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Vane or deflector

Subclass of:

415 - Rotary kinetic fluid motors or pumps

415182100 - WORKING FLUID PASSAGE OR DISTRIBUTING MEANS ASSOCIATED WITH RUNNER (E.G., CASING, ETC.)

Patent class list (only not empty are listed)

Deeper subclasses:

Class / Patent application numberDescriptionNumber of patent applications / Date published
415208200 Plural and arcuately or circularly arranged in radial plane around runner axis 179
415211200 Downstream of runner 39
415211100 In radial plane with runner blade 4
20090028700APPLIANCE PUMP - A pump for washing appliance is described. The pump has a pump casing in which an impeller is located. The pump casing has an inlet and outlet, and an inlet conduit extending from the inlet at a small angle above the horizontal. The ceiling includes a downwardly extending dividing wall section extending radially from a central location to a side wall of the casing. The dividing wall is positioned between the inlet outlet. The ceiling incorporates a ramped surface rising around the central location, between the outlet side and the inlet side of the dividing wall. The ramped surface is higher adjacent the inlet side than the outlet side of the dividing wall section so that when the impeller is not rotating, air inside the pump chamber will rise up the ramped surface through the inlet and up the inlet conduit.01-29-2009
20090081038Cooling fan - A cooling fan includes a frame (03-26-2009
20090110553Omnidirectional electric fan and fan blade structure - The present invention discloses an omnidirectional electric fan and a fan blade structure. The fan blade structure comprises: a transmission shaft, a lower connection element, an upper connection element and a plurality of fan blades. The fan blades are radiately secured in between said lower connection element and said upper connection element. Each fan blade has a root portion and a wing portion. The wing portion extends from the edge of the root portion toward both sides to form a wider portion at the border of the fan blade. The fan blade structure cooperates with a seat, a cover, a plurality of fan grills and a dynamic source to from an omnidirectional electric fan.04-30-2009
20130115074TURBO MOLECULAR PUMP DEVICE - A control unit, which is integrally mounted on a turbo molecular pump, is provided, in which the control unit can be miniaturized or the manufacturing costs are reduced. An upper casing (05-09-2013
Entries
DocumentTitleDate
20090053054LEAKAGE REDUCING VENTURI FOR DRY LOW NITRIC OXIDES (NOx) COMBUSTORS - Disclosed is a leakage reducing venturi for a dry low nitric oxides (NOx) emissions combustor, the venturi including a substantially annular outer liner, a substantially annular inner liner, a venturi channel defined by the annular inner liner and the annular outer liner, the venturi channel including a forward end and an aft end, a forward weld disposed in proximity to the forward end of the venturi channel, the forward weld being configured to connect the annular outer liner with the annular inner liner, and an aft weld disposed in proximity to the aft end of the venturi channel, the aft weld being configured to connect the annular outer liner with the annular inner liner.02-26-2009
20090196745INLET GUIDE VANE, COMPRESSOR AND REFRIGERATOR - An inlet guide vane is turnably installed about an axis line at a suction port into which a fluid is drawn by rotation of an impeller in order to adjust a suction amount and flow direction of the fluid, the inlet guide vane, and includes: a shaft that is turnably supported by inserting a round bar-shaped shaft main body portion thereof in a bearing sleeve; and a plate-shaped vane main body that is joined with the shaft and projects from an inner periphery surface of the suction port to a central portion of the suction port, the shaft including a flange portion that is provided at a distal end side in a direction of the axis line to join with the vane main body and that extends to an outside in a direction perpendicular to the axis line so as to be extended outward in a radial direction of the bearing sleeve.08-06-2009
20100150710STATOR VANE FOR A GAS TURBINE ENGINE - A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine. The first side wall has a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and is configured to receive a sealing plate. The first side wall also has a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance.06-17-2010
20100158684VANE ASSEMBLY CONFIGURED FOR TURNING A FLOW IN A GAS TURBINE ENGINE, A STATOR COMPONENT COMPRISING THE VANE ASSEMBLY, A GAS TURBINE AND AN AIRCRAFT JET ENGINE - A vane assembly configured for turning a flow in a gas turbine engine includes a stationary main guide vane and an additional guide vane, wherein a leading edge of the additional guide vane is positioned upstream of a leading edge of the main guide vane and wherein the additional guide vane extends a distance along the main guide vane towards a trailing edge of the main guide vane forming a passageway between the additional guide vane and the main guide vane.06-24-2010
20100074744Fabricated Turbine Housing - A turbine housing is provided. The turbine housing includes a tongue diverter to manage the interaction between exhaust gases entering the inlet of the housing and gasses flowing within the housing. The tongue member may also be arranged to produce a constant ratio throughout the turbine housing between the cross-sectional area of fluid passages and the distance between the centroid of that area and the axis of rotation of the turbine. The housing may comprise a pair of half shells that each form a portion of the tongue diverter.03-25-2010
20100074743Air Diffuser For a HVAC System - A diffuser for carrying air flow to an evaporator in an air conditioning system of an automotive vehicle includes an inlet and an outlet, a wall extending between the inlet and the outlet, and a guide vane, extending at least partially between the inlet and the outlet, spaced from the wall by a containing a control region whose area ratio changes along a length of the guide vane.03-25-2010
20130034435VANE ASSEMBLY FOR A GAS TURBINE ENGINE - A vane assembly for a gas turbine engine includes a first platform, a second platform, and an airfoil that extends radially across an annulus between the first platform and the second platform. The airfoil is centered relative to a centerline axis of the second platform and is offset relative to a centerline axis of the first platform.02-07-2013
20130034434VANE ASSEMBLY FOR A GAS TURBINE ENGINE - A vane assembly for a gas turbine engine includes a first vane and a second vane. The first vane and the second vane include an inner platform, an outer platform and an airfoil that extends between the inner platform and the outer platform. The first vane and the second vane are attached at least at one of their inner platforms or their outer platforms with a first attachment mechanism and a second attachment mechanism.02-07-2013
20120183395RADIAL COMPRESSOR DIFFUSER - A radial compressor diffuser for a radial compressor stage includes a flow channel which extends radially outwards and which has a cylindrical inlet cross-section on a first radius which extends radially inwards and a cylindrical outlet cross-section which extends radially outwards. A radial diffuser outlet blade is provided in the region of the outlet cross-section in the flow channel. The outlet blade prevents known disadvantages of traditional bladed diffusers.07-19-2012
20130039754VERTICAL DOUBLE-SUCTION PUMP HAVING BENEFICIAL AXIAL THRUST - Apparatus, including a vertical double-suction pump, is provided featuring a pump casing and a double suction impeller arranged therein on a shaft. The pump casing has a pump casing wall. The double suction impeller has upper and lower shrouds with metal rims configured to form upper and lower isolating annuli between the double suction impeller and the wall of the pump casing in order to impede a recirculation flow from an impeller discharge to be able to act of the upper and lower shrouds and create a controlled axial thrust load from differentiated hydraulic pressure on the upper and lower shrouds. The upper and lower isolating annuli may also be geometrically varied between the upper and lower shrouds of the double suction impeller to create a pressure differential in a direction parallel to an axis of rotation of the double suction impeller.02-14-2013
20090155067NACELLE ASSEMBLY WITH TURBULATORS - A nacelle assembly for a turbine engine has a cowl. The cowl extends along an axis and has an exterior surface spaced from an interior surface. The interior surface forms an air inlet for directing airflow to the turbine engine. A turbulator for creating turbulence is disposed on one of the interior surface and the exterior surface.06-18-2009
20100040463Sealing means - A sealing means for sealing between segments of a component assembly. The sealing means comprises a sealing member having a mating surface for mating with the surface of the segment. The sealing means further comprises a location member removably attached to the sealing member along a transition region therebetween, and also a free end distal to the sealing member. The location member is configured to engage a location feature of the segment so as to locate the mating surface of the sealing member in a fixed position on the surface of the segment relative to the location feature. The location member is configured to be detached from the sealing member along the transition region and be removed from the segment after the sealing member has been bonded to the segment.02-18-2010
20100040462Separation-resistant inlet duct for mid-turbine frames - A transition duct assembly for a gas turbine engine includes an outer diameter surface and an inner diameter surface. A substantially annular flowpath having a radial offset is defined between the inner diameter surface and the outer diameter surface. A curvature distribution of the inner diameter surface includes a first region of increasing slope in a radial direction and a second region of decreasing slope in the radial direction adjacent to and downstream of the first region. The first and second regions are configured to reduce flow separation along the outer diameter surface of fluid traveling along the substantially annular flowpath.02-18-2010
20100028145Flow control arrangement - Flow restrictors (02-04-2010
20130045096REMOVABLE MASK FOR A TURBOMACHINE BLADE OR DISTRIBUTOR SECTOR PLATFORM - A removable mask for a platform or a nozzle sector of a turbine engine blade, the blade or sector configured to be covered in an electrolytic deposit, the mask including a mechanism to engage on the platform and a mechanism to cover outer surfaces of the platform that are not to be covered by the electrolytic deposit.02-21-2013
20130084174STRUT RODS FOR STRUCTURAL GUIDE VANES - A reinforced structural guide vane system includes an outer casing; a center body within the outer casing; a plurality of structural guide vanes extending between and connected to the center body and the outer casing; and a plurality of strut rods extended between and connected to the outer casing and to the center body.04-04-2013
20130084175Stator for Progressive Cavity Pump/Motor - A stator for a progressive cavity pump or motor includes a stator housing and a stator thread made of a material moulded within the housing. The stator housing includes an outer tube and an inner anchor element within. The anchor element has radially disposed apertures and is spaced from outer tube. To fix the anchor element in the outer tube, the axial end faces of the anchor element each have a first set of protrusions and indentations around the circumference thereof. Two end caps of the housing are fixed at the end faces of the outer tube. Each end cap is provided with an interconnecting part having a second set of protrusions and indentations. The first and second sets of protrusions and indentations interengage to mechanically fix the anchor element axially and radially within the outer tube.04-04-2013
20130028727GAS TURBINE AND TURBINE STATIONARY BLADE FOR SAME - A gas turbine engine and a turbine stator assembly which is capable of being cooled effectively with a small amount of air. The stator assembly comprises a stator vane disposed to be exposed to a combustion gas passage. The stator vane comprises a cooling passage defined therein. The cooling passage is disposed on an upstream of the gas turbine engine and extending in a radial direction with respect to a central axis of the gas turbine engine. The stator vane also has an inlet communicated to a radially outward end of the cooling passage. The stator vane further has an adjustment member secured to the stator vane so that it covers the inlet. The adjustment member has two apertures for guiding a cooling air radially inwardly through the inlet into the cooling passage. The two apertures are spaced away from each other along a camber line of the stator vane.01-31-2013
20130028726FLOW STRAIGHTENER DEVICE FOR TURBOMACHINE - A flow straightener device for a turbomachine including an inner shell ring and an outer shell ring surrounding the inner shell ring, at least one out of the inner shell ring and outer shell ring having first orifices; at least two flow straightener vanes each including, at least at one same first end, an attachment platform having second orifices positioned facing the first orifices; the at least two vanes being assembled with at least one of the inner shell ring and outer shell ring by at least one first device of attachment introduced into the first orifices and the second orifices. The flow straightener device includes a covering platform covering the at least one first device of attachment.01-31-2013
20130028724AXIAL-RADIAL TURBOMACHINE - Axial-radial flow machine having an axial portion with at least one axial stage, a radial portion with at least one radial stage, a housing having an interior space with a dividing wall extending in a radial direction dividing the housing in an axial direction into a first partial space in which the axial portion is received and a second partial space in which the radial portion is received, and a shaft that extends in axial direction through the interior space and through the dividing wall and on which impellers of the axial portion and of the radial portion are received. A radial gap is formed between the dividing wall and a fluid guiding element of the radial portion. The fluid guiding element is axially fixed to the housing so as to be adjacent to the dividing wall. A plurality of fixing units which are distributed in circumferential direction are arranged in the radial gap, each of which fixing units axially fixes the dividing wall to the fluid guiding element.01-31-2013
20130028725Resurfaced Wicket Gate and Methods - A method for refurbishing wicket gates by applying a sheet material to at least a portion of the vane surface of the wicket gate, thus forming a new face. This sheet material may be applied by wrapping the sheet material around the vane surface. The method may further include applying sheet material to the end surfaces of the wicket vane. If end material is applied, it may be sealed to the sheet material of the vane surface.01-31-2013
20130028723System and Method for Generating Electrical Power Using a Shrouded Turbine System - A system and method for generating electrical power using a shrouded wind turbine system. Specifically, a shrouded wind turbine system can comprise a frame, a turbine mounted to said frame, wherein said turbine comprises a hub, a plurality of blade mounts connected to said hub, said hub rotatable, such that during said rotation said blade mounts move toward a turbine rear when above said hub and toward a turbine front when below said hub. In another embodiment, the shrouded wind turbine system can also comprise a plurality of blades, each connected to a unique one of said blade mounts, and an upper wind shroud comprising a front and a rear, said upper wind shroud front mounted above said turbine front and said upper wind shroud rear mounted above said turbine rear, further wherein said upper wind shroud front is mounted higher than said upper wind rear.01-31-2013
20130028722System and Method for Improving Turbine Efficiency using a Frame and Shroud System - A system and method for improving turbine efficiency using a frame and shroud system is described herein. Specifically, a shroud system can comprise a frame comprising a base and a substantially vertical support structure, said substantially support structure having a top portion and a bottom portion, wherein said bottom portions connect to a base. In another embodiment, the shroud system can also comprise an upper wind shroud connected to said top portion of said support structure, wherein said upper wind shroud is angled between thirty degrees and seventy-five degrees, further wherein a front portion of said wind shroud extends higher than a rear portion of said wind shroud.01-31-2013
20100135778Vane - A vane for a gas turbine engine comprising a cap arrangement comprising a cap insert and a cap adapted to receive the insert, the cap insert comprising a wall defining a through passage from top to bottom of the cap insert for receiving a cable or the like therethrough, the wall comprising a slot with a convoluted profile. Also a vane for a gas turbine engine comprising a cap and a cap insert as described.06-03-2010
20100266398HP TURBINE VANE AIRFOIL PROFILE - A two-stage high pressure turbine includes a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.10-21-2010
20090304501POND PUMP - A pond pump comprising an impeller (12-10-2009
20130071239TURBINE NOZZLE FOR AIR CYCLE MACHINE - A turbine nozzle for an air cycle machine includes a base 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 0.101-0.112.03-21-2013
20130136592TURBINE NOZZLE AIRFOIL PROFILE - A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.05-30-2013
20130058775CATCHER RING ASSEMBLY - A catcher ring assembly (03-07-2013
20110014039TURBINE WITH AXIAL DISCONTINUITY - A turbocharger turbine containing a separate insert affixed within the housing. The insert is of a stamped metal configuration, and forms at least a portion of inlet passageway outer wall. An axial discontinuity is machined into the inlet passageway outer wall, the axial discontinuity being characterized by a size and location to direct airflow away from the blade-gap zone over at least part of the range of flow conditions. The inlet passageway may be either larger or smaller upstream of the axial discontinuity.01-20-2011
20120224956PUMP APPARATUS - A pump apparatus includes a drive shaft supported rotatably in a pump body; a power transmission member attached to the drive shaft, and configured to transmit power to the drive shaft; a pump element configured to pressurize and discharge working fluid; a discharge passage formed in the pump body, and configured to introduce the pressurized working fluid discharged from the pump element to an external of the pump body; a control valve configured to control an amount of working fluid to be discharged through the discharge passage to the external, by controlling a movement of a valving element of the control valve on the basis of the pressurized working fluid; and an electromagnetic valve provided between the power transmission member and the control valve, and configured to control the control valve or a fluid pressure acting on the valving element of the control valve based on the pressurized working fluid.09-06-2012
20120224955DIFFUSER - A diffuser having a flow path including generally annular regions arranged to direct a flow of fluid with both tangential and axial velocity components.09-06-2012
20120224954AIRFOIL CORE SHAPE FOR A TURBOMACHINE COMPONENT - A turbomachine component includes a compressor stator vane having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein 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 core shape.09-06-2012
20130064661AEROFOIL ASSEMBLY - This invention relates to a stator aerofoil for a gas turbine engine, comprising: a body portion; at least one panel which forms at least part of one of either the pressure or section surface of the aerofoil; at least one internal chamber which is bounded by the body portion and panel; and, at least one elastomeric component within the at least one internal chamber, wherein the elastomeric component at least partially defines a cell within the internal chamber, wherein the cell is in fluid communication with the exterior of the aerofoil.03-14-2013
20130189096Pollutants Collecting Pump for Water Surface - A pollutant collecting pump for water surface comprises a power device (07-25-2013
20090246012TURBINE STATOR MOUNT - A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.10-01-2009
20090246011FILM COOLING OF TURBINE COMPONENTS - A turbine component includes a flow path surface and a trench disposed in the flow path surface. At least one cooling through hole is located in the trench and is capable of injecting a cooling flow onto the flow path surface of the turbine component. The cooling flow forms a cooling film on the flow path surface. A method of cooling a turbine component includes injecting a cooling flow onto a flow path surface of the turbine component through at least one cooling through hole disposed in a trench in the turbine component. A cooling film is formed by the cooling flow between the flow path surface and a hot gas flow.10-01-2009
20120114476VENTILATOR - A ventilator includes a first casing, a second casing, a fan blade and a flow guider. The second casing is connected to the first casing and forms a flow channel between the first casing and the second casing. The fan blade is disposed between the first casing and the second casing. When the fan blade rotates, an air-flow compression zone and an air-flow decompression zone are formed in the flow channel. The flow guider is formed along a boundary line to the air-flow decompression zone, wherein the boundary line is adjacent to the air-flow compression zone and the air-flow decompression zone. With the ventilator, the air pressure of the ventilator is increased and noise can be controlled.05-10-2012
20120114475AIR TURBINE STARTER ONE-PIECE AIR EXIT PORT BAFFLE - A one-piece air exit port baffle for containment for an air start turbine includes a circular arc section with a circumferentially corrugated circular arc section and a flange section. The circumferentially corrugated circular arc section has a plurality of openings. The flange section is axially adjacent to the circumferentially corrugated circular arc section and configured for attachment adjacent to an air exit port of an air turbine starter.05-10-2012
20100086400INTAKE DEVICE AND A PUMP STATION - In a first aspect the invention relates to an intake device (04-08-2010
20100209236IMPULSE TURBINE FOR USE IN BI-DIRECTIONAL FLOWS - A bi-directional flow impulse type turbine arrangement (08-19-2010
20110116917Compressor Stator Vane - A compressor component having a non-linear thickness distribution along the span length is disclosed. By altering the thickness distribution to a non-linear arrangement so as to locally increase airfoil thickness proximate a mid-span location, the natural frequency of the airfoil is increased so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1. The present invention also includes a carrier segment or disk fabricated from a material so as to eliminate corrosion with the compressor component.05-19-2011
20110280720Inner Housing for a Turbomachine - A three-shell steam turbine is provided. The three-shell steam turbine includes an outer housing, an outer inner housing and an inner inner housing, wherein the outer inner housing is arranged around the inner inner housing, in such a way that a cooling steam chamber is formed in between and a flow duct is formed between the outer inner housing and the rotor.11-17-2011
20110280719Fan And Shroud Assembly - An axial flow fan assembly includes a plurality of fan blades surrounded by a shroud. The shroud includes an annular first wall which extends radially outwardly, an annular second wall which extends axially and radially outwardly, and an annular third wall which joins the first wall to the second wall. The third wall has a curved cross sectional shape, and has a minimum diameter part which is positioned approximately half-way between the upstream and downstream edges of the fan blades. There is a desired relationship between the radius of curvature of the third wall and the diameter of the fan. There is a desired relationship between the height of the first wall and the diameter of the fan. The fan blades have an upstream edge which is upstream with respect to the first wall. The third wall has a minimum diameter part which is positioned approximately half-way between the upstream and downstream ends of the fan.11-17-2011
20110070077GAS TURBINE - A gas turbine (03-24-2011
20120288365METHOD OF REDUCING ASYMMETRIC FLUID FLOW EFFECTS IN A PASSAGE - A method of reducing the fluid flow effects of one or more flow modifiers (11-15-2012
20100266397LIGHTWEIGHT BLOWER - Blowing devices (10-21-2010
20100226768AXIAL-FLOW TURBINE - The axial-flow turbine includes an extraction chamber 09-09-2010
20120230818Airfoil and corresponding guide vane, blade, gas turbine and turbomachine - An airfoil suitable for being arranged in a compressor section of the gas turbine includes a platform, a pressure surface and a suction surface, and a tip region. The tip region is located between the pressure and the suction surface opposite to the platform in respect of the pressure and the suction surfaces, being a distant end of the airfoil in direction along the first direction perpendicular to the platform. The tip region includes a first surface with a first distance to the platform along the first direction, and a second surface with a second distance to the platform along the first direction. The first distance is greater than the second distance and the first surface and the second surface together build a profiled surface. The profiled surface is a ribbed surface. The material of the first surface is deformable to bend away from the rotation direction of the airfoil.09-13-2012
20080292456Device for Producing Mechanical Energy by Means of a Divergent, Telescopic and Auto Sustained Chimney - A telescopic chimney and methods are disclosed for generation of mechanical energy using air routed through a turbine. Truncated cones stored nested together telescope to interlock when extended end to end to form a conical shape that diverges upwardly. An air output deflector at the exit of the chimney drives the exiting airflow downwards and is optionally divided into six equal radial spans so that airflow can be varied through each by a computer-controlled shutter to compensate for wind forces. An axial cable raises and lowers truncated cones. A method of deploying the chimney includes steps of closing the shutters; filling the truncated cones with heated air; controlling the rise of the truncated with the cable; and, opening the shutters. A method of collapsing the chimney includes the steps of pulling the cable to exert downward force on a truncated cone.11-27-2008
20110299982METHOD FOR REPAIRING A GUIDE BLADE SEGMENT FOR A JET ENGINE - A method for repairing a guide blade segment fashioned as a twin guide blade segment within a guide blade composite element, the guide blades being formed from a nose segment and a rear edge segment, the method having identification, within a guide blade segment, of a non-repairable guide blade to be separated from the guide blade composite structure; separation of a non-repairable guide blade from a one repairable guide blade in a first plane of division; division of at least one separated guide blade in a second plane of division between the nose segment and the rear edge segment; reconditioning of the at least one repairable nose segment and/or rear edge segment; joining of a reconditioned and/or new nose segment to a reconditioned and/or new rear edge segment to form at least one guide blade; and joining of at least two guide blades to form a guide blade segment.12-08-2011
20100034649DEVICE FOR ENHANCING THE EFFECTIVENESS OF POWER CONVERSION FROM WIND AND OTHER FLUIDS - An energy enhancing device for increasing the effectiveness of energy conversion from wind and other fluid flows is presented by improving methods of accelerating the fluid flow passing through a turbine device or energy converter. Their main application is for accelerating the speed of fluid flow for fluid turbines and other devices designed to extract power from winds, induced air currents, river, ocean, tidal and other water currents.02-11-2010
20120171027STRUCTURAL LOW-DUCTILITY TURBINE SHROUD APPARATUS - A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; and an annular stationary structure surrounding the shroud segment, where the shroud segment is mechanically coupled to the stationary structure. The stationary structure includes at least one axially-facing bearing surface which is in direct contact with the shroud segment, and the shroud segment is disposed so as to absorb at least one axially-aligned force and transfer the axially-aligned force to the bearing surface.07-05-2012
20090175719METHOD OF MANUFACTURING A TURBOMACHINE ELEMENT AND DEVICE OBTAINED IN THIS WAY - Use of the stator blade platforms for the deposition of a track of adjacent abradable material inside an external turbomachine shell.07-09-2009
20100098536FLUID FLOW MACHINE WITH RUNNING GAP RETRACTION - A fluid flow machine includes a main flow path which is confined by a hub (04-22-2010
20090280007MULTI-FUNCTIONAL AIR CIRCULATION SYSTEM - A multi-functional air circulation system includes a bottom base, a flow-splitting base, a filter and a main engine. The bottom base has a lower flow-guiding surface, a net, and a space used to contain diverse improving agents. The flow-splitting base is fixed on the bottom base, including an inner flow-guiding surface to rush air flow generated by a blade member down to the bottom base. The filter is laid at an exit of the inner flow-guiding surface, composed of two filter bases forming a room between them for containing aromatic powder, etc. The main engine includes a motor having its shaft fixed with a blade member, and a control system. The motor is installed in a rear shell combined with a front shell. Air is sucked in through the rear shell to run through an ornamental shell and the flow-splitting base to enter a room. The main engine and the bottom base can also be assembled to work independently.11-12-2009
20090104032AIR CONDITIONER - An air conditioner includes a fan and a rear guide which guides air to the fan. A recess is formed in a side surface of the rear guide which faces the fan.04-23-2009
20100135780Component with Compressive Residual Stresses, Process for Producing and Apparatus for Generating Compressive Residual Stresses - A turbine blade or vane is provided. The turbine blade or vane includes an airfoil portion, a root portion arranged below the airfoil portion, a dove tail shaped securing portion arranged below the root portion have a surface including subregions that have locally different compressive residual stresses, and a convexly curved sub region arranged on the surface and adjacent to the concavely curved sub region. The concavely curved region has higher compressive residual stresses than the convexly curved region, and the level of the compressive residual stress in the concavely curved region is at least 30% of the component base material yield strength.06-03-2010
20090297344Rotors and manufacturing methods for rotors - A rotor for driving, or being driven by, a fluid has rotor blades that follow a screw thread shape, all portions of all blades having the same screw pitch. This enables the rotor, or a molding pattern for use in making a mold, to be withdrawn from a mold part by a screw motion without damage to the mold part. This helps to make it economically viable to manufacture the rotor by a molding or casting process in which the mold parts are not destroyed to release the rotor, such as injection molding, for example with reinforced plastics. Additionally, in the case of manufacturing methods in which the mold is destroyed to release the rotor, the process of making or assembling the mold may be improved. In some molding processes, the ability to remove the rotor or the pattern by screw motion improves the economic viability of the process by reducing the number of mold parts required.12-03-2009
20100061850AIRFOIL SHAPE FOR A COMPRESSOR VANE - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. 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 can be joined smoothly with one another to form a complete airfoil shape.03-11-2010
20120294713Advection-Type Fan - An advection-type fan includes a fan frame, a driving module and an impeller. The fan frame has a first cover portion, a second cover portion and a lateral wall portion arranged between the first and second cover portions, wherein the lateral wall portion has an air inlet and an air outlet. The driving module is received in the fan frame and coupled with the first cover portion. The impeller has a hub and a plurality of vanes. The hub is rotatably coupled with the driving module and the vanes are coupled with the hub. The hub has an air-guiding plane facing the second cover portion. Each of the vanes has a top edge facing the second cover portion. The top edge of each of the vanes is higher than the air-guiding plane of the hub in an axial direction of the hub.11-22-2012
20090169375DEVICE FOR STIFFENING THE STATOR OF A TURBOMACHINE AND APPLICATION TO AIRCRAFT ENGINES - The invention concerns a novel type of turbomachine.07-02-2009
20100143110VANE FOR A COMPRESSOR OR A TURBINE OF AN AIRCRAFT ENGINE, AIRCRAFT ENGINE COMPRISING SUCH A VANE AND A METHOD FOR COATING A VANE OF AN AIRCRAFT ENGINE - An aircraft engine comprising a compressor and at least one turbine is disclosed. The compressor and the turbine are each provided with vanes, each of which has a blade that forms a suction side and a pressure side, where at least one first of the blades is coated with a protective layer in order to reduce the erosion or wear. The layer is applied such that at least two areas are formed that adjoin each other at a boundary line. The first area has a protective layer that has a substantially constant first thickness and the second area is free of the protective layer or has the protective layer with a substantially constant second thickness, the second thickness differing from the first thickness. The boundary line has at least two points, of which the connecting line differs from the course of the boundary line between the two points.06-10-2010
20080273971TURBINE NOZZLE SEGMENT AND REPAIR METHOD - A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed.11-06-2008
20080213090Thrust Generating Apparatus - There have been past proposals for air vehicles employing the Coanda effect. In these proposals, a jet of fluid, usually air, is made to flow radially outwardly over a dome-shaped canopy to create lift. A cross-section through the canopy is curved to follow a segment of a circle or it may have a radius of curvature that increases in the direction of flow. In the invention, the radius (r) of the canopy curve decreases towards the downstream direction (x) in a way that is related to the decrease in the width of the jet as it flows over the surface. This means that the radius of curvature decreases (instead of increasing) towards the downstream direction with the rate of decrease being progressively less rapid towards the downstream direction.09-04-2008
20080206049BLADE ANGLE SETTING FOR A TURBOMACHINE - A straightener blade for a turbomachine, comprising a platform arranged at a radially external end of the blade and adapted to be engaged in a annular groove of a housing, and a threaded rod radially extending outwardly from the platform and adapted to pass through an orifice of the housing in order to receive a fixing nut, the upstream and downstream edges of the platform each comprising a protrusion extending in the plan of the platform in order to limit the rotation of the platform in the groove when the nut screwed on the threaded rod is tightened.08-28-2008
20080273972TEMPERATURE CONTROLLING APPARATUS - An apparatus for controlling the temperature of a component, which is situated in use in a gas stream, provides a nozzle to create a jet of air at an angle to the gas stream, the jet being directed into the region of the stagnation point of the component so as to control the temperature of the component. The invention is particularly suited to preventing or reducing the formation of ice on vanes of gas turbine engines, but may also be applied to other components, and may equally be used in situations where a component is to be cooled rather than heated.11-06-2008
20120070275AIRFOIL FOR ENERGY EXTRACTING SHROUDED FLUID TURBINES - Example embodiments described herein relate an integral and/or multi-piece airfoil and a shrouded fluid turbine having the same. The airfoil can have a generally circumferential body extending circumferentially about a central axis, and can be referred to herein as a “ringed airfoil.” The airfoil can have a front portion defining a leading edge of the airfoil and a rear portion defining a trailing edge of the air foil. A cross-sectional thickness of the front portion can be non-uniform and vary along a mean camber line of the airfoil from the leading edge to a transition area. A cross-sectional thickness of the rear portion can be uniform and constant along the mean camber line of the airfoil from the transition area to the trailing edge of the airfoil.03-22-2012
20080317590PRODUCTION METHOD OF STATOR BLADE AND TURBO-MOLECULAR PUMP WITH THE STATOR BLADE - Disclosed is a method of producing a stator blade for use in a turbo-molecular pump. The method includes subjecting a metal plate to a slitting process to form a blade element having an upstream edge surface and a downstream edge surface, wherein a laser beam is emitted onto the metal plate at an incident angle oblique to a principal surface of the metal plate. Thus, the upstream edge surface and/or the downstream edge surface can be formed to extend obliquely relative to the principal surface of the metal plate, in a simple manner, while eliminating a need for a burr removal operation which would otherwise be necessary in a punching-based slitting process.12-25-2008
20110229317HP TURBINE VANE AIRFOIL PROFILE - A two-stage high pressure turbine includes a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.09-22-2011
20090252606Workpiece, and Also a Welding Method for the Manufacture of a Workpiece - The invention relates to a workpiece (10-08-2009
20120195748VORTEX PREVENTION DEVICE AND DOUBLE SUCTION VERTICAL PUMP HAVING SUCH VORTEX PREVENTION DEVICE - A vortex prevention device is capable of preventing creation of air entrained vortex and also provides a double suction vertical pump having such a vortex prevention device. The vortex prevention device is used in combination with the double suction vertical pump which is installed in an open channel and has an upper suction opening and a lower suction opening. The vortex prevention device includes a plate member as a vortex prevention structure arranged above the upper suction opening. The plate member is arranged away from the upper suction opening such that a passage is formed between the plate member and the upper suction opening.08-02-2012
20100189559FIXTURE FOR USE IN A COATING OPERATION - This invention relates to a fixture for use in a physical vapor deposition coating operation which comprises a support structure 07-29-2010
20100221108Turbine nozzle assemblies - A nozzle assembly for a turbine that may include: (1) a nozzle-blade having inner and outer sidewalls and, in part, defining a flowpath upon assembly into the turbine; (2) an outer ring; (3) a flowsplitter having a horizontal extension; (4) an interface between the outer ring and the outer sidewall having at least one of (i) a male/female interface or (ii) a radial interlock; and (5) an interface between the horizontal extension and the inner sidewall having at least one of (i) the male/female interface or (ii) the radial interlock. In some embodiments, one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall comprises a weld and one of the interface between the outer ring and the outer sidewall and the interface between the horizontal extension and the inner sidewall is weld free.09-02-2010
20110058939TURBINE EXHAUST DIFFUSER WITH A GAS JET PRODUCING A COANDA EFFECT FLOW CONTROL - An exhaust diffuser system and method for a turbine engine includes an inner boundary and an outer boundary with a flow path defined therebetween. The inner boundary is defined at least in part by a hub structure that has an upstream end and a downstream end. The outer boundary may include a region in which the outer boundary extends radially inward toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure. The hub structure includes at least one jet exit located on the hub structure adjacent to the upstream end of the tail cone. The jet exit discharges a flow of gas substantially tangential to an outer surface of the tail cone to produce a Coanda effect and direct a portion of the exhaust flow in the diffuser toward the inner boundary.03-10-2011
20100254808MULTI-DIRECTIONAL WIND GUIDE APPARATUS FOR VERTICAL SHAFT MINDMILL - The present invention relates to a vertical shaft aero-generator. An aero-generator has the advantage that it is not influenced by the wind direction, but the resistance in the reverse direction of rotation is a disadvantage thereof. For figuring out this disadvantage, a plurality of dimple panel wind guide apparatuses are mounted around the outer surface of a cylindrical vertical shaft windmill as well as on top and bottom thereof in order to maximally guide the wind coming from various directions including above and below to the rotational direction of the windmill, thereby the efficiency of the vertical shaft aero-generator is increased. The dimple panel wind guide apparatus includes a feature that a great number of dimples are formed on both entire lateral surfaces of the dimple panel so that the resistance may be minimized.10-07-2010
20100143111COMPRESSOR STABILIZER - An annular circulation chamber is arranged in an interior of a compressor housing, which circulation chamber radially surrounds a main flow duct and extends from an intake region to an encircling circulation opening in a region of rotor blades of the compressor wheel. Between the circulation openings, the circulation chamber is delimited from the main flow duct by an annular contoured wall. The contoured wall is connected to the inner compressor housing by plural struts which are spaced apart from one another to different extents in the circumferential direction. As a result of the irregular distribution of the struts in the circumferential direction, generation of undesired vibration excitations can be reduced and/or eliminated.06-10-2010
20090016877THRUST VECTORING SHROUD FOR FLUID DYNAMIC DEVICE - A fluid dynamic device including a shroud disposed about a central axis and having an upstream fluid intake region and a downstream fluid exit region, the shroud directing fluid flow between the upstream fluid intake region and the downstream fluid exit region. The shroud is configured so that, at least during some operating conditions of the fluid dynamic device, at least a portion of fluid exiting the fluid exit region is directed towards the central axis.01-15-2009
20090257867TURBINE, IN PARTICULAR FOR AN EXHAUST-GAS TURBOCHARGER, AND EXHAUST-GAS TURBOCHARGER - The invention relates to a turbine, in particular of an exhaust-gas turbocharger, comprising a turbine rotor which is supported rotatable in a housing, and to which at least one guide vane apparatus forming a radial inlet channel for a medium driving the turbine rotor is allocated, wherein the guide vane apparatus comprises a guide vane mounting ring with a plurality of guide vanes which radially surround the turbine rotor and which are located within the inlet channel, as well as a guide vane cover ring, and wherein the inlet channel is axially bounded by the guide vane mounting ring and the guide vane cover ring, and the guide vane cover ring abuts with a front side facing away from the inlet channel against a support area of the housing. The invention provides that the housing (10-15-2009
20080304961Noise Reduced Variable Displacement Vane Pump - A novel and useful improvement to vane pumps, both variable displacement vane pumps and fixed displacement vane pumps, provides a supply of pressurized fluid to the region within the diameter of the pump rotor which would otherwise be a region of reduced pressure wherein air could be ingested by the pump. By reducing or preventing the ingestion of air, operating noise and damage to the pump can be reduced and wear in an engine or other system supplied from the pump can be reduced. The supply of pressurized working fluid also can be used to lubricate auxiliary components and/or accessories as well. Further, a portion of the supply of pressurized working fluid to this region can act to supercharge the pump, reducing the occurrence of cavitation at higher operating speeds.12-11-2008
20110123325SEAL PLATES FOR DIRECTING AIRFLOW THROUGH A TURBINE SECTION OF AN ENGINE AND TURBINE SECTIONS - A seal plate for directing an airflow includes a hub, main pumping vanes, and splitter vanes. The hub has a tubular section and an annular flange section flared outwardly relative to the tubular section to define a flow surface. The main pumping vanes are disposed circumferentially on the flow surface around the annular flange section and each has a canted section located radially inward relative to a straight section and aligned with a flow direction of the airflow. The straight section extends along a first plane including a centerline of the seal plate. The splitter vanes are disposed circumferentially on the flow surface around the annular flange section such that at least one splitter vane is disposed between the straight sections of two adjacent main pumping vanes. Each splitter vane has a length that is less than a length of each of the two adjacent main pumping vanes.05-26-2011
20110110774Blower Fan - A blower fan includes a housing having a lateral wall defining a compartment. The housing includes an air inlet and an air outlet both in communication with the compartment. An impeller mounted in the compartment includes a hub and blades mounted on the hub. A first plane including opposite first and second end edges in the air outlet is parallel to and spaced from a second plane including a center of the hub. The compartment of the housing includes an air outlet section and a pressure accumulating section on opposite sides of the second plane. The air outlet section is located between the first and second planes. The lateral wall of the housing includes at least one air guiding hole located in the pressure accumulating section. At least one air guiding tube includes an outlet end and an inlet end coupled to the at least one air guiding hole.05-12-2011
20110243723FAN GUARD - A fan guard includes a bracket, a guide sheet and at least two guide ribs. The bracket defines a vent in the center of the bracket. The guide sheet is located in the center of the vent. The at least two guide ribs interconnect the bracket and the guide sheet. Each guide rib includes a first connecting portion and a second connecting portion connecting the first connecting portion. The first connecting portion and the second connecting portion cooperatively define a first angle therebetween.10-06-2011
20090214335METHOD OF REPAIR FOR CANTILEVERED STATORS - A method for repairing a cantilevered stator vane includes removing a damaged portion leaving a remaining vane portion. A supplemental airfoil portion is then selected and is attached to the remaining vane portion to provide a repaired cantilevered stator vane.08-27-2009
20110033289Bypass-Type Motor Protecting Device for a Vacuum Cleaner - A bypass-type motor protecting device includes: a casing fitted into a bypass opening in a body housing of a vacuum cleaner and having an inner abutment wall; a seat body having a bypass entry port; a valve body unit movable within the casing relative to the bypass entry port and including a valve disc to be engaged with and disengaged from the seat body, a plunger body having an externally accessible operated head and an axially extending threaded shank, and an abutment member threadedly engaged with the shank such that rotation of the operated head results in a change of an axial distance between the abutment member and the inner abutment wall; and a biasing member disposed to bias the abutment member and the inner abutment wall such that a biasing force thereof is varied in strength by the change of the axial distance.02-10-2011
20110033288OMNIDIRECTIONAL VERTICAL-AXIS WIND TURBINE - A two-stage, omnidirectional vertical axis wind turbine includes a first chamber in which a plurality of angularly spaced horns guide wind from any side of the wind turbine into a chamber to rotate a first rotor. Wind exiting the first rotor passes through a diverter to produce laminar flow. A fan attached to the shaft intercepts this laminar flow to add additional torque to the shaft.02-10-2011
20110243722ANTI-ROTATION SLOT FOR TURBINE VANE - A fixed vane section for a gas turbine engine includes an anti-rotation slot that receives a pin for maintaining a desired position while providing for movement encountered during operation. The example anti-rotation slot includes a compound radius on inner surfaces to reduce stresses encountered during operation.10-06-2011
20100135779SEMI-FINISHED PRODUCT FOR PRODUCING A REPAIRED BLADE FOR A GAS TURBINE AND REPAIR METHOD FOR REPAIRING A BLADE FOR A GAS TURBINE - The invention relates to a semi-finished product for producing a repaired blade for a gas turbine. Said semi-finished product comprises a first part (06-03-2010
20110085901SHROUDED WIND TURBINE WITH SCALLOPED LOBES - A shrouded wind turbine comprises an impeller and a turbine shroud surrounding the impeller. The shroud includes alternating inward and outward curving elements that form mixing elements on a trailing edge of the turbine shroud. The inward and outward curving elements have exposed lateral surfaces, or in other words do not have sidewalls joining the inward and outward curving elements. This allows for both transverse mixing and radial mixing of air flow through the turbine shroud with air flow passing along the exterior of the turbine shroud.04-14-2011
20090257866Stator blade for a turbomachine, especially a steam turbine - The invention relates to a stator blade (10-15-2009
20100008773Turbine blade and gas turbine equipped with a turbine blade - The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.01-14-2010
20090028698Systems and Methods Involving Aerodynamic Struts - Systems and methods involving struts are provided. In this regard, a representative system includes a gas turbine engine defining a gas flow path. The gas turbine engine comprises a strut extending into the gas flow path. The strut has an interior operative to receive pressurized air, an outer surface, and ports communicating between the outer surface and the interior of the strut, the ports are operative to receive the pressurized air from the interior and emit the pressurized air into the gas flow path such that an effective aerodynamic length of the strut along the gas flow path is increased.01-29-2009
20120201667METHOD AND A DEVICE OF TANGENTIALLY BIASING INTERNAL COOLING ON NOZZLE GUIDE VANE - A deflector for guiding a cooling fluid to a blade device of a turbine is provided. The deflector includes a first opening region with a first opening shape and a second opening region with a second opening shape. The deflector is connectable to a first blade device and to a second blade device in such a way that the cooling fluid is streamable through the first opening region into the first blade device and the cooling fluid is streamable through the second opening region into the second blade device. The first opening shape differs from the second opening shape for achieving a predetermined first mass flow of the cooling fluid into the first blade device and a predetermined second mass flow of the cooling fluid into the second blade device at predetermined installation locations of the first blade device and the second blade device.08-09-2012
20120201666STAGGERED MULTI-LEVEL VERTICAL AXIS WIND TURBINE - A staggered multi-level vertical axis wind turbine includes a cage structure including wind directing elements arranged circumferentially about outer edges thereof. Within the cage structure is a rotor including a centrally located shaft orientated along an axis and extending at least from one end of the cage structured to another end. The rotor includes a first rotor level of torque generating elements of a first type coupled to the shaft. The rotor includes a second rotor level of torque generating elements of a second type coupled to the shaft. The rotor includes a third rotor level including torque generating elements of the first type coupled to the shaft. The wind directing elements receive and re-direct wind onto the torque generating elements of the various levels, thereby producing torque and causing the rotor to spin. The rotor is coupled to an electrical generator, which generates clean and renewable energy.08-09-2012
20100296924Guide Vane for a Variable Turbine Geometry - A guide vane, particularly for a turbocharger, has a line of curvature with at least one or more sectors having a discontinuous course.11-25-2010
20110255961SOLID FEED GUIDE APPARATUS FOR A SOLID FEED PUMP - In one embodiment, a system includes a solid feed pump. The solid feed pump includes a housing, a rotor disposed in the housing, a curved passage disposed between the rotor and the housing, an inlet port coupled to the curved passage, an outlet port coupled to the curved passage, a solid feed guide extending across the curved passage, and multiple discrete contacts distributed along an interface between the solid feed guide and the rotor.10-20-2011
20110255962DIFFUSER HAVING BLADES WITH APERTURES - A diffuser for a mixed flow or centrifugal compressor of a gas turbine. The diffuser includes at least one vane presenting a pressure side, a suction side, and a first flank. The vane includes a plurality of orifices opening out into the suction side and/or the pressure side and communicating with at least one cavity formed in the vane, the cavity extending transversely relative to the vane and opening out into its first flank. The cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank.10-20-2011
20080267775Nozzle segments and method of repairing the same - A method of repairing a nozzle segment is provided. The nozzle segment includes at least one airfoil extending between an inner band and an outer band, and the airfoil includes a first sidewall and an opposing second sidewall that are joined together at a leading edge and at an axially-spaced trailing edge. The method includes identifying a damaged portion of the airfoil, repairing the damaged portion of the airfoil by at least one of welding weld filler in the area of the damaged portion of the airfoil, and brazing preform in the area of the damaged portion of the airfoil, and blending at least one of the weld filler and the preform to remove excess material to facilitate finishing an outer surface of the airfoil.10-30-2008
20110164970Stator blade for a turbomachine, especially a stream turbine - The invention relates to a stator blade (07-07-2011
20110164969METHOD FOR PRODUCING A VANE, SUCH A VANE AND A STATOR COMPONENT COMPRISING THE VANE - A method for producing a vane for application in a component in a gas turbine engine includes casting at least one of a vane leading edge part and a vane trailing edge part and connecting the leading edge part and the trailing edge part.07-07-2011
20080253884Out-flow margin protection for a gas turbine engine - A cooled turbine exhaust case assembly includes a plenum defined at least in part by a forward outer diameter flowpath ring and a turbine case, a probe positioned at a probe opening formed in the forward outer diameter flowpath ring, and an inlet opening in the turbine case for introducing cooling air to the plenum.10-16-2008
20120201665AIR FLOW DEFLECTOR - An air flow deflector comprising (a) a deflector body having an outer surface, the deflector body providing an air passage extending through an inlet, a throat and an outlet, the size of the inlet is greater that the size of the throat; (b) a pair of channels provided between the inlet and the outlet and each of the pair of channels having a venturi profile; and (c) an outlet portion of the air flow deflector provided between the throat and the outlet to provide a gradual transition between the throat and the outlet; wherein the air flow deflector increases an air flow velocity of air entering said inlet.08-09-2012
20120121403REMOVABLE THROAT MOUNTED INLET GUIDE VANE - In certain embodiments, a system includes an inlet guide vane assembly. The inlet guide vane assembly includes a plurality of inlet guide vanes disposed in a radial pattern around a central axis and configured to rotate about axes orthogonal to the central axis. The inlet guide vane assembly also includes a plurality of vane shafts, each connected to a respective inlet guide vane and configured to rotate with the respective inlet guide vane about the respective orthogonal axis. The inlet guide vane assembly further includes a drive shaft directly connected to one of the vane shafts and configured to directly cause rotation of the vane shaft to which it is directly connected and to indirectly cause rotation of the remaining vane shafts in the plurality of vane shafts. In addition, the inlet guide vane assembly includes a rotary actuator connected to the drive shaft and configured to cause rotation of the drive shaft.05-17-2012
20110135459Continuous-Flow Energy Installation, in Particular a Wind Power Installation - Continuous-flow energy installation having at least one rotor (06-09-2011
20110052387NON-AXISYMMETRIC AIRFOIL PLATFORM SHAPING - Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.03-03-2011
20110052386METHOD OF WELDING SINGLE CRYSTAL TURBINE BLADE TIPS WITH AN OXIDATION-RESISTANT FILLER MATERIAL - A method for depositing material on a turbine airfoil having a tip wall extending past a tip cap, wherein the tip wall includes a first alloy with a single crystal microstructure. The method includes: depositing a second alloy on at least a portion of the tip wall to form a repair structure, wherein a high temperature oxidation resistance of the second alloy is greater than a high temperature oxidation resistance of the first alloy, and wherein the repair structure has a crystallographic orientation that is substantially the same as a crystallographic orientation of the tip wall.03-03-2011
20110135458FLUID TURBINE WITH SHROUD HAVING SEGMENTED LOBES - A shrouded fluid turbine comprises an impeller and a turbine shroud surrounding the impeller. The shroud includes alternating inward and outward curving elements that form mixing elements on a trailing edge of the turbine shroud. The inward and outward curving elements have exposed lateral surfaces, or in other words do not have sidewalls joining the inward and outward curving elements. This allows for both transverse mixing and radial mixing of fluid flow through the turbine shroud with fluid flow passing along the exterior of the turbine shroud.06-09-2011
20100172752AIRFOIL PROFILE FOR A SECOND STAGE TURBINE NOZZLE - Second-stage nozzles have vanes including airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I with the X, Y and Z values commencing at the radially innermost aerodynamic section of the airfoil and then made relative to that section for the Z coordinate values. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the nozzle.07-08-2010
20100172753COMPRESSOR SIDE INLET WITH IMPROVED AERODYNAMIC PERFORMANCE AND REDUCED MANUFACTURING COMPLEXITY - An air plenum is configured to direct air into a centrifugal compressor impeller in an ACM compressor. The air inlet plenum has a cylindrical outer wall, a forward circular end wall, and a rearward circular end wall. An air inlet radially extends from the cylindrical outer wall and is in flow communication therewith. An aperture in forward circular end wall is configured to seal receive about a rotating shaft. An aperture in rearward circular end wall is configured to receive the rotating shaft and allow air flow therethrough about the rotating shaft. A rectangular baffle extends radially inward from the cylindrical outer wall at a circumference thereof opposite the air inlet. The rectangular baffle may extend between the forward and rearward end walls.07-08-2010
20110116918METHOD AND MACHINERY WITH COMBINED PARTICLE SEPARATION AND FLOW REGULATION DEVICES - A method for assembling turbomachinery having combined particle separation device and flow regulating device is provided. The turbomachinery includes a casing; a compressor attached to an inside of the casing, the compressor having a shaft supported by bearings; and a cooling system mounted inside the casing and configured to cool the bearings of the compressor with a cooling fluid. The cooling system includes a particle separation device configured to separate particles from the cooling fluid, and a flow regulation device that fluidly communicates with the particle separation device without contacting the particle separation device. The flow regulation device is disposed adjacent to the particle separation device within a wall of the casing.05-19-2011
20100215488FLUID FLOW ENERGY CONCENTRATOR - An energy conversion system for converting energy of naturally occurring fluid flow into output power. The energy conversion system includes an accelerator plate that has a leading edge and an upper surface that is substantially linearly inclined from the leading edge and transitions into a gradually increasing inclined shape so as to receive a fluid flow and form a vortex at a rear portion of the accelerator plate and a turbine positioned at the rear of the accelerator to rotate in the vortex created by the accelerator plate. The cross-sectional shape of the accelerator plate has a duckbill shape which causes the fluid flow to increase up to five times and before turbulence is created and directs the increased air flow onto the blades of the turbine.08-26-2010
20100166551HYBRID TURBOMACHINERY COMPONENT FOR A GAS TURBINE ENGINE - The present invention provides a hybrid turbomachinery component for use in a gas turbine engine. The hybrid turbomachinery component may be operative to direct the working fluid of the gas turbine engine and/or addi energy to the working fluid and/or extract energy from the working fluid. One or more portions of the hybrid turbomachinery component are made from one material, and other portions of the hybrid turbomachinery component are made from another material.07-01-2010
20100196152ROTARY PRESSURE TRANSFER DEVICE WITH IMPROVED FLOW - A rotary pressure transfer device utilizes a multi-channel, generally cylindrical rotor (08-05-2010
20100196153Fluid turbine systems - Various fluid turbine systems and methods are described. The turbine can be a vertical axis wind turbine configured to generate power from wind energy. The turbine system can have a blade assembly. The blade assembly can have a plurality of blades rotatable about an axis. The turbine system can have a concentrator positionable upwind and in front of a return side of the blade assembly. The concentrator can define a convex surface facing the wind. The turbine system can also have a variable concentrator positionable upwind of a push side of the blade assembly. The variable concentrator can be adjustable between a first position and a second position, the variable concentrator being capable of deflecting more wind toward the turbine in the first position than in the second position.08-05-2010
20110189007FLUID TURBINE - A shrouded fluid turbine comprises an impeller and a turbine shroud surrounding the impeller. The inlet of the turbine shroud is flared. The shroud includes alternating inward and outward curving lobe segments along a trailing edge of the turbine shroud. The inward and outward curving lobe segments have exposed lateral surfaces, or in other words do not have sidewalls joining the inward and outward curving lobe segments. This allows for both transverse mixing and radial mixing of air flow through the turbine shroud with air flow passing along the exterior of the turbine shroud.08-04-2011
20100021292FLUID DEFLECTOR FOR FLUID SEPARATOR DEVICES - A fluid deflector is for a fluid separator including a central axis and an enclosed wall having an open end and an inner circumferential separation surface extending about the axis to define an interior separation chamber. The fluid deflector includes a base disposeable proximal to the wall open end and having a central axis collinear with the separator axis. A plurality of vanes are connected with the base so as to be spaced circumferentially about the central axis. The vanes define a plurality of flow channels each bounded by a separate pair of adjacent vanes and having an inlet and an outlet. Each vane directs flow through a bounded channel generally radially inwardly from the channel inlet toward the channel outlet and generally circumferentially and radially outwardly from the channel outlet.01-28-2010
20120308375FAN ASSEMBLY - A fan assembly for creating an air current includes a base having an air inlet and an air outlet, the base housing an impeller and a motor for rotating the impeller to create an air flow passing from the air inlet to the air outlet. The fan assembly further includes a vertically oriented, elongate annular nozzle including an interior passage having an air inlet for receiving the air flow from the base and a mouth for emitting the air flow, the nozzle defining an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth.12-06-2012
20120308374DIFFUSER-GUIDE VANE CONNECTION FOR A CENTRIFUGAL COMPRESSOR - An assembly including a diffuser and an airflow rectifier at an outlet of a centrifugal compressor of a turbine engine, the diffuser being substantially in a shape of a radially positioned double annular disc, and the rectifier being a double toroidal part, arranged as an extension of the double disc of the diffuser and curved such as to divert the airflow in the downstream direction of the engine. The rectifier is attached to the diffuser by a connection positioned immediately adjacent to the contact surface of the two parts and is removable using a standard tool, excluding any other supporting mechanism.12-06-2012
20120308373AXIAL FAN ASSEMBLY - A fan assembly includes an axial flow fan between an inlet stator and an outlet stator. The inlet stator has inlet stator blades which extend outwardly from an inner ring. Each inlet stator blade has a downstream edge which has a tangent which is oriented at a first variable angle with respect to a plane which is perpendicular to the fan axis. The first angle increases with increasing distance from the inner support ring. The outlet stator has a plurality of outlet stator blades which extend outwardly from a second inner ring. Each outlet stator blade has an upstream edge which has a tangent which is oriented at a second variable angle with respect to a plane which is perpendicular to the fan axis. The second angle decreases with increasing distance from the inner ring.12-06-2012
20100124493MULTI-VANE SEGMENT DESIGN AND CASTING METHOD - Provided is an industrial gas turbine multi vane segment, which can be cast in one piece using a wax pattern method. The multi vane segment includes a platform; at least three airfoils, extending radially from the platform, having a combined airfoil volume, a chord length and an airfoil thickness; and a shroud with a shroud volume, disposed on an end of said airfoils radially distant from the platform. The ratio of the shroud volume to the combined airfoil volume defines a first ratio, while the multi vane segment has a first ratio greater or equal to 1.4:1. This ratio enables preferential solidification, during casting, of the airfoils before the shroud.05-20-2010
20120034078IMPELLER AND CENTRIFUGAL COMPRESSOR INCLUDING THE SAME - Provided is an impeller of a centrifugal compressor including: a hub fixed to a rotation shaft; and a plurality of blades extending outward from a center portion of the hub on one surface of the hub, wherein a length of the blade is greater than a straight length between an inlet end of the blade and an outlet end thereof. Assuming that an outlet angle formed along a longitudinal direction of the blade at the outlet end of the blade is β and an inclination angle of the blade from the one surface of the hub at the outlet end of the blade is γ, the following equation is satisfied: 102-09-2012
20090047125FLOW CHANNEL OF A REGENERATIVE PUMP - The present invention provides an improvement in a new structure of a regenerative pump, including a cross section structure of the flow channel of a pump casing and closed type impeller, whereby to improve a better flow model for pump performance to solve problems of noise, and to increase the outflow capacity and higher efficiency.02-19-2009
20110305564LOCAL EXHAUST APPARATUS - A local exhaust system includes a motor provided in an exhaust pipe to generate a rotary drive force when power is applied thereto, in which air is taken in through an intake port and exhausted through the exhaust pipe, a rotor structure disposed on the leading end of the intake port and connected to a drive shaft of the motor, the rotor structure rotating about a central portion of the exhaust pipe, and a plurality of turbulence-generating outer blades for generating a turbulent flow when rotated. Each of the turbulence-generating outer blades is assembled to the outer surface of the rotor structure via an angle-adjusting member in such a fashion that the angle of the turbulence-generating outer blade is adjustable with respect to the direction in which air is taken in through the intake port.12-15-2011
20110305563Wind Turbine Funnel - The wind turbine funnel includes a frame rotatably mounted to support about a rotational axis. The frame includes an inlet having a funnel directing incoming wind towards a turbine wheel disposed adjacent the funnel. The funnel includes an angled upper, main deflector and an optional, angled lower deflector disposed between side panels. The turbine wheel includes a plurality of curved wind blades radiating from the axis of the wheel. The blades are configured to maximize conversion of the wind energy into rotational force for the wheel. The center of gravity of the frame and turbine is disposed behind the rotational axis to permit free rotational adjustment of the frame with respect to wind direction with minimal force. The side panels may include raised sections that function as a rudder.12-15-2011
20090003999Three-Vaned Drag-Type Wind Turbine - A novel three-vaned, drag-type wind turbine, wherein air, when it exits a first vane, is split into two flow paths. A first path is directed to a second vane, while a second path is directed to a third vane. The air, then, impinges on a plurality of vanes wherein the momentum of the air is altered, thus providing the force needed to drive the wind turbine. In a first embodiment, a wind shield is used to deflect a portion of the wind from entering the wind turbine, this portion being in a region where the vanes are rotating into the wind. In second embodiment, the wind shield is not used.01-01-2009
20120148395STEAM TURBINE SINGLET NOZZLE DESIGN FOR BREECH LOADED ASSEMBLY - A steam turbine nozzle airfoil with integral inner and outer sidewalls is engaged with an inner ring and an outer ring in a nozzle assembly. Previous designs required large clearances between radial surfaces to permit simultaneous circumferential loading of the inner and outer sidewall into the inner and outer rings. The inventive arrangement provides for breech loading of the inner sidewall into the inner ring which allows near line-to-line radial contact on the hooks between the rings and the integral sidewalls of the Singlet nozzle airfoil. Tighter radial clearance overcome problems with loose assembly such as movement during welding, gaps leading to stress risers and performance issues associated with nozzle throat control.06-14-2012
20090074571VANE STRUCTURE OF AN AIRFLOW GENERATOR - The present invention provides a vane structure of an airflow generator. The plate of predefined thickness and width has a locating portion and a swinging end. The swinging end of the vane is wider than the locating portion. There is an oblique section placed between the swinging end and locating portion for linking purposes. A better wind guide effect can be obtained from the expanded swinging end, and the oblique section is employed to reduce inlet stagnation, thus greatly improving the smoothness of air flow and the operating performance of the vane with better applicability.03-19-2009
20090081035GAS TURBINE ENGINE COMPRESSOR CASE MOUNTING ARRANGEMENT - A compressor case support arrangement for a gas turbine engine includes a fan section having a central axis and a compressor case for housing a compressor. An inlet case guides air to the compressor. The compressor case is positioned axially further from the fan section than the inlet case. A support member extends between the fan section and the compressor case. The support member restricts movement of the compressor case relative to the inlet case. The support member is positioned axially further from the fan section than the plumbing access area.03-26-2009
20080219841Fan with strut-mounted electrical components - A cooling fan comprises a fan housing, a motor which is positioned within the fan housing, a plurality of electronics components which are associated with the motor, and at least one strut which extends radially between the motor and the fan housing, and on which the electrical components are mounted.09-11-2008
20110318177Turbine housing for an exhaust gas turbocharger and method for producing turbine housing - In the turbine housing for an exhaust gas turbocharger of a drive assembly at least one spiral channel, which can be coupled to an exhaust gas line of the drive assembly is provided A receiving chamber for a turbine wheel to which exhaust gas can be supplied is disposed upstream of the at least one spiral channel. The turbine wheel is disposed in the turbine housing so as to be rotatable about a rotational axis. A guide baffle is arranged fixed to the turbine housing in a transition region between the at least one spiral channel, the guide baffle being connected to the turbine housing by a metal-to-metal joint whereby the guide baffle is connected to the turbine housing in a particular tight manner.12-29-2011
20120207594GAS TURBINE ENGINE AIR INTAKE IN A NACELLE - An assembly including a gas turbine engine and a nacelle in which the engine is housed, the nacelle including an air intake fairing that forms an air inlet and includes: a member for deflecting foreign objects, which together with the fairing, forms an air intake duct; and, downstream from the deflecting member, a secondary deflecting channel, and a main channel for supplying air to the engine. The air intake duct is configured to deflect at least some of the foreign objects sucked in through the air inlet towards the secondary deflecting channel. The secondary deflecting channel is shaped such that the flow velocity of the air flowing therethrough increases from upstream to downstream, the secondary channel having an outlet with an opening leading into the outer wall of the nacelle.08-16-2012
20120301289FUEL PUMP - A fuel pump, including a driven impeller, which rotates in a pump housing and on the two sides comprises guide blades that each delimit a ring of blade chambers, and further including partial ring-shaped channels, which are arranged on both sides in the region of the guide blades in the pump housing and which form delivery chambers with the blade chambers for delivering fuel, wherein an inlet channel leads into the one delivery chamber and the other delivery chamber leads into an outlet channel, and mutually opposing blade chambers are connected to each other. The cross-sectional surface of the partial ring-shaped channel arranged on the inlet side decreases toward the end of the partial ring-shaped channel to zero. The region in which the cross-sectional surface decreases extends over an angular region of more than 45°.11-29-2012
20120301288CHARGING DEVICE - An exhaust gas turbocharging device is disclosed. The turbocharging device comprises a turbine comprising at least one flow guide vane for a medium. The flow guide vane is pivotably mounted on a housing component of the charging device by a bearing shaft seated in a recess of the housing component, wherein the bearing shaft and the recess form at least two bearing locations with different diameters spaced from each other in an axial direction.11-29-2012
20090068005Airfoil Shape For A Turbine Nozzle - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth TABLE I. The X and Y values are distances in inches, which when connected by smooth continuing arcs define airfoil profile sections at each distance Z in inches The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of +0.130 inch to −0.030 inch.03-12-2009
20120171028VANE WITH SPAR MOUNTED COMPOSITE AIRFOIL - A vane includes a composite airfoil having one or more pockets and one or more spars received therein respectively. The spars extending radially away from a bridge of a vane mount supporting airfoil. The spars may be integrally formed with the bridge. The spars may be adhesively bonded to the composite airfoil within the pockets. A passage may extend between an airfoil base and an airfoil tip. A gas turbine engine annular fan frame includes an annular row of the composite outlet guide vanes extending radially between and connecting radially inner and outer rings of the fan frame.07-05-2012
20120219410AIRFOIL SHAPE FOR A COMPRESSOR BLADE - 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.08-30-2012
20120121402CENTRIFUGAL COMPRESSOR DIFFUSER - A system, in certain embodiments, includes a centrifugal compressor diffuser vane including a leading edge, a trailing edge, and a constant thickness section extending between the leading edge and the trailing edge. A radius of curvature of the leading edge and a radius of curvature of the trailing edge vary along a span of the vane. A ratio of a length of the constant thickness section to a chord length of the vane is at least approximately 50%, and the ratio is substantially constant along the span of the vane.05-17-2012
20120128480BLADE - The present invention relates to a blade of a turbomachine, in particular an adjustable guide blade or vane of a gas turbine, having at least one thickened area (05-24-2012
20120128478CENTRIFUGAL PUMP ASSEMBLY - The invention relates to a centrifugal pump assembly with at least one impeller, with a suction union (05-24-2012
20120128479DIFFUSOR - The guide device for the diffusor at the compressor impeller outlet of a radial compressor has guide blades with stepped inlet edges. The step is implemented by setting back the hub-side inlet edge. This meridional stepping divides the guide blades into two component blades, of which the first component blade is made longer than the second component blade. The set-back of the inlet edge of the hub-side component blade and the associated superposition of the noise fields which are produced on the front and rear inlet edge of the diffusor leads to improvement of the acoustic properties of the compressor.05-24-2012
20100209237VANE - A vane for use in a duct, such as an exhaust duct in a gas turbine engine, comprises a shear web arranged to extend substantially across the duct and to be fixedly attached to at least one wall thereof, and one or more vane plates removably mountable on the web. On each side of the web three retaining plates are secured to the web by bolts 08-19-2010
20120213633GAS TURBINE ENGINE COMPONENT - A gas turbine engine component includes a ring element and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. At least one of the vanes is made of a composite material. The at least one composite vane is fastened to the ring element. The component further includes first and second wall portions that are fixed in relation to the ring element and arranged on opposite sides of the composite vane. At least a first hole extends through the first wall portion, the composite vane and the second wall portion. The first hole is adapted to receive a first insertion member. The component is arranged such as to, with regard to the first hole, provide a tight fit for the first insertion member in the first wall portion as well as in the composite vane and to provide a loose fit with a radial play in the second wall portion.08-23-2012
20120213632Non-Metallic Vertical Turbine Pump - A non-metallic vertical turbine pump and a method of manufacturing same are provided. In accordance with one embodiment, the vertical turbine pump can include a motor, and a drive shaft coupled to the motor for rotation, a casing with a mixed flow diffuser including a diffuser hub and diffuser vanes that project out from the diffuser hub, and a mixed flow impeller configured to rotatably fit inside the casing, having an impeller hub, impeller vanes, extending from the hub, and a front and a back shroud connected to opposing ends of the impeller vanes. At least one of the mixed flow impeller and the mixed flow diffuser can be made of a non-metallic material and is a singular homogenous component.08-23-2012
20120213631UNFLARED COMPRESSOR BLADE - A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.08-23-2012
20120134796VOLUTE AND DRAINAGE PUMP - A drainage pump has an impeller, a motor for driving the impeller, and a volute housing the impeller. The volute has an end wall, a side wall, an inlet, and an outlet. The side wall extends from the end wall. The side wall and the end wall cooperatively define a pump chamber. The inner surface of the side wall has at least one interfering surface for mixing of fluid flowing through the volute.05-31-2012
20080273970HP turbine vane airfoil profile - A two-stage high pressure turbine comprises a second stage vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.11-06-2008
20120219411TWO-STAGE CENTRIFUGAL PUMP - The invention relates to a centrifugal pump (08-30-2012
20100272564MULTI STAGE RADIAL COMPRESSOR - A multistage radial compressor (10-28-2010
20100226769FAN ASSEMBLY - A bladeless fan assembly includes a nozzle mounted on a base housing a motor and an impeller driven by the motor for creating an air flow. The nozzle includes an interior passage for receiving the air flow, a mouth for emitting the air flow, and a plurality of stationary guide vanes located within the interior passage and each for directing a portion of the air flow towards the mouth. The nozzle defines an opening through which air from outside the fan assembly is drawn by the air flow emitted from the mouth.09-09-2010
20090060732SERIAL FAN MODULE AND FRAME STRUCTURE THEREOF - A serial fan module includes a first fan, a second fan and a plurality of guide elements. The first fan has a first frame body and a first impeller disposed within the first frame body. The second fan has a second frame body and a second impeller disposed within the second frame body. The guide elements are disposed between the first impeller and the second impeller, wherein the guide elements guide airflow from the first fan to the second fan. Each of the guide elements has an axial extended part and an inclined part and the inclined part meets the axial extended part at a camber angle. Each of the inclined part has an inner edge toward the first impeller and each of the axial extended part has an outer edge toward the second impeller.03-05-2009
20120082542STEAM TURBINE ROTOR, METHOD OF MANUFACTURING THE SAME, AND STEAM TURBINE - In one embodiment, a steam turbine rotor has a first and a second rotor, a first and a second flange, a bolt, and a cap nut. The first flange is connected to an end portion of a first shaft of the first rotor and has a first through hole. The second flange is connected to an end portion of a second shaft of the second rotor and has a second through hole. The bolt is inserted through the first and second through holes and has a shaft part, a male screw part disposed on one end of the shaft part, and a projection part disposed on an end portion of the male screw part. The cap nut has a female screw part engaged with the male screw part and a projection through hole which the projection part penetrates.04-05-2012
20120263586INLET GUIDE VANE FOR A COMPRESSOR - A compressor assembly (10-18-2012
20120263587TURBOMACHINE WITH AXIAL COMPRESSION OR EXPANSION - The turbomachine has a ring of radial blades which are connected to an annular end wall. Situated on the end wall upstream of each blade is a deflector wedge with two divergent guide surfaces. The deflector wedge generates pressure-side and suction-side vortices of which the vortices caused by the blade cascade are altered such that the transverse flow and backflow areas on the blade are reduced, and therefore the edge zone losses are decreased.10-18-2012
20080298960Micro-Air Motor - A micro-air motor comprises a collector rotatably mounted in a casing for the compressed air supply and discharge to or from the rotor. By twisting the collector as far the end positions a direction of rotation reversal as well as continuous speed regulation is possible. In a neutral position of the collector the rotor can be additionally stopped and locked.12-04-2008
20120269623Guide vane with a winglet for an energy converting machine and machine for converting energy comprising the guide vane - An energy converting machine includes a guide vane. The guide vane includes a guide vane body for guiding a streaming fluid. The guide vane body has a pressure surface and a suction surface, a trailing edge and a leading edge, and a winglet for reducing leakage of the streaming fluid from the pressure surface to the suction surface. The winglet is arranged at a longitudinal end of the guide vane body. The winglet extents from the trailing edge to the leading edge and is arranged at the pressure surface. The winglet is free of protrusions beyond the leading edge and beyond the trailing edge.10-25-2012
20120269622TURBINE VANE AND GAS TURBINE - A turbine vane of the invention includes: a plurality of outer shrouds (10-25-2012
20120321455TURBOCHARGER HOUSING - A turbocharger housing is split lengthwise and has two housing halves, which in the assembled state sectionally form a bearing housing, a turbine housing, and a compressor housing. The turbocharger housing contains at least one fluid chamber, which is arranged in the bearing housing and/or in the turbine housing and/or in the compressor housing of at least one of the two housing halves. The fluid chamber contains a plurality of raised webs, which are disposed to influence the fluid flow.12-20-2012
20110236200GAS TURBINE ENGINE WITH NON-AXISYMMETRIC SURFACE CONTOURED VANE PLATFORM - A vane segment for a gas turbine engine according to an exemplary aspect of the present disclosure includes an inner vane platform relative an axis, the inner vane platform having a non-axisymmetric surface contour.09-29-2011
20110236199NOZZLE SEGMENT WITH REDUCED WEIGHT FLANGE - A nozzle segment for a gas turbine engine includes a flange which extends from a vane platform, the flange includes a hollow cavity.09-29-2011
20100232958NOZZLE BOX OF AXIAL FLOW TURBINE AND AXIAL FLOW TURBINE - A nozzle box 09-16-2010
20100232957Blower Fan - A blower fan includes a housing having a compartment. A stator and an impeller are mounted in the compartment. The housing further includes an air inlet and an air outlet both communicated with the compartment. The impeller has a hub and a plurality of vanes coupled to the hub. Each vane includes an upper edge whose end is an air input portion adjacent to the air inlet of the housing, and an air gap is formed between the upper edge of each vane and a top of the housing, with various widths of the air gap ranging from 0.3 mm to 2.0 mm, while a shortest width of the air gap is formed between the air input portion of the upper edge and the top of the housing for providing reduced turbulence and noises.09-16-2010
20100232956Turbine Singlet Nozzle Assembly with Radial Stop and Narrow Groove - A nozzle assembly for a turbine including an airfoil, inner and outer sidewalls, and inner and outer rings is provided. The sidewalls and rings are coupled together using a weld and mechanical interconnection, including axial and radial mechanical stops to allow for an accurate assembly, to ensure correct radial and axial positions of the parts during welding, to minimize weld shrinkage and to control an axial weld length. The configuration may further include one or more surfaces at an interface between a ring and a sidewall angled away from the interface to form a narrow groove. The configuration further may include a ring with a consumable root portion to facilitate the weld, and to provide a fixturing stop to further ensure that the parts remain in the correct position.09-16-2010
20120087787TURBOFAN JET ENGINE - There is a turbofan jet engine including an engine core. The engine core includes a fan and a compressor. The engine core includes a combustion chamber and a turbine functionally coupled to the compressor. The engine core includes a nozzle in fluid communication with the turbine. The turbofan jet engine includes a nacelle. The nacelle includes a forward extension proximate the fan and extending forward therefrom. The forward extension is funnel shaped to impart radial momentum to intake air during operation. The nacelle includes a vortex device disposed inside the forward extension and shaped to impart angular momentum to intake air. The vortex device includes a fixed blade extending from the interior of the forward extension and set at a rotational angle. The vortex device is shaped and positioned to direct intake air substantially perpendicular to the blades of the fan.04-12-2012
20120328429Ni-BASED ALLOY, AND TURBINE ROTOR AND STATOR BLADE FOR GAS TURBINE - A Ni-based alloy including chromium, cobalt, aluminum, titanium, tantalum, tungsten, molybdenum, niobium, carbon, and boron, the balance being nickel and incidental impurities, is provided. The alloy has an alloy composition of, on the basis of mass percent, chromium: 13.10% to 16.00%, cobalt: 8.00% to 12.50%, aluminum: 2.30% to 3.50%, titanium: 4.80% to 5.50%, tantalum: 0.40% to less than 1.00%, tungsten: 4.50% to 6.00%, molybdenum: 0.10% to 1.50%, niobium: 0.60% to 1.70%, carbon: 0.01% to 0.20%, boron: 0.005% to 0.02%, and the balance: nickel and incidental impurities.12-27-2012
20120099983Torque Balanced, Lift Rotor Module, Providing Increased Lift, With Few or No Moving Parts - A device for continuous torque/anti-torque force balance, except for trim adjustments, of the torque requirements of a single lift rotor while lifting varying load weights and with varying power settings, using a relatively short, cylindrical, vertical duct, flared at the top, air entry end, which flare the lift rotor plane of rotation is parallel to and just below, and is closely contained by the relatively short, cylindrical, vertical duct's inside diameter, and just above a fixed pitch, essentially vertical, array of air foil shaped vanes. In this configuration, lateral lift in an anti-torque rotational direction is generated, in direct proportion to the lift rotor torque requirements, by the lift rotor's rotor wash with swirl air flow component forced interaction with the fixed pitch, essentially vertical, array of air foil shaped vanes to continuously balance torque/anti-torque forces.04-26-2012
20100202878Turbo Engine and Method for Producing Such a Turbo Engine - A flow machine having a housing, an axial diffuser, a rotor for deflecting a fluid between an axial direction and a radial direction, a spiral, and an axial diffuser insert which is at least partially received in the housing. A spiral contour is formed in the diffuser insert and, together with the housing, defines the spiral.08-12-2010
20100166550METHODS, SYSTEMS AND/OR APPARATUS RELATING TO FREQUENCY-TUNED TURBINE BLADES - A method of tuning a compressor stator blade, having a base portion and an airfoil portion, to achieve a desired natural frequency, comprising: a) identifying the natural frequency of the compressor stator blade; b) determining a different target natural frequency for the compressor stator blade; and c) removing material from at least one of the side surfaces of the base portion of the compressor stator blade in an amount and in a configuration that achieves the target natural frequency.07-01-2010
20130017081SYSTEM FOR ENHANCED RECOVERY OF TANGENTIAL ENERGY FROM AN AXIAL PUMP IN A LOOP REACTOR - A loop reactor axial pump system improves conversion of tangential to axial flow of a flowing slurry by attaching a straight impeller section to the inlet of an elbow section. A pump shaft extends rotatably from the elbow through guide vanes located in the impeller section, so that flow from an impeller mounted on the shaft passes through the guide vanes before entering the elbow. When the impeller section is detached, the guide vanes have “see through” access from both ends, thereby allowing the guide vanes to be longer and/or more curved than in the prior art. Guide vanes can be straight or curved, and can have inlet angles approximating the absolute flow angle of the fluid, and/or outlet angles approximating 0 degrees. Additional guide vanes can be included in the elbow. Additional straight pipe sections containing only guide vanes can be included between the impeller section and the elbow.01-17-2013
20130017080FLOW DIRECTING MEMBER FOR GAS TURBINE ENGINE - In a gas turbine engine, a flow directing member includes a platform supported on a rotor, a radially facing endwall, at least one axial surface extending radially inwardly from a junction with the endwall, an airfoil extending radially outwardly from the endwall, and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface and has radially inner and outer groove ends. The outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall. The groove further includes a first groove wall extending from the inner groove end to the outer groove end, and a second groove wall opposed from the first groove wall and extending from the inner groove end to the outer groove end.01-17-2013
20080240913FAN FRAME WITH DIVERSION STRUCTURE - The present invention provides an improved fan frame with a diversion structure. A cooling fan includes a rotor, and fan blades spaced around the rotor at intervals. The fan frame positions the rotor and defines a diversion loop, which corresponds to the air outlet direction when fan blades are turning and has an expanding diversion surface. The fan frame has a diversion surface with diversion ribs spaced at intervals, the placement of the diversion ribs being in a vortex pattern without passing through the hypothetical point of the rotor center. The airflow generated by turning fan blades is guided by the diversion ribs and converted to outlet airflow in axial direction corresponding to the rotor, effectively reducing impact and friction of the gyrate airflow generated by fan blades against the frame diversion surface, lowering the noise level, making air exhaustion smoother, and improving the cooling efficiency of fan.10-02-2008
20080232960Fluid return in the splitter of turbomachines with bypass-flow configuration - A turbomachine, includes an annular flow duct, which downstream of at least one stage, is divided into an outer annular bypass duct and an inner annular core-flow duct via a concentrically arranged splitter, wherein the splitter is designed as an intermediate casing with at least one inner volume, through which fluid may be returned between core-flow stages.09-25-2008
20130170975FIXED VANE-TYPE TURBOCHARGER - The present invention relates to a fixed vane-type turbocharger provided with a fixed vane (07-04-2013
20130170976VTG CARTRIDGE OF AN EXHAUST-GAS TURBOCHARGER - A VTG cartridge (07-04-2013
20130170973MIXING SYSTEM FOR AN EXHAUST GASES AFTER-TREATMENT ARRANGEMENT - A mixing system includes a pipe having a longitudinal axis, in which exhaust gases can flow in a flow direction, a nozzle designed to inject a fluid inside the pipe from an injection inlet arranged in the pipe wall, according to an injection direction, a first mixing device positioned inside the pipe upstream from the injection inlet, the first mixing device including a peripheral portion including blades capable of creating a peripheral swirl along the pipe wall, and a central portion designed to create substantially no turbulence, and a second mixing device positioned inside the pipe downstream from the injection inlet, the second mixing device including a central portion including blades capable of creating a swirl inside the pipe.07-04-2013
20130170974PUMPING ELEMENT DESIGN - A pumping element includes a blade (07-04-2013
20110274540TURBOMACHINE CASING - A turbomachine casing forming a continuous annular ring extending over 360° around a bladed wheel and serving as a propagation medium for rotating waves, each rotating wave being generated by two standing waves of the same frequency, and the casing including at least one longitudinal stiffener at its outer periphery that is dimensioned and positioned in such a manner as to separate the frequencies of the two standing waves of at least one given rotating wave.11-10-2011
20130142639APPARATUS AND METHOD FOR THE FORMING OF TURBINE VANE COVER PLATES - A method is provided for reconditioning a turbomachine vane cover plate, by a forming apparatus. The vane having a mounting portion, an airfoil extending radially outward therefrom and a vane head connected to the airfoil. The vane also having a cover plate connected to the vane head, bulged in a direction opposite to the root. In a first analysis step, dimensions of the vane in relation to the cover plate are determined in respect of predefined reference points. If, thereafter, forming of the cover plate seems necessary and possible based on comparison of measurement values from the analysis step with predefined dimension values, the bulged cover plate is formed, at least essentially pressed smooth, by pressing by the forming apparatus in a forming step. After the forming step, the cover plate is re-treated in one or more follow-up steps. An apparatus is also provided for carrying out the method.06-06-2013
20130183149HOUSING-SIDE STRUCTURE OF A TURBOMACHINE - A housing-side structure of a turbomachine, in particular of a gas turbine, including an in particular segmented jacket ring (07-18-2013
20120251311FUEL PUMP - A fuel pump, including at least one driven impeller made of plastic, which rotates in a pump housing and on the sides having guide blades that each delimit at least one ring of blade chambers, and further having partial ring-shaped channels arranged on both sides in the region of the guide blades in the pump housing, said channels forming delivery chambers with the blade chambers for delivering fuel. An inlet channel leads into the one delivery chamber and the other delivery chamber leads into an outlet channel and the impeller contains carbon fibers embedded in the plastic.10-04-2012
20130115073NACELLE COVER - For a wind turbine, an electromagnetically shielding nacelle cover is formed of a composite material which can comprise, for example, an outer layer made of a fiber material or fiber mats such as glass fiber mats and an interposed foam layer. A conductor layer, for example a mesh, a woven fabric or a coating made of conductive material is integrated between the fiber layers of the composite material to provide electromagnetic shielding of the nacelle. The conductor layer is also connected, or can be connected, directly or indirectly, to at least one conductive structure that is applied to the outside of the nacelle cover.05-09-2013
20130115072ALLOYS FOR BOND COATINGS AND ARTICLES INCORPORATING THE SAME - In an exemplary embodiment, a high temperature oxidation and hot corrosion resistant MCrAlX alloy is disclosed, wherein M comprises cobalt and X comprises, by weight of the alloy, from about 0.001 percent to less than 0.19 percent yttrium. In these alloys, X may also optionally include silicon, including, by weight of the alloy, up to about 1.5 percent. In another exemplary embodiment, a coated article is disclosed. The coated article includes a substrate having a surface. The article also includes a bond coat disposed on the surface. The bond coat comprises a high temperature oxidation and hot corrosion resistant MCrAlX alloy, wherein M comprises cobalt and X comprises, by weight of the alloy, from about 0.001 percent to less than 0.19 percent yttrium.05-09-2013
20130121823CHROMIUM ALLOY - A hypereutectic chromium alloy consisting of 9 to 12 at % tantalum, 4 to 15 at % silicon, 0 to 7 at % molybdenum, 0 to 7 at % aluminium, 0 to 7 at % titanium, 0 to 5 at % rhenium, 0 to 2 at % silver, 0 to 2 at % hafnium, 0 to 2 at % lanthanum, 0 to 2 at % cerium, 0 to 2 at % yttrium and the balance chromium and incidental impurities. The hypereutectic chromium alloy has good oxidation resistance and good fracture toughness. The chromium alloy may be used to make gas turbine engine turbine blades, turbine vanes, turbine seals, combustion chamber tiles, exhaust nozzle segments or steam turbine components.05-16-2013
20130129497EXHAUST-GAS TURBOCHARGER - The invention relates to an exhaust-gas turbocharger (05-23-2013
20130177410CASING FOR AN AIRCRAFT TURBOFAN BYPASS ENGINE - A casing for an aircraft turbofan bypass engine includes an outer ring, an inner hub and a plurality of struts radially extending therebetween. An annular portion of an engine core casing having an outer wall and an inner wall, is disposed between the outer ring and inner hub, forming an annular splitter supporting an upstream splitter tip structure. The annular splitter further includes an intermediate wall disposed in the annular splitter fixed to the outer wall and the struts, to distribute loads from the annular splitter box to the struts.07-11-2013
20130177409ROTOR FOR A PUMP, PRODUCED WITH A FIRST ELASTIC MATERIAL - The invention relates to a rotor for a pump, having at least one blade, the rotor being able to be actuated to rotate about an axis of rotation in order to convey a fluid in the axial or radial direction, the rotor being able to be deformed reversibly elastically in the radial direction between a first, radially compressed state and a second, radially expanded state which the rotor adopts without the effect of external forces, and a third state of the rotor being provided in which, in pumping operation under fluid loading, the rotor is deformed from the first state to beyond the second state.07-11-2013
20130149129VARIABLE GEOMETRY TURBOCHARGER - An exhaust nozzle 06-13-2013
20130149130Fan Hub Frame for Double Outlet Guide Vane - A fan hub frame comprises a circular hub having an opening extending axially wherein an engine core is capable of being positioned, the circular hub having a radially outer surface, the radial outer surface having a plurality of cradles, each of the cradles having a lower surface and fillets disposed between the lower surface and upwardly extending sidewalls, the cradles capable of receiving a double outlet guide vane.06-13-2013
20130149131SURROUND FOR A VERTICAL AXIS WIND TURBINE - A surround for housing a wind turbine directs and concentrates wind from any direction toward the wind turbine. The surround can be formed from an upper apron and a lower apron, each having three or more sides, typically four sides. A fin can be disposed between the upper and lower aprons and extend from a corner thereof toward a central region. The wind turbine can be disposed in the central region. Openings formed on each side of the surround are defined by the upper and lower aprons and the two fins extending from each corner on that side. The openings can deliver wind, from any direction, toward the wind turbine. The upper and lower aprons may angle inward to further concentrate and direct wind toward the wind turbine.06-13-2013
20130149132TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly including a casing adapted to encase an aerofoil structure, the aerofoil structure having a tip, a leading edge and a trailing edge, the casing substantially surrounding the tip of the aerofoil structure, wherein the casing has a set-back portion extending from a position in the region of the leading edge or the trailing edge of the aerofoil structure part way towards a position in the region of the respective other edge and set back from the remainder of the casing away from the aerofoil structure, such that the set-back portion permits a flow over a corresponding portion of the tip of the aerofoil structure.06-13-2013
20130156570WIND COLLECTION APPARATUS - A wind collection apparatus includes an outer tube and an inner tube assembly. The outer tube has a front end and a rear end. The inner tube assembly is installed in the outer tube and has an inner channel and an outer channel. An air-guiding channel is formed between an outer circumferential wall of the inner tube assembly and an inner circumferential wall of the outer tube. The inner channel has two openings. One of the openings is located at the front end and the other one of the openings is located at the rear end. The outer channel is in communication with the inner channel and the air-guiding channel at two ends of the outer channel.06-20-2013
20120282087DIAPHRAGM FOR TURBOMACHINES AND METHOD OF MANUFACTURE - A turbine diaphragm assembly is described having an annulus of static blades, each static blade including at least an aerofoil and an outer platform; and an outer diaphragm ring or segments of a ring for holding the annulus of static blades; with confronting edges of the outer platforms and the ring are held by an interference fit when pushed in axial direction into contact with the interference fit designed to withstand the forces on the diaphragm during operation of the assembled turbine.11-08-2012
20110293412ANTI-ROTATION PIN RETENTION SYSTEM - A turbine engine vane assembly assembled using an anti-retention pin method can include a vane assembly having a vane supported on a shroud ring and a cavity seal coupled to the vane assembly by a securement mechanism. The cavity seal defines a securement receiving portion through which the securement mechanism is inserted. The securement receiving portion also includes a deformation receiver. The securement mechanism has a deformable rim at a first end and a key at a second end. The securement is rotatable between a first configuration and a second configuration where the key matingly engages the shroud ring and the cavity seal to reduce axial movement of the vane assembly. The deformable rim can be deformed into the deformation receiver to prevent rotation of the securement mechanism and disengagement of the securement mechanism from the vane assembly and cavity seal.12-01-2011
20130121822ANTI-RELIEF FAN FRAME BODY STRUCTURE - An anti-relief fan frame body structure includes a frame body and multiple anti-relief sections. The frame body has a receiving space and a shaft seat received in the receiving space. The frame body further has multiple flow guide members extending from a circumference of shaft seat to an inner circumference of the frame body to connect with the inner circumference of the frame body. The anti-relief sections are disposed on the inner circumference of the frame body between the flow guide members to increase the performance of the fan.05-16-2013
20130189095TURBOMACHINE CASING ASSEMBLY - A turbomachine casing assembly includes a first casing element, located radially outward of one or more rotating aerofoil elements of a turbomachine, and a second casing element, located radially distal to the first element. A void is provided at a first end of the first element, between radially proximal faces of the first and second elements. The first end of the first element is located against a corresponding first end of the second element by an energy absorbing element. The first element includes a cantilever, arranged in a region extending along the first element from the first end with a pivot axis at its mid-portion. Release of one of the rotating aerofoil elements, resulting in impact with the first element, further results in the cantilever bending into the void between the first and second elements, enabling the rotating aerofoil element to be trapped within the casing assembly.07-25-2013
20120020778DIAGONAL FAN - A diagonal fan for gaseous media has a diagonal impeller with a plurality of vanes, which are fastened on a carrier plate, and a guide device, adjoining the diagonal impeller in the axial direction on the outflow side, for increasing the pressure of the medium, with a plurality of guide vanes. The vanes of the diagonal impeller and/or the guide vanes of the guide device are three-dimensionally twisted. By means of an intake unit, the gaseous medium can be directed into the diagonal impeller. The intake unit and/or an exhaust unit, by means of which the gaseous medium can be directed out of the guide device, is, or are, provided as an exchangeable module and can be fastened on the diagonal fan by means of a fastening element.01-26-2012
20130195640DUAL-FLOW TURBOMACHINE FOR AIRCRAFT, INCLUDING STRUCTURAL MEANS OF RIGIDIFYING THE CENTRAL CASING - A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled.08-01-2013
20130202428METHOD FOR ATTACHING THE COVER OF A CENTRIFUGAL COMPRESSOR OF A TURBINE ENGINE, COMPRESSOR COVER IMPLEMENTING SAME AND COMPRESSOR ASSEMBLY PROVIDED WITH SUCH A COVER - An attachment arrangement at a middle of a cover having an elastically deformable portion. The cover includes a concave shell including an inner surface spaced apart from the compressor including an impeller including blades by an attachment. The attachment includes one connection end at the middle of the shell, another end attached to a casing of the turbine engine, and an axisymmetric diaphragm having a generally frusto-conical configuration having an arm profile coupled to the end for attachment to the casing by a double-elbow joint having right and obtuse angles when in a rest position. The distance between the inner surface of the shell and upper edges of the blades can be held constant during operation with minimum clearance adjustment. The cover can be moved such that clearance between the cover and blades of the compressor impeller remains substantially constant and as low as possible.08-08-2013
20130202427METHODS FOR THE CONTROLLED REDUCTION OF TURBINE NOZZLE FLOW AREAS AND TURBINE NOZZLE COMPONENTS HAVING REDUCED FLOW AREAS - Embodiments of a method for controllably reducing of the flow area of a turbine nozzle component are provided, as are embodiments of turbine nozzle components having reduced flow areas. In one embodiment, the method includes the steps of obtaining a turbine nozzle component having a plurality of turbine nozzle flow paths therethrough, positioning braze preforms in the plurality of turbine nozzle flow paths and against a surface of the turbine nozzle component, and bonding the braze preforms to the turbine nozzle component to achieve a controlled reduction in the flow area of the turbine nozzle flow paths.08-08-2013
20120093637Axial Compressor - An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length.04-19-2012
20130209247SIDE CHANNEL BLOWER, IN PARTICULAR A SECONDARY AIR BLOWER FOR AN INTERNAL COMBUSTION MACHINE - A side channel blower includes a housing comprising a substantially tangential outlet. A housing cover comprises an axial inlet. At least one conveying duct is configured so that the axial inlet fluidly communicates with the outlet. An impeller is driven by a drive unit. The impeller is rotatably supported in the housing and comprises conveying blades which cooperate with the at least one conveying duct. An interruption region is arranged between the outlet and the axial inlet. The interruption region comprises a radially limiting wall and interrupts the at least one conveying duct in a circumferential direction. A first recess is arranged in the radially limiting wall of the interruption region downstream of the outlet. Further recesses are arranged in the interruption region before the axial inlet and after the outlet. A smallest distance between the further recesses is 0.5 to 3 times a distance between two conveying blades.08-15-2013

Patent applications in class Vane or deflector

Patent applications in all subclasses Vane or deflector