160186720 | WIND POWER GENERATION TOWER PROVIDED WITH GYROMILL TYPE WIND TURBINE - The present invention discloses a wind power generation tower. The wind power generation tower, according to various embodiments of the present invention, comprises: a wind collection unit and an energy conversion unit, wherein wind power generation can be implemented by accelerating wind speed even for low speed wind and simultaneously increasing the utilization efficiency of the wind which rotates blades, thereby improving overall power generation efficiency. | 06-30-2016 |
20160194969 | Turbine Vane With Platform Rib | 07-07-2016 |
20160201514 | MID-TURBINE FRAME STATOR WITH REPAIRABLE BUSHING AND RETENTION PIN | 07-14-2016 |
20160376895 | GAS TURBINE ENGINE COMPONENT PLATFORM COOLING - A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least the leading edge portion or the trailing edge portion of the outer surface of the platform. | 12-29-2016 |
20170234134 | Riblets For A Flowpath Surface Of A Turbomachine | 08-17-2017 |