Method Of Operation Patents (Class 415/1)
  • Publication number: 20140356122
    Abstract: Gas turbine inlet guide vane ice detection and control systems and methods that utilize active infra-red monitoring of inlet guide vanes, detection of ice formation on the guide vanes and elimination of the ice by altering properties of the gas turbine inlet intake airflow, such as by introducing compressed and/or heated air bled from the turbine. Ice has lower detectable emissivity intensity in the infra-red spectrum than ice-free inlet guide vane surfaces. Ice formation is inhibited by direct monitoring of inlet guide vane icing conditions, rather than by indirect empirical assumptions of ice formation based on atmospheric condition monitoring. Direct monitoring mitigates ice formation in real time without reliance on excessive use of gas turbine compressed or heated air bleed, which enhances turbine operational efficiency.
    Type: Application
    Filed: May 29, 2013
    Publication date: December 4, 2014
    Inventors: CLIFFORD HATCHER, JR., Forrest R. Ruhge
  • Publication number: 20140356127
    Abstract: A pump (1) for pumping highly viscous fluids is presented that includes a casing (3), an inlet (7), an outlet (8) and a closed impeller (5) rotatably arranged in the casing between the inlet and the outlet and that has a side room (6) between a shroud (4) of the impeller and the casing (3). In addition, the pump (1) includes a sealing element (7a, 7b, 8a, 8b) between the impeller (5) and the casing (3) each at an inlet side and at an outlet side of the impeller for restricting back flow through the side room (6) and for allowing the fluid contained in the side room to heat up, and an injection port (9) leading into the side room (6) for injecting a fluid into the side room for diminishing disk friction between the shroud (4) of the impeller and the casing (3).
    Type: Application
    Filed: November 28, 2012
    Publication date: December 4, 2014
    Inventor: Johann Guelich
  • Publication number: 20140356123
    Abstract: Embodiments of the present disclosure are directed towards a bearing of a rotor assembly having a first lubricant flow path configured to flow a first lubricant flow to a first bearing surface of the rotor assembly and a second lubricant flow path separate from the first lubricant flow path and configured to flow a second lubricant flow to a second bearing surface of the rotor assembly.
    Type: Application
    Filed: May 30, 2013
    Publication date: December 4, 2014
    Inventors: Thomas Edward Gerber, Jonathan David Clemons
  • Publication number: 20140356125
    Abstract: An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid.
    Type: Application
    Filed: December 12, 2013
    Publication date: December 4, 2014
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventors: Eric S. Donovan, Daniel J. Vonderwell, Craig Heathco
  • Publication number: 20140356128
    Abstract: The present invention relates to a method for providing a fluid flow to a compressor system of a first turbo machine, wherein the compressor system includes at least one compressor housing in which at least one impeller is arranged and through which a compressor flow flows. The method includes feeding a primary fluid flow to a mixing region of the compressor system. The method further includes feeding a secondary fluid flow from an outside region of the compressor housing to the mixing region so that the secondary fluid flow mixes at least in part with the primary fluid flow to form a resulting fluid flow so that between the primary fluid flow and the secondary fluid flow a momentum exchange takes place, and so that the secondary fluid flow is promoted by the primary fluid flow. The method further includes feeding the resulting fluid flow to the compressor flow upstream of the impeller in the direction of the impeller.
    Type: Application
    Filed: December 20, 2012
    Publication date: December 4, 2014
    Applicant: UNIVERSITAT DER BUNDESWEHR MUNCHEN
    Inventors: Stefan Bindl, Marcel Stossel, Reinhard Niehuis, Bastian Muth
  • Publication number: 20140352299
    Abstract: A turbocharger assembly includes a compressor assembly, a turbine wheel, a shaft, a bearing assembly, and a cooling gas conduit. The compressor assembly includes a compressor impeller. The compressor impeller includes an outermost impeller edge and has a maximum cross-sectional dimension at the outermost impeller edge. The shaft interconnects the compressor impeller and the turbine wheel. The bearing assembly surrounds at least a portion of the shaft. The cooling gas conduit is disposed in fluid communication with the compressor assembly and the bearing assembly. At least a portion of the cooling gas conduit is disposed adjacent the outermost impeller edge such that the cooling gas conduit is configured to receive a portion of intake gases flowing along the outermost impeller edge and guide the portion of the intake gases toward the bearing assembly to cool the bearing assembly.
    Type: Application
    Filed: May 31, 2013
    Publication date: December 4, 2014
    Inventors: Louis Begin, Brian J. Edwards, Carnell E. Williams
  • Publication number: 20140356126
    Abstract: It is provided in the present invention a method for synchronously inhibiting subcritical vibrations of magnetic levitation molecular pump rotor, by means of synchronously sampling signals of subcritical vibrations of the rotor generated after the rotor of the magnetic levitation molecular pump touches down so as to obtain the amplitude and the phase of subcritical vibrations of the rotor, based on which outputting a compensation force for inhibiting subcritical vibrations of the rotor. Through using the present method, it is achieved of accurate synchronous for signals of subcritical vibrations and fast inhibition for subcritical vibrations of the rotor.
    Type: Application
    Filed: November 22, 2012
    Publication date: December 4, 2014
    Applicants: KYKY Technology Co., Ltd., Tsinghua University
    Inventors: Kai Zhang, Han Wu, Qizhi Li, Xiaozhang Zhang, Meng Zou
  • Publication number: 20140356129
    Abstract: A fluidics module rotatable about a rotational center includes first and second chambers and a compression chamber. First and second fluid channels are provided between the first and second chambers and the compression chamber, respectively. The flow resistance of the second fluid channel is smaller, for a flow of liquid from the compression chamber to the second chamber, than a flow resistance of the first fluid channel for a flow of liquid from the compression chamber to the first chamber. Upon rotation at a high rotational frequency, liquid is initially introduced from the first chamber into the compression chamber via the first fluid channel, so that a compressible medium is compressed within the compression chamber. Subsequently, the rotational frequency is reduced, so that the compressible medium within the compression chamber will expand and so that, thereby, liquid is driven into the second chamber via the second fluid channel.
    Type: Application
    Filed: August 14, 2014
    Publication date: December 4, 2014
    Inventors: Nils PAUST, Steffen ZEHNLE, Felix VON STETTEN
  • Publication number: 20140356124
    Abstract: A compressor for pressurizing a flow of air within an aircraft including an inlet providing the flow of air to the compressor. An outlet provides the flow of air, after pressurization by the compressor, to a chamber of the aircraft. A diffuser assembly is disposed between the inlet and the outlet. The diffuser assembly includes one or more vanes at least partially impeding the flow of air through the diffuser assembly. A backing plate is included having a surface adjacent to the one or more vanes. The surface includes a relief feature that enables air to bypass the one or more vanes. The relief feature has an axial depth of about 0.25% to 2.5% of a width of a flow path through the diffuser assembly or of about 0.5% to 5% of a thickness of a flange of the backing plate. A method of operating a compressor is also included.
    Type: Application
    Filed: June 4, 2013
    Publication date: December 4, 2014
    Inventors: David A. Dorman, Harold W. Hipsky, Peter A. Wierzbowski, Eric Chrabascz, Brian Cabello
  • Patent number: 8899921
    Abstract: A wind turbine blade is configured such that the lift force from the blade airfoil is always normal, or nearly normal, to the shaft torque. This condition maximizes energy conversion. This objective may be achieved by a) having the airfoil chord always aligned to the actual wind direction (subject only to small angle of attack variations), and b) slowing the turbine rotation rate so that no blade twist is needed. As a result, blade tip speed due to shaft rotation is less than the wind speed, and preferably much less. This low tip speed eliminates any hazard to birds. The lift force from the blade airfoil directly drives the torque on the shaft, so the control problem simplifies to adjusting the blade angle of attack to keep the lift constant across varying wind speeds.
    Type: Grant
    Filed: October 6, 2011
    Date of Patent: December 2, 2014
    Inventor: Earl McCune
  • Patent number: 8899908
    Abstract: The disclosure refers to a method and apparatus for checking the bearing alignment of a rotor of a gas turbine or steam turbine having a rotor with a radial offset and a radial offset surface and in a bearing shell, which supports the rotor, with a radial, at least in sections, end surface, wherein the radial offset surface and the radial end surface face the free end of the rotor. The radial offset is arranged in the bearing shell and offset towards the free end of the rotor. The degree of offset in the axial direction with regard to the rotor is measured at least two different circumferential positions around the rotor periphery in order to determine the alignment of the rotor. Differences in the degree of offset at different circumferential positions are used as measurement for the bearing alignment.
    Type: Grant
    Filed: June 17, 2011
    Date of Patent: December 2, 2014
    Assignee: Alstom Technology Ltd.
    Inventors: Eduard Br├╝hwiler, Marc Rauch
  • Patent number: 8899920
    Abstract: A wind turbine yaw system is provided that includes a yaw gear, at least two pinion gears, and at least two drive units, each of which is associated to one of the pinion gears for driving that pinion gear. The yaw system also includes a control system with a controller for generating a drive unit control signal for each drive unit for controlling the respective drive unit according to a reference signal having a desired operational parameter value for the respective drive unit, so as to realize the desired operational parameter value in the respective drive unit. The control system includes a feedback loop for each drive unit feeding a drive unit feedback signal including at least the actual value of one operational parameter of the respective drive unit back to the controller. The controller generates the drive unit control signals based on the reference signal and the feedback signals.
    Type: Grant
    Filed: June 22, 2011
    Date of Patent: December 2, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventor: Kurt Andersen
  • Patent number: 8899909
    Abstract: The present application provides a steam turbine system. The steam turbine system may include a high pressure section, an intermediate pressure section, a shaft packing location positioned between the high pressure section and the intermediate pressure section, a source of steam, and a cooling system. The cooling system delivers a cooling steam extraction from the source of steam to the shaft packing location so as to cool the high pressure section and the intermediate pressure section.
    Type: Grant
    Filed: June 27, 2011
    Date of Patent: December 2, 2014
    Assignee: General Electric Company
    Inventors: Vishwas Kumar Pandey, Debabrata Mukhopadhyay, Manikandan Srinivasan, Santhosh Donkada
  • Patent number: 8899910
    Abstract: A clutch assembly includes a shaft, vent plug and oil guide sleeve. The shaft includes an internal cavity, first passages for allowing oil to lubricate clutch components, and second passages for allowing excess oil to drain from the internal cavity. The vent plug has a radial passage in communication with the internal cavity for venting the cavity with an external source of air. The oil guide sleeve directs oil into the internal cavity. A method for lubricating and venting an air turbine starter includes delivering lubricating oil to an internal cavity of a clutch via an oil guide sleeve. The oil guide sleeve prevents oil from exiting the cavity through excess oil drainage passages before it lubricates the clutch components. The method also includes draining excess oil from the cavity through excess oil drainage passages so that excess oil does not substantially impede air flow through a vent plug passage.
    Type: Grant
    Filed: August 26, 2011
    Date of Patent: December 2, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Jeffrey M. Makulec, Marc Westen
  • Patent number: 8899911
    Abstract: The invention provides a heat-dissipating system and a control method thereof. The heat-dissipating system has a plurality of fans and is configured for adjusting rotation-speeds of the fans. The control method includes following steps: obtaining a plurality of rotation-speed values of the fans; computing out a rotation-speed reference value according to the rotation-speed values; when the rotation-speed reference value is greater than a first threshold value, decreasing the rotation-speeds of the fans through a corresponding fan control signal; when the rotation-speed reference value is less than a second threshold value, increasing the rotation-speeds of the fans through the corresponding fan control signal.
    Type: Grant
    Filed: July 16, 2012
    Date of Patent: December 2, 2014
    Assignee: Coretronic Corporation
    Inventors: Chih-Cheng Chou, Wen-Hsien Su, Tsung-Ching Lin, Chao-Nan Chien
  • Publication number: 20140348630
    Abstract: A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region. A thickness of the leading edge region is based on a thickness of a wake in the airflow produced by the first airflow structure when the airflow passes between the first airflow structure and the second airflow structure.
    Type: Application
    Filed: March 11, 2014
    Publication date: November 27, 2014
    Applicant: United Technologies Corporation
    Inventors: Constantine Baltas, Oliver V. Atassi
  • Publication number: 20140348629
    Abstract: 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: Application
    Filed: May 21, 2013
    Publication date: November 27, 2014
    Applicant: TurboGen, LLC
    Inventor: John Kuczaj
  • Publication number: 20140348631
    Abstract: A turbomachine stage, particularly a turbine stage or a compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, conical in particular, housing in which is arranged a moving vane arrangement with multiple moving vanes which have an exterior shroud band with at least one radial sealing flange. The sealing flange has a recess arrangement with at least one radial recess in which, centrally in particular, a radial projection is arranged. There is arranged on the housing a sensor arrangement with at least one capacitive sensor for detecting a radial clearance to a peripheral surface of the sealing flange.
    Type: Application
    Filed: May 21, 2014
    Publication date: November 27, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Florian GERBL, Juergen Gruendmayer, Martin Stadlbauer, Ernst Trassl
  • Publication number: 20140348633
    Abstract: A turbine stage having a gas channel in which at least one rotor assembly is disposed, is disclosed. A cavity communicates with the gas channel and is delimited by a front side of a rotor element and by a rotor element-mounted seal. A blow-out arrangement with at least one gas passage for blowing out a sealing gas flow into the cavity is provided, where the gas passage for blowing out the sealing gas flow is configured with a swirl in the circumferential direction and has an outlet opening that is offset radially outwardly from the rotor element-mounted seal.
    Type: Application
    Filed: May 23, 2014
    Publication date: November 27, 2014
    Applicant: MTU Aero Engines AG
    Inventor: Alexander BOECK
  • Publication number: 20140345372
    Abstract: A system (e.g., a chromatography system) includes a rotor, a microfluidic device, a rotor driver, a clamping mechanism, and control electronics. The rotor defines a plurality of first fluid-conveying features. The micro fluidic device defines one or more channels and a plurality of second fluid-conveying features, in fluid communication with the one or more channels. The rotor driver is coupled to the rotor and is configured to rotate the rotor, relative to the microfluidic device, between a first position and a second position such that, in each of the positions, at least one of the first fluid-conveying features cooperates with at least one of the one or more channels to provide for fluid communication therebetween. The clamping mechanism is operable to provide a sealing force to establish a fluid-tight seal between the rotor and the microfluidic device.
    Type: Application
    Filed: January 30, 2013
    Publication date: November 27, 2014
    Applicant: WATERS TECHNOLOGIES CORPORATION
    Inventors: Geoff C. Gerhardt, Keith Fadgen, Joseph D. Michienzi, Bernard Bunner
  • Publication number: 20140348632
    Abstract: A turbomachine stage, in particular a turbine stage or compressor stage of a gas turbine, is disclosed. The turbomachine stage has a, in particular conical, housing in which a rotor blade arrangement having a plurality of rotor blades is disposed which have an outer shroud having at least one radial sealing flange. The sealing flange has a recess arrangement having at least one radial recess in which a radial projection is disposed, in particular centrally. A sensor arrangement having at least one capacitive sensor for detecting a radial distance from a circumferential surface of the sealing flange is disposed on the housing.
    Type: Application
    Filed: May 21, 2014
    Publication date: November 27, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Michael Zielinski, Andreas Zeisberger, Rene Schneider
  • Patent number: 8893499
    Abstract: An expander-generator is disclosed having an expansion device and a generator disposed within a hermetically-sealed housing. The expansion device may be overhung and supported on or otherwise rotate a hollow expansion rotor having a thrust balance seal being arranged at least partially within a chamber defined in the expansion rotor. Partially-expanded working fluid is extracted from an intermediate expansion stage and a first portion of the extracted working fluid is used cool the generator and accompanying radial bearings. A second portion of the extracted working fluid may be introduced into the chamber defined within the expander rotor via a conduit defined in the thrust balance seal chamber. The second portion of extracted working fluid minimizes unequal axial thrust loads on the expander rotor due to the overhung arrangement.
    Type: Grant
    Filed: October 9, 2012
    Date of Patent: November 25, 2014
    Assignee: Dresser-Rand Company
    Inventor: William C. Maier
  • Publication number: 20140341704
    Abstract: A heat exchange arrangement for a gas turbine engine. The arrangement includes a first conduit for an engine component cooling fluid and a second conduit for a second fluid. The arrangement further includes a heat exchange portion in which fluids flowing through the first and second conduits are in a heat exchange relationship. A valve is provided, which is configured to moderate the mass flow rate of one of the fluids through the heat exchange portion. The arrangement includes divert valve in the first conduit which diverts flow to the second conduit as the flow in the second conduit is moderated to reduce thermal shock in the heat exchange portion.
    Type: Application
    Filed: March 28, 2014
    Publication date: November 20, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventor: Paul FLETCHER
  • Publication number: 20140341706
    Abstract: A supersonic compressor provided may include an axial inlet and a centrifugal impeller fluidly coupled to the axial inlet. The centrifugal impeller may have a periphery and may be configured to impart energy to process fluid received via the axial inlet and discharge the process fluid from the periphery in at least a partially radial direction. The supersonic compressor may further include a static diffuser circumferentially disposed about the periphery of the centrifugal impeller and configured to receive the process fluid from the centrifugal impeller and convert the energy imparted. The static diffuser may include a plurality of diffuser vanes defining diffuser passageways therebetween. A supersonic ramp may be formed at an end of the at least one diffuser vane proximate the periphery of the centrifugal impeller. The supersonic ramp may be configured to generate a shock wave from the process fluid.
    Type: Application
    Filed: May 8, 2014
    Publication date: November 20, 2014
    Applicant: DRESSER-RAND COMPANY
    Inventors: Pascal Lardy, James M. Sorokes, Mark J. Kuzdzal
  • Publication number: 20140339827
    Abstract: A method and a control device for damping an oscillatory movement of the top of a tower of a wind turbine are provided. The described method includes (a) rotating a rotor being rotatably attached to a nacelle of the wind turbine with a rotational speed, and (b) yawing the nacelle of the wind turbine around an axis being aligned with the longitudinal axis of the tower with a yawing speed. Thereby, a yawing movement being associated with yawing the nacelle is coordinated with the oscillatory movement in such a manner that a gyroscopic torque resulting (i) from rotating the rotor and (ii) from yawing the rotor damps the oscillatory movement of the top of the tower. A wind turbine comprising such a control device and a computer program for controlling this method are also provided.
    Type: Application
    Filed: March 15, 2014
    Publication date: November 20, 2014
    Applicant: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Thomas Esbensen, Gustav Hoegh, Kristian Holm-Joergensen
  • Publication number: 20140341703
    Abstract: A system and method for operating an engine turbocharger is described. In one example, the turbocharger includes an electrically actuated waste gate. A controller adjusts a position of the electrically actuated waste gate.
    Type: Application
    Filed: May 16, 2013
    Publication date: November 20, 2014
    Applicant: FORD GLOBAL TECHNOLOGIES, LLC
    Inventors: Vladimir V. Kokotovic, Amey Y. Karnik, Yan Wang
  • Publication number: 20140341708
    Abstract: A gas turbine engine is disclosed having an air injection system useful to supply a relatively pressurized air to a flow path of a compressor. The air injection system includes a port cover operable to open and close a port through which the air can flow to the compressor from a relatively pressurized source. The port cover extends circumferentially around the gas turbine engine and can include a portion that is anchored and an opposite portion coupled to an actuator. Movement of the actuator causes the port cover to open and close the port. Biasing members can be used to urge the port cover into one of an open and closed position against the movement of the actuator.
    Type: Application
    Filed: June 27, 2014
    Publication date: November 20, 2014
    Inventors: Douglas David Dierksmeier, Daniel Kent Vetters
  • Publication number: 20140341702
    Abstract: A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.
    Type: Application
    Filed: March 11, 2013
    Publication date: November 20, 2014
    Applicant: General Electric Company
    Inventor: General Electric Company
  • Publication number: 20140341705
    Abstract: An adjustment assembly for pump casing of a pump, the pump casing including a main part and a side part having a main axis and a side wall section extending laterally with respect to the main axis. The adjustment assembly is operable to cause relative displacement between the side part and the main part of the pump casing. The adjustment assembly includes a drive device and an actuator which can be activated externally of the pump, the drive device being operable to cause the relative displacement of the side part in response to activation of said actuator, the relative displacement capable of being a combination of axial and rotational movement.
    Type: Application
    Filed: April 17, 2014
    Publication date: November 20, 2014
    Applicant: Weir Minerals Australia, Ltd.
    Inventors: Kevin Edward Burgess, Michael Christopher Foreman
  • Publication number: 20140341707
    Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard hot gas flow path facing side and an outboard side; a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion; a first cooling circuit within the plate for cooling a first portion of the plate; a second cooling circuit within the plate for cooling a second portion of the plate; wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another. Also described is a method of cooling a seal segment in a gas turbine engine.
    Type: Application
    Filed: May 12, 2014
    Publication date: November 20, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventors: Simon Lloyd JONES, Mark John SIMMS
  • Patent number: 8888437
    Abstract: A dual flow steam turbine includes coolant passageways which extract coolant steam from the main steam flow paths at locations downstream from the inlet. The coolant passageways conduct the coolant steam through portions of the dual flow steam turbine which are subjected to a high temperature flow. In some cases, the passageways conduct the coolant steam through first stage nozzle boxes and an inlet assembly of the dual flow steam turbine. In some cases, the inlet assembly of the steam turbine includes an annular diaphragm, and a coolant passageway passes through the annular diaphragm to help cool the annular diaphragm.
    Type: Grant
    Filed: October 19, 2011
    Date of Patent: November 18, 2014
    Assignee: General Electric Company
    Inventors: Vishwas Kumar Pandey, Rohit Pruthi, Santhosh Donkada
  • Patent number: 8888436
    Abstract: The present application provides a section cooling system for a steam turbine to limit a leakage flow therethrough. The section cooling system may include a first pressure flow extraction from a first section to a shaft packing location between the first section and a second section and a rotor aperture extending towards the first section. The first pressure flow extraction diverts the leakage flow from the first section into the rotor aperture so as to limit the leakage flow to the second section.
    Type: Grant
    Filed: June 23, 2011
    Date of Patent: November 18, 2014
    Assignee: General Electric Company
    Inventors: Santhosh Donkada, Howard Brilliant, Vishwas Kumar Pandey, Debabrata Mukhopadhyay
  • Publication number: 20140334911
    Abstract: A method for operating a multistage compressor is provided. The method includes monitoring the pump limit, wherein at least a first measurement parameter measured during operation is compared to a reference parameter. The reference parameter is characteristic of reaching the surge limit or a specific distance of the operating point from the surge limit. A multistage compressor is also provided. In order to enlarge the operating range without risking safety, it is proposed that each stage to be monitored individually for the onset of the surge.
    Type: Application
    Filed: July 22, 2014
    Publication date: November 13, 2014
    Inventor: Georg Winkes
  • Patent number: 8882438
    Abstract: A method and system for power generation including a turboexpander with at least two expansion stages, the turboexpander being connected to a power generation unit, is provided. The system includes a controller configured to control (i) an angle of a first inlet guide vane provided at an inlet of a first expansion stage of the turboexpander for maintaining an inlet pressure of the first expansion stage in a predetermined range, and (ii) an angle of a second inlet guide vane provided at an inlet of a second expansion stage of the turboexpander. The controller is configured to determine a highest power from determined powers of the power generation unit and a corresponding angle of the second inlet guide vane and to adjust the angle of the second inlet guide vane independent of the angle of the first inlet guide vane to achieve the highest power.
    Type: Grant
    Filed: May 23, 2011
    Date of Patent: November 11, 2014
    Assignee: Nuovo Pignone S.p.A.
    Inventors: Antonio Asti, Alberto Scotti Del Greco, Paolo Del Turco, Alessio Miliani
  • Patent number: 8882439
    Abstract: Embodiments relate to a guiding apparatus, a wind turbine system, and methods related thereto. In an embodiment, a guiding apparatus for guiding a flow of a fluid for use with a rotor, the rotor comprising an annular radial vane assembly surrounding a central space which is enclosed save via the vane assembly and being arranged to rotate about a vertical axis, includes a screening for guiding the fluid to circulate substantially about the vertical axis within the central space in the same direction as the rotor during use, wherein the screening comprises an inner guide array concentrically surrounded by the vane assembly.
    Type: Grant
    Filed: July 19, 2013
    Date of Patent: November 11, 2014
    Inventor: Guy Andrew Vaz
  • Publication number: 20140328665
    Abstract: Methods and systems are provided for adjusting a wastegate in response to condensate forming conditions in a charge air cooler (CAC). In one example, a wastegate may be opened in response to an induction pressure greater than a threshold pressure when the induction pressure is greater than required to produce a manifold pressure required for a torque demand. Further, a compressor recirculation valve may be opened to further reduce the induction pressure during certain driving conditions.
    Type: Application
    Filed: May 2, 2013
    Publication date: November 6, 2014
    Applicant: Ford Global Technologies, LLC
    Inventors: Chris Paul Glugla, Shuya Shark Yamada
  • Publication number: 20140328666
    Abstract: A bezentropic bladeless turbine has a bladeless rotor, a bladeless stator, and a CD nozzle that feeds a rectified molecular, supersonic flow of gas and/or steam into the rotor. Spiral channels are provided in the rotor, which serve to maintain and sustain the rectified molecular flow of the working fluid through the rotor. An energy booster device is assembled at the exit of the CD nozzle, to increase the efficiency of the CD nozzle. The rotor is attached to an output shaft, to convert the kinetic energy of the working fluid to mechanical work. Various fluids, such as steam, Freon, wind, may be used as the working fluid.
    Type: Application
    Filed: October 31, 2013
    Publication date: November 6, 2014
    Inventor: Diana Michaels Christopher
  • Publication number: 20140328667
    Abstract: An improved variable geometry diffuser (VGD) mechanism for use with a centrifugal compressor. This VGD mechanism extends substantially completely into the diffuser gap so that the VGD mechanism may be used more fully to control other operational functions. The VGD mechanism may be used to minimize compressor backspin and associated transient loads during compressor shut down by preventing a reverse flow of refrigerant gas through the diffuser gap during compressor shutdown, which is prevented because the diffuser gap is substantially blocked by the full extension of the diffuser ring. During start-up, transient surge and stall also can be effectively eliminated as gas flow through the diffuser gap can be impeded as load and impeller speed increase, thereby alleviating the problems caused by startup loads at low speeds. The VGD mechanism can be used for capacity control as well so as to achieve more effective turndown at low loads.
    Type: Application
    Filed: November 4, 2013
    Publication date: November 6, 2014
    Inventors: Steven T. Sommer, Jeb W. Schreiber, Justin P. Kauffman, Kurt F. Nenstiel (Deceased)
  • Publication number: 20140328664
    Abstract: Removing water from a subterranean formation entails pumping hydraulic oil from a surface-located hydraulic oil pump through a hydraulic oil line to a downhole water pump piston to drive it in a first direction to pump water through a downhole water line to a water chamber of a hydraulic accumulator at the surface. A piston separates the water chamber and an oil chamber and moves to compress the hydraulic oil in the oil chamber of the hydraulic accumulator. The hydraulic oil pump may then pump hydraulic oil into the oil chamber causing the piston to move toward the water chamber, thereby moving water in the downhole water line and resetting the piston in the downhole water pump. A water valve in the downhole water line at the surface may open and release water when the piston in the downhole water pump reaches a predetermined or reset position.
    Type: Application
    Filed: May 2, 2013
    Publication date: November 6, 2014
    Applicant: CONOCOPHILLIPS COMPANY
    Inventor: David Dewitt Hearn
  • Patent number: 8876458
    Abstract: An example blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially from the support member toward the blade outer air seal. The support tab is configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the support member.
    Type: Grant
    Filed: January 25, 2011
    Date of Patent: November 4, 2014
    Assignee: United Technologies Corporation
    Inventors: Anne-Marie B. Thibodeau, Bruce E. Chick, Thurman Carlo Dabbs, James N. Knapp, Dmitriy A. Romanov, Russell E. Keene, Jeffrey Vincent Anastas
  • Patent number: 8876460
    Abstract: An apparatus for measuring turbine rotor-to-stator clearances and a method for assembling a turbomachine based on the measured clearances are disclosed. In an embodiment, at least one clearance sensor is inserted into a stator of a turbomachine. Using the sensor, tops-on clearance between a rotor blade tip and an inner surface of a stator is measured while an upper stator shell, a rotor, a lower stator shell are assembled together; and a tops-off clearance is measured while the lower stator shell and a rotor are assembled together. A tops-on/tops-off shift, i.e., a difference between the tops-on clearance and the tops-off clearance, is determined. The turbine can be assembled by adjusting a relative position of the rotor and stator to account for the tops-on/tops-off shift.
    Type: Grant
    Filed: August 11, 2011
    Date of Patent: November 4, 2014
    Assignee: General Electric Company
    Inventor: Fred Thomas Willett, Jr.
  • Publication number: 20140321970
    Abstract: A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.
    Type: Application
    Filed: July 8, 2014
    Publication date: October 30, 2014
    Inventors: Steven H. Zysman, Wesley K. Lord, Robert M. Miller, Oliver V. Atassi
  • Publication number: 20140321969
    Abstract: A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall (1) and an inner wall (2) defining the flow channel; and a hollow space (4) being formed between the inner wall and the outer housing wall. The hollow space is separable into at least two regions (5, 6); a movable wire element (slide ring seal) (10, 10?), which is adapted to rest against the contact faces (8, 9), being configured in the hollow space for purposes of the separation.
    Type: Application
    Filed: April 9, 2014
    Publication date: October 30, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Norbert Schinko, Janine Sangl
  • Publication number: 20140321971
    Abstract: An internally-cooled centrifugal compressor having a shaped casing and a diaphragm disposed within the shaped casing having a gas side and a coolant side so that heat from a gas flowing through the gas side is extracted via the coolant side. An impeller disposed within the diaphragm has a stage inlet on one side and a stage outlet for delivering a pressurized gas to a downstream connection. The coolant side of the diaphragm includes at least one passageway for directing a coolant in a substantially counter-flow direction from the flow of gas through the gas side.
    Type: Application
    Filed: July 8, 2014
    Publication date: October 30, 2014
    Applicant: DRESSER-RAND COMPANY
    Inventors: James Jeffrey Moore, Andrew Hampton Lerche, Brian Scott Moreland
  • Publication number: 20140321967
    Abstract: The present application provides a power augmentation system for use with a gas turbine engine. The power augmentation system may include a compressor discharge manifold, an inlet bleed heat system in communication with the compressor discharge manifold via an inlet bleed heat line, and an auxiliary compressor in communication with the compressor discharge manifold via the inlet bleed heat line.
    Type: Application
    Filed: April 30, 2013
    Publication date: October 30, 2014
    Applicant: General Electric Company
    Inventors: Jianmin Zhang, Tailai Hu, Bradly Aaron Kippel
  • Publication number: 20140321964
    Abstract: A nozzle and shroud for use in an air cycle machine has a plate and a shroud curving in a first axial direction about a center axis of the shroud relative to the plate. A plurality of vanes extends in a second axial direction away from the plate. The plurality of vanes extends for a height away from the plate and a width defined as the closest distance between two adjacent vanes, with a ratio of the height to the width being between 0.1091 and 0.1401. An air cycle machine and a method of repair are also disclosed.
    Type: Application
    Filed: April 24, 2013
    Publication date: October 30, 2014
    Applicant: Hamilton Sundstrand Corporation
    Inventors: Craig M. Beers, Brent J. Merritt
  • Publication number: 20140321961
    Abstract: A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage.
    Type: Application
    Filed: May 31, 2012
    Publication date: October 30, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jeffrey S. Beattie, Scott D. Lewis, Mark F. Zelesky, Ricardo Trindade, Bret M. Teller, Jeffrey Michael Jacques, Brandon M. Rapp
  • Publication number: 20140321962
    Abstract: A nozzle for use in an air cycle machine has a plate. A plurality of vanes extend away from the plate. The plurality of vanes extend for a height away from the plate. A width is defined as the closest distance between two adjacent vanes. A ratio of the height to the width is between 3.253 and 3.800. An air cycle machine and a method of repair are also disclosed.
    Type: Application
    Filed: April 24, 2013
    Publication date: October 30, 2014
    Applicant: Hamilton Sundstrand Corporation
    Inventors: Craig M. Beers, Christopher McAuliffe
  • Publication number: 20140321965
    Abstract: A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.
    Type: Application
    Filed: April 24, 2013
    Publication date: October 30, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: HONEYWELL INTERNATIONAL INC.
  • Publication number: 20140321973
    Abstract: The present invention provides a hydroelectric turbine system comprising a base mounted turbine for location on the seabed or the like, in order to generate electricity from the tidal flow of water through the turbine, the system incorporating a load bank, for example in the form of an array of resistive windings, to which the turbine can be selectively electrically connected in order to dissipate the electrical power as heat into the passing water.
    Type: Application
    Filed: December 19, 2012
    Publication date: October 30, 2014
    Applicant: OPENHYDRO IP LIMITED
    Inventors: James Ives, Paul Dunne, Simon Cawthorne