Selectively Adjustable Vane Or Working Fluid Control For Bypass Patents (Class 415/145)
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Publication number: 20150125272Abstract: A regulating flap arrangement (1) of an exhaust-gas turbocharger (3) having a flap shaft (5), which is guided by means of a bushing (10) in the turbine housing (2). A shaped sealing ring (13), as viewed in cross section, has at least one cavity (14). The shaped sealing ring (13) bears simultaneously against the first sealing surface (11) and against the second sealing surface (12), and in order to impart its sealing action, is compressed and deformed in the axial direction (15) of the flap shaft (5).Type: ApplicationFiled: April 29, 2013Publication date: May 7, 2015Inventor: Sebastian Mack
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Publication number: 20150125273Abstract: An exhaust-gas turbocharger (1) with a turbine housing (2) which has a turbine housing inlet (8) and a turbine housing outlet (9) for exhaust gas, and which has a wastegate duct (19) between the turbine housing inlet (8) and the turbine housing outlet (9), and a flap arrangement (10) having a pivotable flap plate for opening and closing the wastegate duct (19), wherein the flap plate is in the form of an elastic spring disk (11).Type: ApplicationFiled: June 14, 2013Publication date: May 7, 2015Inventor: Juergen Tschirschke
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Publication number: 20150118027Abstract: In an adjusting device fir an exhaust gas turbocharger with a first adjusting member and a second adjusting member for operating a valve element for varying the flow cross-section of a bypass duct of a flow-through exhaust gas guide portion of a turbine of an exhaust gas turbocharger, the first adjusting member and the second adjusting member are connected so as to be pivotable relative to one another by a pin-shaped connecting element with a locking element establishing a pivot joint of the first adjusting member and the second adjusting member with a predetermined axial engagement force.Type: ApplicationFiled: December 13, 2014Publication date: April 30, 2015Inventors: Nicolas ZIEBOLI, Hermann BURMESTER
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Publication number: 20150104289Abstract: Methods and apparatus to adjust bleed ports on an aircraft engine are disclosed. An example apparatus for bleeding air from a multi-stage compressor of an aircraft engine includes a compressor case having a plurality of bleed ports. A first bleed port is associated with a first stage of a compressor, and a second bleed port is associated with a second stage of the compressor. The apparatus includes a plenum connected to the compressor case to define a plenum cavity. The plenum fluidly coupling the first and second bleed ports to a fluid conduit for providing bleed air to one or more systems of an aircraft. The apparatus also includes a bleed port selection mechanism located within the plenum cavity. The bleed port selection mechanism including a first portion proximate the first bleed port and operable to prevent fluid flow through the first bleed port.Type: ApplicationFiled: February 25, 2014Publication date: April 16, 2015Inventors: Steve G. Mackin, Sean C. Thomas, Brian W. Debronsky
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Publication number: 20150098803Abstract: An exhaust turbocharger has a wastegate valve and a thrust circulation valve, which can be actuated by a single, common actuator. The actuation of the thrust circulation valve is dependent on the positioning velocity of the actuator.Type: ApplicationFiled: March 7, 2013Publication date: April 9, 2015Inventors: Florian Kronschnabl, Roland Herfurth, Christoph Sparrer
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Publication number: 20150071759Abstract: A method for controlling air flow through a compressor recirculation passage, comprising: during a first condition: reducing air flow through the compressor recirculation passage based on a margin, the margin based on a rate of air flow at a compressor inlet, a rate of air flow through the compressor recirculation passage, and a rate of EGR flow. In this way, the CRV recirculation flow may be controlled to be less than the amount that could potentially backflow into an air filter disposed in the air intake passage, thus preventing EGR contained in the CRV recirculation flow from fouling the air filter with soot, oil and water.Type: ApplicationFiled: January 21, 2014Publication date: March 12, 2015Applicant: Ford Global Technologies, LLCInventors: David Karl Bidner, Julia Helen Buckland
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Patent number: 8961114Abstract: One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide valve axially translatable within the duct is operable to open and close or vary a variable area between the heat exchangers and one of inner and outer casings bounding the duct. The heat exchangers may be being circumferentially distributed around an annular duct and include radial or circumferentially curved heat transfer tubes or vanes.Type: GrantFiled: November 22, 2010Date of Patent: February 24, 2015Assignee: General Electric CompanyInventor: Michael Anthony Ruthemeyer
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Publication number: 20150050128Abstract: A turbo pump has a common axis of rotation for a plurality of compressor and turbine wheels. One or more of the turbine and compressor wheels defines a gas passage axially therethrough, said gas passage being associated with another of the turbine and compressor wheels. The arrangement provides a compact multi-stage turbocharger.Type: ApplicationFiled: March 8, 2013Publication date: February 19, 2015Inventor: Olivier Roques
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Publication number: 20150044033Abstract: A turbocharger includes an open-and-close mechanism which opens and closes a circulation hole through which an exhaust gas flows into a turbine housing or the exhaust gas flows out of the turbine housing. The open-and-close mechanism includes: a valve; and an attachment plate one end of which is fixed to the valve, and the other end of which is provided with an insertion hole through which a stem turnably supported by the turbine housing is inserted, and an exposure hole which communicates with the insertion hole to expose part of an outer peripheral surface of the stem. The diameter of the insertion hole is gradually smaller in a direction of insertion of the stem. The stem includes a tapered portion whose diameter is gradually smaller toward its tip end in the direction of insertion into the insertion hole.Type: ApplicationFiled: October 27, 2014Publication date: February 12, 2015Applicant: IHI CorporationInventor: Tomokazu MURAYAMA
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Patent number: 8950069Abstract: A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system.Type: GrantFiled: December 21, 2007Date of Patent: February 10, 2015Assignee: Rolls-Royce North American Technologies, Inc.Inventor: Robert A. Ress, Jr.
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Patent number: 8944754Abstract: A gas-turbine engine with at least one compressor and at least one bleed-air tapping device, which includes an annular duct in a radially outer wall of a flow duct, and with an annular closing element, which is arranged in the region of the annular duct and can be moved in a substantially axial direction from a closed position to an open position, with the closing element having an annular flow divider projection which in the open position projects in the flow duct.Type: GrantFiled: May 10, 2012Date of Patent: February 3, 2015Assignee: Rolls-Royce Deutschland Ltd & Co KGInventor: Sacha Pichel
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Publication number: 20150016963Abstract: A turbine comprises a turbine housing defining a turbine inlet upstream of a turbine wheel and a turbine outlet downstream of the turbine wheel; a wastegate passage connecting the turbine inlet and the turbine outlet; and a wastegate valve comprising a movable valve member. The wastegate valve has an open state and a closed state. The valve member is mounted to an actuation member passing through an actuator conduit of the turbine housing, and movable so as to move the wastegate valve between the open and closed states. The turbine further comprises a sealing arrangement configured to provide a seal arranged to substantially prevent gas from passing from the turbine outlet into the actuator conduit. The sealing arrangement is configured such that when the valve member is urged into the closed state by the actuator member the sealing effectiveness of the sealing arrangement is increased.Type: ApplicationFiled: July 10, 2014Publication date: January 15, 2015Inventor: James Alexander McEwen
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Publication number: 20150010390Abstract: A turbocharger includes: an inflow passage to guide a fluid to a housing space for a turbine wheel; an exhaust passage to discharge the fluid having rotated the turbine wheel from a turbocharger body; a bypass passage connecting the inflow passage and the exhaust passage; a valve unit having one valve for a communicating portion between the exhaust passage and the housing space, and another valve for the bypass passage; an actuator to turn the valve unit and a stem connected to the valve unit about an axis of the stem; and a controller to operate the actuator. The controller adjusts the opening of the bypass passage by turning the valve unit within a specific range about the axis of the stem when a specific condition is met, and closes the exhaust passage by turning the valve unit beyond the specific range when the specific condition is not met.Type: ApplicationFiled: June 24, 2014Publication date: January 8, 2015Applicant: IHI CorporationInventors: Kazuhiro ONITSUKA, Takahiro Kobayashi
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Patent number: 8926264Abstract: In order to improve a turbo compressor comprising a compressor housing, in which an incoming gas volume flow is supplied to an impeller channel through an inlet channel, is compressed in the impeller channel by an impeller and is discharged from the impeller channel via an outlet channel, and a flow diversion channel which is provided in the compressor housing, extends outside of the impeller channel and the inlet channel, opens into the inlet channel with an opening on the inlet side and into the impeller channel with an opening on the impeller side and conveys a diversion volume flow between the openings as a function of a difference in pressure, in such a manner that it can be operated optimally with volume flows which are far below the volume flow provided for the design point it is suggested that the flow diversion channel have a cross-sectional flow area increasing in size up to the opening on the inlet side proceeding from the opening on the impeller side.Type: GrantFiled: June 14, 2012Date of Patent: January 6, 2015Assignee: Piller Industrieventilatoren GmbHInventors: Hans-Joachim Ring, Joel Kofi Adomako
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Publication number: 20150003959Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.Type: ApplicationFiled: December 26, 2013Publication date: January 1, 2015Applicant: Rolls-Royce North American Technologies Inc.Inventor: Robert T. DUGE
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Patent number: 8919784Abstract: A seal assembly for a fan duct metering valve disposed within a casing of a gas turbine engine includes a tab for extending through an opening in the casing and attaching to the valve, a carrier for extending into the opening and engaging the valve such that fluid does not leak between the valve and the carrier.Type: GrantFiled: June 29, 2011Date of Patent: December 30, 2014Assignee: United Technologies CorporationInventors: Darren M. Smith, Judith F. Brooks
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Publication number: 20140369804Abstract: The present disclosure relates to shroud bleed in centrifugal compressors. An air-limiting component 130 may be located adjacent to a shroud 120. The shroud 120 may have a primary bleed slot 210, and the air-limiting component 130 may have a secondary bleed slot 310. The primary bleed slot 210 and the secondary bleed slot 310 may overlap at an effective bleed slot location. The air-limiting component 130 may rotate relative to the shroud 120, which may change a streamwise location of the effective bleed slot.Type: ApplicationFiled: June 11, 2014Publication date: December 18, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Benjamin E. Fishler
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Publication number: 20140363277Abstract: A structural assembly for a fluid-flow machine includes a main flow path boundary, a row of relatively rotating blades with a gap existing between the blade ends and the main flow path boundary. A secondary flow duct is connected to the main flow path via the two openings spaced apart in the flow direction. A structural assembly has at least one support component and at least one replaceable plug connected directly or indirectly to the support component. The replaceable plug includes a part-section of a secondary flow duct, where the part-section complements at least one further part-section of the secondary flow duct extending outside the plug in the structural assembly to form a secondary flow duct which is continuous between its openings.Type: ApplicationFiled: May 28, 2014Publication date: December 11, 2014Applicant: Rolls-Royce Deutschland Ltd & Co KGInventor: Volker GUEMMER
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Publication number: 20140348629Abstract: A turbomachine assembly generally has a compressor section including a first end of a rotating member and a first cover configured to substantially enclose the first end therein. The compressor section includes a bypass valve coupled to the first cover portion and configured to control fluid flow within the compressor section to enable controlling at least one operating parameter of the compressor section. A turbine section is arranged in flow communication with the compressor section. The turbine section includes a second end of the rotating member and a second cover configured to substantially enclose the second end therein. At least one regulating valve that is in flow communication with the compressor section and the turbine section, wherein the regulating valve is configured to control fluid flow between the compressor and turbine sections to enable controlling at least one operating parameter of the turbine section.Type: ApplicationFiled: May 21, 2013Publication date: November 27, 2014Applicant: TurboGen, LLCInventor: John Kuczaj
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Patent number: 8888444Abstract: A steam seal system is disclosed. In one embodiment, the steam seal system includes: a low pressure steam turbine positioned on a shaft; a pair of end packings surrounding the shaft, each of the pair of end packings located proximate an axial end of the low pressure steam turbine along the shaft; and an pair of extraction conduits fluidly connected to the low pressure steam turbine and the shaft, the pair of extraction conduits connected to the shaft at a location axially outward of the pair of end packings and the low pressure steam turbine.Type: GrantFiled: May 16, 2011Date of Patent: November 18, 2014Assignee: General Electric CompanyInventors: Nestor Hernandez Sanchez, Kamlesh Mundra
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Patent number: 8882443Abstract: A turbomachine or high pressure compressor including a stator casing housing a plurality of compression stages that are spaced apart in an axial direction along the central axis of the turbomachine, each compression stage including a row of rotor blades followed by a row of stator vanes. The compressor further includes an air injection system including at least one air injection passage through the casing and including an outlet segment that opens out in an inclined manner upstream from and directed towards a row of rotor blades into a set-back zone of the inside face of the casing.Type: GrantFiled: May 28, 2009Date of Patent: November 11, 2014Assignee: SNECMAInventors: Xavier Agneray, Alexandre Chartoire, Armel Touyeras, Julien Loucheux
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Publication number: 20140321986Abstract: A turbocharger includes: a turbine housing including a through-hole through which a turbine impeller is bypassed; and a wastegate valve configured to open and close the through-hole. A biasing portion biases the wastegate valve and a support plate in opposite directions, and restrains rotation of the wastegate valve relative to the support plate.Type: ApplicationFiled: July 9, 2014Publication date: October 30, 2014Applicant: IHI CorporationInventors: Yukio TAKAHASHI, Shinichi Kaneda
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Publication number: 20140314548Abstract: One embodiment of the present invention is a unique vane system. Another embodiment is a unique gas turbine engine. Another embodiment is a unique method for manufacturing a bypass vane stage. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbine engines and vane systems for turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: June 30, 2014Publication date: October 23, 2014Inventors: Jonathan Michael Rivers, Roy David Fulayter
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Patent number: 8858164Abstract: An air discharge system for an aviation turbomachine compressor is disclosed. The discharge system includes at least one discharge valve. Each valve includes a valve body suitable for moving between an open position and a closed position of the discharge valve, a camshaft including a cylindrical rod carrying a cam mounted to bear against the valve body in such a manner that rotating the camshaft causes the valve body to move between its open and closed positions, and a device for keeping the cam bearing permanently against the valve body. The discharge system further includes at least one main electric motor having its rotor suitable for driving the camshaft of each discharge valve in rotation, and an electronic control system for controlling each main electric motor.Type: GrantFiled: June 15, 2009Date of Patent: October 14, 2014Assignee: SNECMAInventors: Baptiste Colotte, Bruno Gaully
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Publication number: 20140271110Abstract: A compressor start bleed system for a turbine system includes a compressor section. Also included is a turbine section disposed downstream of the compressor section. Further included is at least one duct fluidly coupled to the compressor section, wherein the at least one duct is configured to route a start bleed extraction from the compressor section to a location downstream of the turbine section. Yet further included is at least one control device of the at least one duct configured to actively modulate the start bleed extraction during a part speed operation of the turbine system.Type: ApplicationFiled: March 15, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Steven William Tillery, David August Snider
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Patent number: 8834108Abstract: A running-gap control system of an aircraft gas turbine with a core engine including a turbine whose blade rows have a running gap 13 to the turbine casing 12, with the turbine casing 12 being surrounded by a core-engine ventilation compartment 15 enclosed by a fairing 2 of the core engine, with the fairing 2 forming an inner wall of a bypass duct 1. Air from the bypass duct 1 can be introduced via at least one inlet nozzle 5 into a cooling-air distributor 7 by a control system 6, 10, 11 and the air is subsequently returned to the bypass flow 3.Type: GrantFiled: February 24, 2010Date of Patent: September 16, 2014Assignee: Rolls-Royce Deutschland Ltd & Co KGInventors: Dimitrie Negulescu, Stephan Lisiewicz
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ACTIVE BYPASS FLOW CONTROL FOR A SEAL IN A GAS TURBINE ENGINE CROSS-REFERENCE TO RELATED APPLICATION
Publication number: 20140248132Abstract: An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed. The active bypass flow control system is an adjustable system in which one or more metering devices may be used to control the flow of bypass compressed air as the flow of compressed air past the outer balance seal changes over time as the outer balance seal between the rim cavity and the cooling cavity wears. In at least one embodiment, the metering device may include a valve formed from one or more pins movable between open and closed positions in which the one pin at least partially bisects the bypass channel to regulate flow.Type: ApplicationFiled: February 28, 2014Publication date: September 4, 2014Applicant: Siemens Energy, Inc.Inventors: Todd A. Ebert, Keith D. Kimmel -
Publication number: 20140248133Abstract: An active bypass flow control system for controlling bypass compressed air based upon leakage flow of compressed air flowing past an outer balance seal between a stator and rotor of a first stage of a gas turbine in a gas turbine engine is disclosed.Type: ApplicationFiled: February 28, 2014Publication date: September 4, 2014Applicant: Siemens Energy, Inc.Inventors: Todd A. Ebert, Keith D. Kimmel
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Publication number: 20140241863Abstract: A turbine exhaust section comprises a turbine exhaust case having radially outer and inner ducts defining therebetween an annular exhaust portion for the hot exhaust gases, and an exhaust mixer projecting axially rearwardly from the turbine exhaust case for mixing the hot exhaust gases with a cooler bypass duct flow. The upstream end of the exhaust mixer surrounds a downstream end of the outer duct and defines therewith an axially extending overlap joint with a radial play between the outer duct and the exhaust mixer. A sliding attachment in the radial direction is provided between the outer duct and the exhaust mixer for accommodating differences in thermal growth during engine operation. The sliding attachment includes a circumferential array of sliding guides extending radially through the axially extending overlap joint. A resilient sealing ring seals the radial play between the outer duct and the exhaust mixer at the overlap joint.Type: ApplicationFiled: February 22, 2013Publication date: August 28, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventor: MARC TARDIF
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Patent number: 8814499Abstract: Provided is a centrifugal compressor having improved operation performance to improve durability. The centrifugal compressor includes an impeller connected to a rotary shaft and configured to radially eject a fluid suctioned in an axial direction upon rotation thereof; a shroud configured to cover front and rear sides of the impeller and having a suction port formed to face one surface of the impeller at a center of one side thereof; a volute chamber formed at an outer periphery of the shroud in a circumferential direction thereof and configured to guide the fluid ejected by the impeller to an ejection port; and a regulator installed at one side of the shroud and configured to selectively communicate a space formed at the other surface of the impeller with the outside.Type: GrantFiled: March 15, 2011Date of Patent: August 26, 2014Assignee: Korea Fluid Machinery Co., Ltd.Inventor: Chun Kyung Kim
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Patent number: 8814506Abstract: There is provided a variable capacity turbine that is capable of suppressing separation from an outer peripheral face of an involute dividing wall at an inlet portion of an outer scroll, enhancing performance, and increasing a flow rate. The variable capacity turbine includes: a turbine housing having an involuted scroll formed therein; a turbine wheel rotatably provided on an inner periphery side of the scroll; the involute dividing wall mounted on the turbine housing to divide the scroll into an inner scroll and the outer scroll; and a flow regulating valve for opening and closing an introducing port formed at an inlet end of the outer scroll. The inlet portion of the outer scroll is formed to have a continuous and gentle throttle flow path from an upstream side to a downstream side.Type: GrantFiled: October 13, 2009Date of Patent: August 26, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventor: Atsushi Matsuo
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Publication number: 20140234081Abstract: A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.Type: ApplicationFiled: February 19, 2013Publication date: August 21, 2014Applicant: Rohr, Inc.Inventors: Daniel M. Amkraut, Michael John Layland, Norman John James
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Patent number: 8789369Abstract: A turbocharger of a supercharging apparatus includes a turbine impeller, which is rotatable by exhaust gas discharged from an internal combustion engine of a vehicle. An electric heater is placed in an exhaust passage, which extends from an exhaust outlet of the internal combustion engine to the turbine impeller. The electric heater generates a heat when the electric heater is energized.Type: GrantFiled: July 11, 2012Date of Patent: July 29, 2014Assignee: Denso CorporationInventor: Osamu Sato
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Patent number: 8770914Abstract: A steam turbine system including a steam turbine is provided. The steam turbine system includes a high-pressure side steam inlet device, a low-pressure side steam device, and a control device for controlling the steam turbine. An additional steam inlet device is also included arranged between the high-pressure side steam inlet device and the low-pressure side steam device. The control device control a supply of steam via the additional steam inlet device as a function of operating parameters detected at the steam turbine system.Type: GrantFiled: July 16, 2009Date of Patent: July 8, 2014Assignee: Siemens AktiengesellschaftInventors: Jörg Eppendorfer, Bernd Leidinger, Markus Mantei
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Publication number: 20140157791Abstract: A system for controlling a flow rate of a compressed cooling medium between a compressor section and a turbine section of a gas turbine includes a flow path that is defined between the compressor section and the turbine section of the gas turbine and a thermally actuated variable flow valve disposed within the flow path. The variable flow valve defines an opening that changes in size based on a temperature of the compressed cooling medium flowing therethrough.Type: ApplicationFiled: December 7, 2012Publication date: June 12, 2014Applicant: General Electric CompanyInventors: Rajarshi Saha, Santhosh Donkada, Indrajit Mazumder, Bhasker Pemmi
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Patent number: 8734092Abstract: A flood pump includes a pump housing having a pump housing inlet and a pump housing outlet, an impeller housing disposed in fluid communication with the pump housing between the pump housing inlet and the pump housing outlet, an impeller disposed in the impeller housing, a power unit drivingly engaging the impeller, a diversion conduit disposed in fluid communication with the pump housing between the pump housing inlet and the pump housing outlet and a pump housing outlet valve in the pump housing between the diversion conduit and the pump housing outlet.Type: GrantFiled: March 14, 2011Date of Patent: May 27, 2014Inventor: Rick D. Spargo
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Publication number: 20140140821Abstract: Embodiments for vacuum generation are provided. In one example, a method for an engine including a turbocharger having a compressor driven by a turbine comprises generating vacuum via compressor bypass flow through an ejector, and applying vacuum from the ejector to a wastegate actuator. In this way, vacuum produced via boosted engine operation may be used to actuate the wastegate valve.Type: ApplicationFiled: November 16, 2012Publication date: May 22, 2014Applicant: FORD GLOBAL TECHNOLOGIES, LLCInventor: Ross Dykstra Pursifull
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Publication number: 20140127002Abstract: A multi-stage turbocharger arrangement (TLA), having a high-pressure stage, the high-pressure turbine of which has an associated first bypass valve; and having a low-pressure stage which is arranged downstream as viewed in the flow direction of the exhaust gases and which has a low-pressure turbine and a second bypass valve, wherein at least one of the bypass valves is arranged in an associated, cooled housing module.Type: ApplicationFiled: February 28, 2012Publication date: May 8, 2014Applicant: BORGWARNER INC.Inventors: Volker Joergl, Timm Kiener, Michael Becker, Thomas Kritzinger, Rainer Kolmar
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Patent number: 8696299Abstract: A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises inner and outer tubular walls extending away from the impeller wheel in an upstream direction and defining between them gas flow passage. A bleed passage between the gas flow passage and the impeller wheel is selectively opened and closed by movement of a sliding sleeve in a helical direction.Type: GrantFiled: May 7, 2010Date of Patent: April 15, 2014Assignee: Cummins Turbo Technologies LimitedInventors: John Michael Bywater, James Alexander McEwen
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Patent number: 8684675Abstract: A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines an annular bypass passage surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve includes a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.Type: GrantFiled: April 4, 2013Date of Patent: April 1, 2014Assignee: Honeywell International Inc.Inventors: Alain Lombard, Michael Ladonnet, Michel Thirion
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Patent number: 8684660Abstract: A pressure and temperature actuation system is provided having a high-temperature low-pressure zone, a low-temperature high-pressure zone, a boundary, a pressure actuated mechanism, and a temperature mechanism. A gas located in the high-temperature low-pressure zone has a greater gas temperature than the gas located in the low-temperature high-pressure zone. The gas located in the low-temperature high-pressure zone has a greater gas pressure than the gas located in the high-temperature low-pressure zone. The boundary separates the high-temperature low-pressure zone from the low-temperature high pressure zone. The pressure actuated mechanism is located within the boundary and is configured for opening at a specified gas pressure in either the high-temperature low-pressure zone or the low-temperature high-pressure zone.Type: GrantFiled: June 20, 2011Date of Patent: April 1, 2014Assignee: General Electric CompanyInventors: Carlos Miguel Miranda, Edward William Cummings
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Patent number: 8678755Abstract: A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines an annular bypass passage surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.Type: GrantFiled: January 15, 2013Date of Patent: March 25, 2014Assignee: Honeywell International Inc.Inventors: Alain Lombard, Michael Ladonnet, Michel Thirion
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Patent number: 8672617Abstract: The invention relates to a hydraulic plant (I) that defines a path (4, 5, 6) for a forced water flow (E), and comprises at least one machine (1) of the turbine, pump or turbine-pump type, a member (8) provided with at least one deformable wall (81) and defining at least one closed volume (V8) with variable dimensions. The plant also includes means (9, 91) for supplying (Fg) the closed volume with a pressurized fluid. The member with a deformable wall (81) is mounted in a hydraulic duct (6) located downstream from a rotary portion (2) of the machine (1). The deformable wall defines, locally and downstream from the rotary portion (2), a modular section (S63) for the flow (E) passage in the hydraulic duct (6). According to the method of the invention, a pressurized fluid is injected (F9) into a closed volume having variable dimensions (V8) and defined by a member (8) provided in a hydraulic duct (6) located downstream from the rotary portion (2), in order to modulate the passage section (S63).Type: GrantFiled: November 14, 2008Date of Patent: March 18, 2014Assignee: Alstom Renewable TechnologiesInventors: Michel Henri Couston, Michel Sabourin
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Publication number: 20140072399Abstract: A system includes a gas turbine engine, which includes a compressor configured to generate compressed air and a turbine. The turbine includes a stationary component and a conduit configured to convey the compressed air from the compressor to the stationary component in a forward direction. The gas turbine engine also includes a flow control device coupled to the conduit. The conduit is configured to convey a gas path air from the stationary component in a reverse direction opposite from the forward direction when the flow control device is in a startup mode. The gas turbine engine also includes a shaft coupled to the compressor and the turbine.Type: ApplicationFiled: September 7, 2012Publication date: March 13, 2014Applicant: General Electric CompanyInventors: Jaime Javier Maldonado, Sandip Dutta
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Patent number: 8662831Abstract: A shell structure for a turbine engine that includes a plurality of diaphragms, wherein each diaphragm comprises: an annularly formed support structure that positions and secures a row of circumferentially spaced stator blades, and wherein the plurality of diaphragms are configured and axially stacked such that each diaphragm abuts the diaphragm that is positioned directly upstream from it and the diaphragm that is positioned directly downstream from it such that a first shell structure is formed; a second shell structure disposed outboard of the first shell structure; and an intermediate chamber defined between an outboard face of the first shell structure and an inboard face of the second shell structure; wherein: a downstream end and an upstream end of the first shell structure define the axial length of the first shell structure; one or more downstream radial ports are defined at the approximate axial position of the downstream end of the first shell structure, each downstream radial port fluidly connectiType: GrantFiled: December 23, 2009Date of Patent: March 4, 2014Assignee: General Electric CompanyInventor: Michael E. Montgomery
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Publication number: 20140056696Abstract: A pump device (1A) includes: an impeller (2) that rotates about an axis of rotation (A); an inlet passage (10a) that extends along the axis of rotation (A) of the impeller (2); a volute chamber (10b) provided around the impeller (2); a high-pressure chamber (4) provided around the inlet passage (10a); a circumferential wall (5) that separates the inlet passage (10a) and the high-pressure chamber (4); and a bypass passage (6) that communicates the volute chamber (10b) and the high-pressure chamber (4). The circumferential wall (5) has a plurality of through holes (51) provided in a circumferential direction. The central axis (B) of each of the through holes (51) is included in a plane substantially perpendicular to the axis of rotation (A). The central axis (B) is inclined with respect to a reference line (L).Type: ApplicationFiled: October 5, 2012Publication date: February 27, 2014Inventors: Bunki Kawano, Kou Komori, Tomoichiro Tamura
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Patent number: 8657568Abstract: An air cycle machine includes a turbine wheel, a turbine inlet nozzle, a valve body, and a poppet member. The turbine wheel is mounted to rotate within the air cycle machine and the turbine inlet nozzle is positioned to direct airflow thereto. The poppet member selectively extends into the turbine inlet nozzle and the valve body controls a pressure on the poppet member to move the poppet member relative to the turbine inlet nozzle to vary the size of the turbine nozzle directing airflow to the turbine wheel.Type: GrantFiled: April 19, 2010Date of Patent: February 25, 2014Assignee: Hamilton Sundstrand CorporationInventors: Christopher McAuliffe, John M. Dehais, Craig M. Beers
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Patent number: 8657567Abstract: A gas turbine engine is provided with a nacelle having a hollow inner space. The inner space is utilized as a plenum for directing air from an inlet to an outlet at the upstream end of the nacelle to allow control of an effective lip width of the nacelle under certain flight conditions.Type: GrantFiled: May 29, 2007Date of Patent: February 25, 2014Assignee: United Technologies CorporationInventors: Thomas G. Cloft, Ashok K. Jain
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Patent number: 8651798Abstract: A kinetic hydropower generation system has a turbine and a generator coupled to the turbine. An underwater intake nozzle assembly is fluidly coupled to the turbine. For one embodiment, an underwater tower nozzle may be fluidly coupled between the turbine and the underwater intake nozzle assembly. The underwater intake nozzle assembly may include a collector and a converging nozzle.Type: GrantFiled: May 15, 2009Date of Patent: February 18, 2014Assignee: Sheer Wind, Inc.Inventor: Daryoush Allaei
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Patent number: 8641363Abstract: A turbocharger having a turbine with a wastegate, and a compressor including a compressor housing, a compressor wheel, and a wastegate actuator. The turbine wheel includes blades defining an inlet. The compressor housing has an inlet wall leading to the inlet, and a shroud wall surrounding the blades. The actuator includes a base that is integral with the inlet wall, and an electric motor that is attached to the base. The shroud wall forms a first port that is in direct fluid communication with the actuator chamber, and the inlet wall forms a second port that is in direct fluid communication with the actuator chamber. Air from the first port to passes through the actuator housing and out the second port. This airflow convectively cools the working components of the actuator, while the connection of the motor to the inlet wall conductively cools the motor.Type: GrantFiled: December 29, 2010Date of Patent: February 4, 2014Assignee: Honeywell International Inc.Inventors: Andrew C. Love, Nicolas Devulder