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Rotary kinetic fluid motors or pumps June invention type 06/09Below are recently published patent applications awaiting approval from the USPTO. Recent week's RSS XML file available below.
Listing for abstract view: USPTO application #, Title, Abstract excerpt,Patent Agent. Listing format for list view: USPTO National Class full category number, title of the patent application. 06/25/2009 > patent applications in patent subcategories. invention type
20090162186 - Method and apparatus for vibration-based automatic condition monitoring of a wind turbine: Method and apparatus for vibration-based automatic condition monitoring of a wind turbine, comprising the steps of: determining a set of vibration measurement values of the wind turbine; calculating a frequency spectrum of the set of vibration measurement values; calculating a cepstrum of the frequency spectrum; selecting at least one quefrency... Agent: Siemens Corporation Intellectual Property Department
20090162187 - Counter-rotating compressor case and assembly method for tip turbine engine: A tip turbine engine (10) provides an axial compressor (22) having a compressor case (50) from which extend radially inwardly a plurality of outer compressor airfoils (54). The compressor case (50) is directly driven by the rotation of the turbine (32) and fan (28), while at least one gear (77)... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090162188 - Quick release screen for vent assemblies: A screen member, for a vent assembly including a housing with an inner side, has a base ring and a screen coupled to the base ring. The attachment mechanism is unitarily formed with the base ring to enable readily removal of the screen member. A plurality of cantilevered extending members... Agent: Harness, Dickey & Pierce, P.L.C
20090162190 - Centrifugal impeller with internal heating: An internal heating arrangement for a centrifugal impeller for a gas turbine engine is provided having at least one heating passage extending through into the rotor for directing air bled from the rotor exit along the backface and forwardly through the impeller.... Agent: Ogilvy Renault LLP (pwc)
20090162189 - Systems and methods involving variable throat area vanes: Systems and methods involving variable throat area vanes are provided. In this regard, a representative gas turbine engine includes: a vane extending into a gas flow path and having: an interior operative to receive pressurized air; a pressure surface portion; and a first port communicating between the interior and pressure... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090162191 - Real-time turbomachinery blade breakage monitoring unit and turbo-apparatus: Disclosed herein are a turbo-machinery blade breakage monitoring unit and a turbo-apparatus having the same. The blade breakage monitoring unit includes a pressure sensor disposed near a rotor having a plurality of blades to be rotated at a predetermined speed, the pressure sensor functioning to measure total pressures of the... Agent: Edwards Angell Palmer & Dodge LLP
20090162192 - Variable turbine vane actuation mechanism having a bumper ring: A variable vane actuation assembly for gas turbine engines having rotatable stator vanes comprises an engine casing, a unison ring, a bumper ring, a radial spline connection and a plurality of bumper shims. The engine casing is configured to encase the rotatable stator vanes. The unison ring is disposed concentrically... Agent: Kinney & Lange, P.A.
20090162193 - Turbine inlet guide vane with scalloped platform and related method: A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine... Agent: General Electric Company Ge Global Patent Operation
20090162194 - Annular component: A stator vane assembly for a compressor has a support structure which carries and is bounded by an annular stator vane structure. The stator vane structure comprises a central bore and a sleeve carried on the central bore. The sleeve is disposed between the support structure and bore of the... Agent: Oliff & Berridge, PLC
20090162195 - Fan ring shroud assembly: A shroud assembly for an engine cooling fan positioned between an engine and a radiator includes a ring shroud, a radiator shroud, and a flexible boot. The ring shroud is mounted adjacent to the fan and includes a locking feature. The radiator shroud, which is mounted to the rear of... Agent: Christensen, O'connor, Johnson, Kindness, PLLC
20090162196 - Device for use in detecting dangerous materials or illegal substances in shipping containers: A portable device for use in detecting dangerous materials and illegal substances in shipping containers with the aid of a trained dog. The device is used by a dog handler and constructed to be able to withdraw air from within a shipping container, through a high air vent in it's... Agent: Jack Paavila06/18/2009 > patent applications in patent subcategories. invention type
20090155042 - Multi functional pump for pumping molten metal: The present invention features a multi-functional pump for pumping molten metal, which includes a base that is submerged in molten metal having at least two impeller chambers. The base includes one or more inlet openings and one or more outlet openings. Each outlet opening leads from one of the impeller... Agent: Pearne & Gordon LLP
20090155043 - Vertical multi-phased wind turbine system: A vertical axis multi-phased wind turbine power generating system is disclosed. An adjustable air scoop directs air from a first phase of the prevailing wind into an air turbine for efficient power generation. An exit section, which uses a second phase of the prevailing wind in combination with an optional... Agent: Loen Patent Services
20090155044 - Composite containment casings having an integral fragment catcher: Composite containment casings including a body having an interior and a fragment catcher integrally joined to the interior of the body of the containment casing.... Agent: General Electric Company
20090155045 - Intelligent cooling fan device and fan rotation speed controlling method thereof: A fan cooling device and a method of controlling a fan rotation speed are provided. The fan cooling device includes a thermo sensor, a thermo monitor unit, a processing unit, a driving unit, and a fan. The thermo monitor unit compares the sensed result from the thermo sensor with at... Agent: J C Patents, Inc.
20090155046 - Nacelle assembly having inlet bleed: 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. An opening is disposed on the cowl. A device for... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090155047 - Compressor: A compressor for compressing a gas comprises an impeller wheel mounted within a housing (2) defining an inlet and an outlet. The inlet comprises a map-width enhanced structure with an annular flow passage (11) defined between inner (9) and outer (7) tubular walls. The flow passage (11) is in fluid... Agent: John H. Allie, Krieq Devault LLP
20090155048 - Vortex pump with splitter blade impeller: A vortex pump impeller utilizes primary blades in combination with splitter blades. An increase in total head is observed through exemplary impellers in a vortex pump, compared to an impeller lacking the splitter blades. Single stage and dual stage pumps utilizing the exemplary impellers are also disclosed. Exemplary pumps may... Agent: Standley Law Group LLP
20090155049 - Rotary pump with exclusively hydrodynamically suspended impeller: v
20090155050 - Divergent turbine nozzle: A turbine nozzle includes a row of vanes extending radially in span between inner and outer bands. The vanes include opposite pressure and suction sidewalls and opposite leading and trailing edges. Each vane includes an inner pattern of inner cooling holes and an outer pattern of outer cooling holes distributed... Agent: Francis L. Conte, Esq.
20090155051 - Duplex turbine shroud: A gas turbine engine shroud includes a row of different first and second shroud segments alternating circumferentially therearound. The first segments have a first pattern of first cooling holes extending therethrough. The second segments have a second pattern of second cooling holes extending therethrough. The corresponding patterns have different collective... Agent: Francis L. Conte, Esq.
20090155052 - Mounting tubes for pressurizing an internal enclosure in a turbomachine: A turbomachine comprising high- and low-pressure compressor shafts guided in bearings isolated from an internal enclosure by a sealing end plate, and radial pressurization tubes connecting the enclosure to an air passage passing through the intermediate casing, the ends of these tubes being engaged in sealed manner in radial ducts... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.C.
20090155053 - Turbine cooling flow modulation: Cooling air flow in a gas turbine engine, for example to a first turbine rotary stage is modulated in accordance with a predetermined cooling schedule by means of a fluidic valve arrangement disposed in the interior of the engine. Since fluidic valves have no moving parts they are more reliable... Agent: Oliff & Berridge, PLC
20090155054 - Wall structure for limiting a hot gas path: A wall structure for restricting a hot-gas path in a gas turbine or in a combustion chamber including a first wall segment having a first face, and a second wall segment having a second face. Each wall segment disposed adjacent to each other so as to define an inside of... Agent: Darby & Darby P.C.
20090155055 - Cooling fan: A cooling fan for cooling a heat source includes a frame (10), a stator (20) mounted in the frame, a rotor (30) rotatably attached in the frame, a cover (40) fixed on the frame, and a pair of bearings (50, 60) received in the cover and the frame respectively. The... Agent: PCe Industry, Inc. Att. Steven Reiss
20090155056 - Device for bleeding air from a turbomachine compressor: A turbomachine compressor, such as a high-pressure compressor, including air bleed means comprising a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor, a screen sheet of annular shape being mounted radially inside... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.C.
20090155057 - Compressor variable stage remote actuation for turbine engine: A turbine engine locates an actuator (55) for the compressor variable guide vanes (54a, b, c) at a location remote from the variable guide vanes. The actuator is connected to the variable guide vanes through a torque rod (56) inside an inlet guide vane. The torque rod rotatably drives an... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090155058 - Variable geometry compressor module: A variable geometry compressor housing module has a housing (1) into which a diffuser plate (3), a unison ring (5) and vanes (7) supported by a backplate (9) are inserted. The backplate is fixed to the housing by a crimping process. An actuation mechanism (13) for actuating the vanes (7)... Agent: Honeywell International Inc. Patent Service
20090155059 - Centrifugal blower: A centrifugal blower includes a casing, a motor fixed in the casing, a fan structure, and an anti-leakage element. The casing has a top portion having an inlet, a bottom portion, and a side wall respectively connecting the top and bottom portions and having an outlet. The fan structure disposed... Agent: Jianq Chyun Intellectual Property Office
20090155060 - Integrated fan with pump and heat exchanger cooling capability: Disclosed is a compact and integrated fan, pump, and heat exchanger system where air-cooling is performed via the fan, liquid cooling is performed via a pump, and the drilled pump diffusers act as a heat exchanger. The pump has drilled diffusers through which liquid passes into the volute, the drilled... Agent: Townsend And Townsend And Crew, LLP
20090155061 - sectorized nozzle for a turbomachine: A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.C.
20090155062 - Method of designing a multistage turbine for a turbomachine: A method of designing a multistage turbine for a turbomachine in which each turbine stage comprises a stator row and a rotor row each made up of an annular row of airfoils, wherein, for all of the stator or rotor rows, it consists in simultaneously modifying the shapes of the... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.C.
20090155063 - Intermediate casing for an aircraft jet engine, of improved design: The invention relates to an intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also front and rear flanges (25, 27) which are arranged radially inside with respect to the outer shell, the casing (21) also comprising structural arms (17) which extend radially between the... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.C.
20090155064 - System, method and apparatus for two-phase homogenizing stage for centrifugal pump assembly: A two-phase, homogenizing or mixing stage for a centrifugal pump assembly homogenizes the fluids being circulated therethrough. The mixing stage produces high shut-in head pressure and a very high maximum flow rate. The mixing stage has a diffuser with fixed diffuser vanes that extend radially or tangentially at acute angles.... Agent: Bracewell & Giuliani LLP
20090155065 - Composite containment casings: Composite containment casing including a body having an interior, an abradable system integrally joined to the interior of the body of the containment casing wherein the abradable system comprises, a sandwich structure including a first facesheet and a second facesheet position about at least one core layer, and at least... Agent: General Electric Company
20090155066 - Pump driving apparatus: A guide tube 23 is provided coaxially with an output shaft 4 of a motor M inside a pump chamber 8, and the ends in the axial direction of the guide tube 23 are fitted into and make sliding contact with a case inner wall surface that forms the pump... Agent: Birch Stewart Kolasch & Birch
20090155067 - Nacelle 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... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090155068 - Radial loading element for turbine vane: A vane assembly for a gas turbine engine comprising a number of radial loading elements disposed between lugs of the vane ring and the vane support, such as to generate a radial load force against the vane ring. The radial load force prevents unwanted relative movement between the vane ring... Agent: Ogilvy Renault LLP (pwc)
20090155069 - Axial loading element for turbine vane: A vane assembly for a gas turbine engine comprising an axial loading element disposed between a mounting element of the vane ring and a cooperating portion of the supporting structure, such as to generate a load force therebetween in an axial direction. The axial load force limits unwanted relative movement... Agent: Ogilvy Renault LLP (pwc)
20090155070 - Intermediate casing extension for an aircraft jet engine, comprising a sectorised annular groove for receiving the nacelle covers: The invention relates to an extension (30) of an intermediate casing for an aircraft jet engine, intended to project towards the downstream end from an external shell of the intermediate casing, this extension comprising an annular connecting downstream end (64) forming an annular groove (66) open radially towards the outside,... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.C.
20090155071 - Sealing a hub cavity of an exhaust casing in a turbomachine: The exhaust casing of a turbomachine includes a cylindrical jacket for guiding a flow of exhaust gas and for defining a hub cavity inside the casing, the jacket including at its ends an annular flange and a radial annular portion extending inwards and formed with an annular rim that is... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.C.
20090155072 - Fan nacelle flow control: This disclosure relates to a gas turbine engine including a core engine that drives a fan. A fan nacelle surrounds the fan and provides an inner surface facing the fan. The fan nacelle includes an inlet lip adjoining the inner surface. A ring is arranged at the inner surface and... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090155073 - Sealing the fastening of a bearing support in a turbomachine: A turbomachine including a shaft guided in an upstream bearing and a downstream bearing, the upstream bearing being carried by a first annular support that is fastened by bolts to a casing via a second annular support that carries the downstream bearing, wherein the ends of the fastener bolts are... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.C.06/11/2009 > patent applications in patent subcategories. invention type
20090148268 - Mixer for jet spray: Mixer for a jet spray including a regulator equipped with hot and cold water inlets, a mixed water outlet and shutters arranged between the outlet and, respectively, the hot water inlet and the cold water inlet; motorized means for actuating the shutters; an interception assembly, comprising a manifold mounted axially... Agent: Seed Intellectual Property Law Group PLLC
20090148269 - Gas turbine engines and related systems involving air-cooled vanes: Gas turbine engines and related systems involving air-cooled vanes are provided. In this regard, a representative vane for a gas turbine engine includes: an airfoil having a leading edge, a pressure surface, a trailing edge and a suction surface; and a cooling air channel; the suction surface being formed by... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090148270 - Device for detecting a fractured shaft of a gas turbine and a gas turbine: The present technology relates generally to a device for the detection of a shaft fracture in a rotor of a turbine, for example a medium pressure turbine such as a gas turbine, in particular an aircraft engine, whereby at least one stator-side sensor element is positioned downstream from the turbine... Agent: Mcandrews Held & Malloy, Ltd
20090148271 - Bearing mounting system in a low pressure turbine: A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The... Agent: Kinney & Lange, P.A.
20090148272 - Tip turbine engine and operating method with reverse core airflow: A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or educing the number of axial compressor (122) stages by moving the core airflow inlet (27) aft of the fan (24). As a result, the core airflow entering the core airflow inlet is... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090148273 - Compressor inlet guide vane for tip turbine engine and corresponding control method: A tip turbine engine (30) includes a low pressure compressor (22) having a plurality of inlet guide vanes (55) that are mounted at an inlet to the compressor case (50). Each inlet guide vane (55) includes at least one fluid outlet (56) proximate a trailing edge of the inlet guide... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090148274 - Compact bearing support: The compact squirrel-cage bearing support comprises a first end portion, a second end portion axially spaced from the first end portion, and a plurality of beams interconnecting the first end portion to the second end portion. The beams have a length that is greater than an axial spacing between the... Agent: Ogilvy Renault LLP (pwc)
20090148275 - Laminate air seal for a gas turbine engine: A laminate air seal for a gas turbine engine includes at least one fabric layer made of fiberglass, ceramic fiber, basalt and/or carbon, and a polymeric resin that is stable at an operating temperature of the gas turbine engine. The resin may be preimpregnated into the fabric layers, or introduced... Agent: Kinney & Lange, P.A.
20090148277 - Gas turbine engines and related systems involving blade outer air seals: Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes: an annular arrangement of outer air seal segments, each of the segments having ends, the segments being positioned in an end-to-end... Agent: Thomas, Kayden, Horstemeyer & Risley, LLP
20090148276 - Seal assembly for a fan rotor of a tip turbine engine: A seal assembly (118) mounted within a nonrotatable static inner support structure (16) for engagement with an axial seal face surface (114) and a radial seal face surface (116). The radial seal (120) engages the axial seal face surface and the axial seal (122) engages the radial seal face surface.... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090148278 - Abradable coating system: This invention relates to an abradable coating system for use in axial turbine engines. When coated onto a turbine ring seal segment the coating system may allow formation of an individualized seal between turbine blade disks and the surrounding ring seal without causing excessive wear to the blade tips. The... Agent: Siemens Corporation Intellectual Property Department
20090148279 - Gas turbine belly band seal anti-rotation structure: A seal strip assembly for use in a turbomachine having a plurality of stages including rotationally driven disks, and arms on opposed portions of adjoining disks to define paired arms with a space therebetween. The seal strip assembly includes a seal strip positioned in the space between the paired arms... Agent: Siemens Corporation Intellectual Property Department
20090148280 - Turbine vane for a gas turbine engine: A turbine vane for a gas turbine engine having an outer wall of nonuniform thickness. The turbine vane may be formed from a generally elongated airfoil formed from an outer wall having a leading edge, a trailing edge, a pressure side, a suction side, a first endwall at a first... Agent: Siemens Corporation Intellectual Property Department
20090148281 - Resinous shroud and manufacturing method of the same: A resinous shroud includes a resinous wall portion formed between a portion corresponding to a casing and a portion corresponding to a retaining member in a shroud portion when a resin material is filled from a gate portion. Thereby, a flow of the resin material to the portion corresponding to... Agent: Harness, Dickey & Pierce, P.L.C
20090148282 - 3d contoured vane endwall for variable area turbine vane arrangement: A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090148283 - Nozzle ring adhesive bonded blading for aircraft engine compressor: A compressor nozzle ring for an aircraft includes an inner shroud, an outer shroud and a multiplicity of blades extending from the inner shroud to the outer shroud. Each blade passes through the inner shroud and is attached to it with sealing cement containing an organic polymer adhesive. The adhesive... Agent: Oblon, Spivak, Mcclelland Maier & Neustadt, P.C.
20090148284 - Vacuum pump: A vacuum pump for producing a vacuum in a space which is to be evacuated comprises a housing (10) having a cylindrical inner space (22). An expeller (26) is arranged eccentrically in the inner space (22). A helical sealing element (34) is provided between the expeller (26) and an inner... Agent: Fay Sharpe LLP06/04/2009 > patent applications in patent subcategories. invention type
20090142178 - Wind turbine tower and a control system and method for altering the eigenfrequency of a wind turbine tower: A wind turbine comprising a wind turbine rotor with at least one wind turbine blade, a wind turbine tower, such as a standard tubular steel tower, positioned on a foundation and connected to the wind turbine rotor through a wind turbine nacelle, and a control for establishing oscillation control values... Agent: St. Onge Steward Johnston & Reens, LLC
20090142179 - Centrifugal fan: A centrifugal fan includes a fan frame (20), and a stator (30) and a rotor (40) received in the fan frame. The fan frame includes a bottom base (22), an opposite top cover (21) and a side wall (23) interconnecting the bottom base and the top cover. A first air... Agent: PCe Industry, Inc. Att. Steven Reiss
20090142180 - Circumferential sealing arrangement: A circumferential sealing arrangement is disclosed herein. The circumferential sealing arrangement includes a structure operable to rotate about an axis and having a first surface facing radially outward. The circumferential sealing arrangement also includes a static housing circumscribing the rotatable structure. The circumferential sealing arrangement also includes at least one... Agent: Macmillan, Sobanski & Todd, LLC
20090142181 - Gas turbine engine systems involving mechanically alterable vane throat areas: Gas turbine engine systems involving mechanically alterable vane throat areas are provided. In this regard, a representative vane for a gas turbine engine includes: a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090142182 - Gas turbine engines and related systems involving offset turbine frame struts: Gas turbine engines and related systems involving offset hub struts are provided. In this regard, a representative bearing assembly for a gas turbine engine includes: a bearing operative to support a rotatable shaft; an annular hub positioned about the bearing; and an annular array of struts extending radially outwardly from... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090142183 - Turbo vacuum pump: A turbo vacuum pump of the present invention includes a suction part for sucking gas in an axial direction; a discharge section in which rotating impellers and stationary impellers are alternately arranged; a rotating shaft for rotating the rotating impellers; and a turbine impeller part fixed to the suction side... Agent: Wenderoth, Lind & Ponack, L.L.P.
20090142184 - Vectoring transition duct for turbine engine: A transition duct (112) is provided at the outlet of a turbine engine. The transition duct transitions the outlet of the tip turbine engine (10) from round to rectangular. The transition duct also provides a plurality of variable vanes at the outlet of the transition duct. The transition duct incorporates... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090142185 - Adjusting ring for adjusting the blades of the vtg distributor of exhaust gas turbochargers: The invention relates to an adjusting ring (1) for adjusting the blades of the VTG distributor of exhaust gas turbochargers, comprising a bearing ring (2) and a lever engagement ring (3) connected to said bearing ring (2), the bearing ring (2) and lever engagement ring (3) being separately manufactured individual... Agent: Borgwarner Inc. C/o Patent Central LLC
20090142186 - Variable geometry turbine: A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary... Agent: John H. Allie, Esq. Krieg Devault LLP
20090142187 - Seals in steam turbine: A seal structure for a steam turbine is provided, which is capable of suppressing transfer of heat generated by a friction between a rotating portion and a fixed portion to the rotating portion and of suppressing an increase in the temperature of the rotating portion. A labyrinth seal device serves... Agent: Mattingly & Malur, P.C.
20090142188 - Seal assembly for a fan-turbine rotor of a tip turbine engine: A seal assembly (116) mounted within a rotationally fixed static outer support structure (14) for engagement with an annular seal face surface (172) located upon a fan-turbine rotor assembly. The seal assembly provides minimal leakage of core airflow when the airflow is turned and diffused by the diffuser section (74)... Agent: Carlson, Gaskey & Olds/pratt & Whitney
20090142189 - Abradable labyrinth tooth seal vane shroud through flow-platform cover: A seal assembly (52, 54) for a gas turbine engine (10). The seal assembly (52, 54) includes a first seal member (40) including an abradable structure having at least first and second seal portions (58, 64) radially spaced from each other, and a second seal member (44) including first and... Agent: Siemens Corporation Intellectual Property Department
20090142190 - Frame structure for fan: The present invention relates to a fan frame structure including a plastic frame and a metal fixing frame, in which at least two support arms are disposed on the rim of the fixing frame and extended outwardly therefrom, the outwardly extended distance of each support arm shall be beyond the... Agent: Bacon & Thomas, PLLC
20090142191 - Fan comprising a fan wheel: A fan for cooling a circuit board (26) has a fan wheel (10; 10′) that is adapted for rotation about a rotation axis (11) and in a predetermined rotation direction (14), and an outer wall (18) that is rigidly joined to an inner wall (16). Defined between the two walls... Agent: Ware Fressola Van Der Sluys & Adolphson, LLPPrevious industry: Material or article handling
Next industry: Fluid reaction surfaces (i.e., impellers)
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