Method Of Operation Patents (Class 415/1)
  • Patent number: 9004849
    Abstract: A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: April 14, 2015
    Assignee: United Technologies Corporation
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Patent number: 9004850
    Abstract: A compressor for a gas turbine engine with variable inlet guide vanes each defining an airfoil portion twisted such that at each location of the airfoil portion along the pivot axis, an angle is defined between a respective chord extending between the leading and trailing edges and a same reference plane containing the pivot axis and extending radially with respect to the compressor. The angle, which is measured along a direction of rotation of the rotor, varies from a minimum value near the hub side wall to a maximum value near the shroud side wall. A method of reducing vortex whistle in a radial inlet of a compressor is also provided.
    Type: Grant
    Filed: April 27, 2012
    Date of Patent: April 14, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jason Nichols, Hien Duong, Peter Townsend
  • Publication number: 20150098791
    Abstract: A method to design a turbine including: estimating rates of thermal radial expansion for each of a stator and a rotor corresponding to a period of operation of the turbine; estimating a clearance between the rotor and the stator based on the rates of thermal radial expansion, and determining a mass or surface area of the stator or rotor based on the clearance.
    Type: Application
    Filed: October 4, 2013
    Publication date: April 9, 2015
    Applicant: General Electric Company
    Inventors: Henry G. Ballard, JR., Douglas Frank Beadie, John David Memmer
  • Publication number: 20150098794
    Abstract: A turbine-pump system bowl assembly for use with flowing liquid in a liquid conduit has an impeller subassembly that includes multiple axially abutting impeller members.
    Type: Application
    Filed: September 25, 2014
    Publication date: April 9, 2015
    Inventor: Henry A. Baski
  • Publication number: 20150098792
    Abstract: The present invention relates to a method of decelerating a turbine rotor of a turbine engine. At least one electric motor is engaged with the turbine rotor. A braking system, preferably the starting system, is engaged with the at least one electric motor, preferably the generator of the turbine engine, so as to use the at least one electric motor to apply a negative (braking) torque on the turbine rotor. The method includes after flame off, the braking system being used for dissipating kinetic energy available in the turbine engine after flame off by means of the at least one electric motor.
    Type: Application
    Filed: September 25, 2014
    Publication date: April 9, 2015
    Inventors: Klaus DOEBBELING, Christopher Michael Robson, Massimo Giusti
  • Publication number: 20150098793
    Abstract: A turbine-pump system adapted for use with well liquid that is displaceable within a well conduit. The turbine-pump system may include a bowl assembly; and a bowl support device fixedly attachable to the bowl assembly and selectively engageable with the well conduit for holding a portion of the bowl assembly in substantially axially, radially and rotationally fixed relationship with the well conduit.
    Type: Application
    Filed: September 25, 2014
    Publication date: April 9, 2015
    Inventor: Henry A. Baski
  • Patent number: 8998563
    Abstract: An active clearance control system for a gas turbine engine includes a structural member that is configured to be arranged near a blade tip. A plenum includes first and second walls respectively providing first and second cavities. The first wall includes impingement holes. The plenum is arranged over the structural member. A fluid source is fluidly connected to the second cavity to provide an impingement cooling flow from the second cavity through the impingement holes to the first cavity onto the structural member. A method includes the steps of providing a conditioning fluid to an outer cavity of a plenum providing an impingement cooling flow through impingement holes from an inner wall of the plenum to an inner cavity, directing the impingement cooling flow onto a structural member, and conditioning a temperature of the structural member with the impingement cooling flow to control a blade tip clearance.
    Type: Grant
    Filed: June 8, 2012
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventor: Philip Robert Rioux
  • Publication number: 20150093232
    Abstract: A supersonic compressor rotor and method of compressing a fluid is disclosed. The rotor includes a first and a second rotor disk, a first set and a second set of rotor vanes. The first set and second set of rotor vanes are coupled to and disposed between the first and second rotor disks. Further, the first set of rotor vanes are offset from the second set of rotor vanes. The rotor includes a first set of flow channels defined by the first set of rotor vanes disposed between the first and second rotor disks. Similarly, the rotor includes a second set of flow channels defined by the second set of rotor vanes disposed between the first and second rotor disks. Further, the rotor includes a compression ramp disposed on a rotor vane surface opposite to an adjacent rotor vane surface.
    Type: Application
    Filed: October 1, 2013
    Publication date: April 2, 2015
    Applicant: General Electric Company
    Inventors: Rajesh Kumar Venkata Gadamsetty, Chaitanya Venkata Rama Krishna Ongole, Douglas Carl Hofer, Vittorio Michelassi
  • Publication number: 20150093233
    Abstract: A turbocharger assembly can include a housing with a through bore and an axial face disposed in the through bore; a locating plate with a keyed opening attached to the housing; and a journal bearing disposed in the through bore where the journal bearing includes a keyed compressor end and an enlarged outer portion defined between two axial faces by an outer diameter and an axial length where the axial face disposed in the through bore of the housing, the locating plate, and the two axial faces of the journal bearing axially locate the journal bearing in the through bore and where the keyed opening of the locating plate and the keyed compressor end of the journal bearing azimuthally locate the journal bearing in the through bore. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
    Type: Application
    Filed: May 13, 2013
    Publication date: April 2, 2015
    Inventors: Frederic Daguin, Joel Castan, Nicolas Vazeille, Dominique Aramd, Steven Liu, Yong Jun Chen, Shinichi Adachi
  • Patent number: 8992161
    Abstract: Gas turbine engine, broadband damping systems, and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine includes an engine case, a rotor assembly mounted within the engine case for rotation about a rotational axis, and a broadband damping system disposed between the rotor assembly and the engine case. The broadband damping system includes a first set of three parameter axial dampers angularly spaced around the rotational axis, and a second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers. The first and second sets of three parameter axial dampers are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine.
    Type: Grant
    Filed: August 26, 2011
    Date of Patent: March 31, 2015
    Assignee: Honeywell International Inc.
    Inventors: Timothy Hindle, Steven Hadden, Torey Davis
  • Patent number: 8996277
    Abstract: A gas turbine engine control apparatus comprises a controller 34, a memory 36 associated with the controller 34 and inputs 38 for measurement data from an engine. The controller 34 determines the start of a monitoring cycle at 73, receives measurement data at the inputs 38 during the monitoring cycle, manipulates the measurement data to provide an incremental deterioration value representing deterioration occurring within the engine and during the monitoring cycle, and uses the incremental deterioration value at 72 to update a deterioration value 74 stored in the memory 36, and determines the start of a further monitoring cycle.
    Type: Grant
    Filed: January 7, 2013
    Date of Patent: March 31, 2015
    Assignee: Rolls-Royce PLC
    Inventors: Peter Beecroft, Leo Vivian Lewis, Marko Bacic
  • Publication number: 20150086326
    Abstract: A method for optimizing performance of a compressor by adjusting the position of an inlet guide vane and the speed of a drive unit. In one embodiment, the method can compare measured values for operating flow rate and operating pressure for a combination of operating settings for the position and the speed against threshold values for each of these measured values. In this way, the method can identify “how” the compressor is operating and equate such operation to one of a plurality of operation scenarios. In turn, the method can provide an adjustment to one or both of the speed and the position that corresponds with such operating scenario. The method can also vet the selected adjustment to avoid operation of the compressor outside of its safe operating configurations, as defined for example by minimum and maximum values for the position of the inlet guide vane and the speed of the drive unit.
    Type: Application
    Filed: December 1, 2014
    Publication date: March 26, 2015
    Inventors: Dale Eugene Husted, Marc Gavin Lindenmuth
  • Publication number: 20150086325
    Abstract: A pump for a dishwasher is configured as an impeller pump having a central water inflow to a rotating impeller for conveying the water in the radial direction out of the impeller into a pump chamber which surrounds the impeller in a ring-like manner and has a heated pump chamber wall on its outer side. Here, the pump has an outlet in the end region of the pump chamber at an axial spacing from the impeller. Heating elements which have a decreasing power output with regard to the area power output in the axial direction of the pump toward the outlet are arranged on the pump chamber wall. An input of energy into the pump chamber can thus be varied and in the process adapted depending on a turbulent or laminar flow.
    Type: Application
    Filed: February 6, 2013
    Publication date: March 26, 2015
    Applicant: E.G.O. Elektro-Geraetebau GmbH
    Inventors: Holger Koebrich, Tobias Albert, Volker Block
  • Publication number: 20150082767
    Abstract: The present application provides a passive control valve actuator cooling system to provide a flow of cooling air to a control valve actuator used with a gas turbine engine. The passive control valve actuator cooling system may include a turbine enclosure with a negative pressure therein, a radiation shield with a number of radiation shield outlets and the control valve actuator positioned therein, and a cooling air line extending from outside of the turbine enclosure to the radiation shield such that the negative pressure within the turbine enclosure pulls the flow of cooling air into and through the radiation shield so as to cool the control valve actuator.
    Type: Application
    Filed: September 24, 2013
    Publication date: March 26, 2015
    Applicant: General Electric Company
    Inventors: Dean Matthew Erickson, Martin Lopez, Jose Francisco Aguilar
  • Patent number: 8985967
    Abstract: A rotor is provided. The rotor comprises external blades for use in causing rotation of the rotor, and internal blades for use in propelling a fluid through the rotor during rotation of the rotor.
    Type: Grant
    Filed: August 23, 2012
    Date of Patent: March 24, 2015
    Assignee: Vetco Gray Controls Limited
    Inventor: Gopalakrishna Gudivada
  • Patent number: 8985938
    Abstract: An engine has a blade, a casing surrounding the blade, an seal ring, and a passive system for connecting the seal ring to the casing and for accommodating thermal expansion of the seal ring relative to the casing so as to maintain blade tip clearance control. The passive system may include at least one, metallic Z-band extending between the casing and the seal ring.
    Type: Grant
    Filed: December 13, 2011
    Date of Patent: March 24, 2015
    Assignee: United Technologies Corporation
    Inventor: Dale William Petty
  • Patent number: 8989890
    Abstract: In polishing a substrate having a layer of GST disposed over an underlying layer, during polishing, a non-polarized light beam is directed onto the layer of GST. The non-polarized light beam reflects from the first substrate to generate a reflected light beam having an infra-red component. A sequence of measurements of intensity of the infra-red component of the reflected light beam are generated, and, in a processor, a time at which the sequence of measurements exhibits a predefined feature is determined.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: March 24, 2015
    Assignee: Applied Materials, Inc.
    Inventors: Kun Xu, Feng Liu, Dominic J. Benvegnu, Boguslaw A. Swedek, Yuchun Wang, Wen-Chiang Tu, Laksh Karuppiah
  • Publication number: 20150078880
    Abstract: A support assembly and method for supporting an internal assembly in a casing of a turbomachine are provided. The support assembly may include a support member that may be slidably disposed in a recess formed in the internal assembly and configured to engage an inner surface of the casing. A biasing member may be disposed in a pocket extending radially inward from the recess. The biasing member may at least partially extend into the recess and may be configured to apply a biasing force to the support member disposed therein.
    Type: Application
    Filed: August 11, 2014
    Publication date: March 19, 2015
    Applicant: DRESSER-RAND COMPANY
    Inventors: David J. Peer, Andrew J. Ranz, William C. Maier, Joel D. Johnson
  • Publication number: 20150078879
    Abstract: A system and method are provided for controlling the movement of an aircraft engine cowl door between an open position and a closed position. The system includes an electric motor, at least one actuator, and an electrically operated brake. The actuator is coupled to the motor and is operable to move the cowl door between the closed and the open position. The electrically operated brake is coupled to the electric motor and the at least one actuator and is configured, upon being energized, to supply a unidirectional resisting torque load to the electric motor that does not prevent motor rotation.
    Type: Application
    Filed: October 25, 2013
    Publication date: March 19, 2015
    Inventors: Ron Vaughan, Leroy Allen Fizer, James Wawrzynek, Kevin K. Chakkera, Mohamed A. Salam, William Warr, Stephen Birn
  • Publication number: 20150078882
    Abstract: A hydraulic rotary actuator including a stator housing having a through bore to position a rotor assembly. A rotor assembly includes an output shaft and at least a first rotary piston member disposed radially about the output shaft. The rotary piston member includes an vane element. A continuous seal is disposed on peripheral longitudinal faces and lateral end faces of the rotary piston element. The bore through the stator housing includes an interior cavity with surfaces adapted to receive the rotor assembly and contact the continuous seal. With rotation fluid ports blocked, the housing cavity is sealed with the continuous piston seal for hydraulic blocking, preventing actuator displacement by external forces. A method of operation and method of assembly is disclosed.
    Type: Application
    Filed: November 19, 2014
    Publication date: March 19, 2015
    Inventors: Rhett S. Henrickson, Robert P. O'Hara
  • Publication number: 20150078881
    Abstract: An arrangement includes a vacuum pump having a rotor, and a drive unit for driving the rotor and having at least one magnetic interference field-generating component and at least one compensation coil for compensating the magnetic interference field generated by the at least one component.
    Type: Application
    Filed: September 10, 2014
    Publication date: March 19, 2015
    Inventor: Armin Conrad
  • Patent number: 8979486
    Abstract: A spring seal includes a split body portion with a first leg and a second leg that extend away from a plane and a projection portion which extends from the split body portion within the plane.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: March 17, 2015
    Assignee: United Technologies Corporation
    Inventor: Philip Robert Rioux
  • Patent number: 8979471
    Abstract: A bearing assembly, a pump with a bearing assembly and a method of lubricating a pump bearing using a bearing assembly. The bearing assembly includes a bearing carrier and a bearing housing that are rotatably connected to one another to permit axial adjustment of the pump's impeller or other fluid-conveying apparatus, as well as variable rotational positioning of the bearing carrier relative to a pump housing. Numerous lubricant access apertures placed around the periphery of the bearing carrier facilitate lubricant passage from a connection on the bearing housing to the bearings, regardless of the rotational position of the carrier relative to the bearing housing or other pump structure.
    Type: Grant
    Filed: February 22, 2012
    Date of Patent: March 17, 2015
    Assignee: Flowserve Management Company
    Inventors: Philip Richard Riley, Sarath Alayilveetil, John Roger Bower, Anthony George Stafford
  • Patent number: 8979470
    Abstract: A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.
    Type: Grant
    Filed: August 4, 2011
    Date of Patent: March 17, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Sergei Riazantsev, Holger Kiewel, Sven Olmes, Thomas Kramer, Sergey Shchukin
  • Publication number: 20150071760
    Abstract: A compressor and a method for reducing acoustic energy generated in the compressor are provided. The compressor may include a housing defining a fluid pathway and a shunt hole fluidly coupling the fluid pathway with another component of the compressor. The compressor may also include an impeller at least partially disposed in the fluid pathway and coupled with a rotary shaft. The impeller may be configured to rotate with the rotary shaft to direct a process fluid through the fluid pathway of the compressor. A disk may be disposed between the fluid pathway and the shunt hole. The disk may define a plurality of openings fluidly coupling the fluid pathway with the shunt hole and configured to reduce acoustic energy generated in the compressor.
    Type: Application
    Filed: August 12, 2014
    Publication date: March 12, 2015
    Applicant: DRESSER-RAND COMPANY
    Inventors: Zheji Liu, Scott D. Wisler
  • Publication number: 20150071759
    Abstract: 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: Application
    Filed: January 21, 2014
    Publication date: March 12, 2015
    Applicant: Ford Global Technologies, LLC
    Inventors: David Karl Bidner, Julia Helen Buckland
  • Publication number: 20150071758
    Abstract: An electro-pneumatic actuator for a waste gate includes an electric actuator to impart linear motion to an actuator shaft, and a pneumatic chamber defining a passage extending therethrough, the actuator shaft extending through the passage, the pneumatic chamber being sealed with respect to the actuator shaft. A piston is disposed in the pneumatic chamber and arranged for movement in the pneumatic chamber, the piston being affixed to the actuator shaft such that the actuator shaft and the piston move together as a unit. There is a port into the pneumatic chamber for feeding a gas into the pneumatic chamber or exhausting the gas therefrom so as to exert a pressure force on the piston and thereby provide a pneumatic assist to the force exerted on the actuator shaft.
    Type: Application
    Filed: September 12, 2013
    Publication date: March 12, 2015
    Applicant: Honeywell International Inc.
    Inventors: Andrew Love, Julien Mailfert, Nicolas Devulder
  • Patent number: 8967944
    Abstract: A buffer air pump provides pressurized cooling air for cooling components of the gas turbine engine. The buffer air pump is supported on and/or within an accessory gearbox and draws bypass air in through an inlet manifold. An impeller supported within a scroll housing pressurizes the incoming bypass air and directs the pressurized air through passages to a component requiring cooling. The buffer air pump draws in relatively cool air from the bypass flow, pressurizes the air with the impeller and sends the air through conduits and passages within the gas turbine engine to the component that requires cooling such as a bearing assembly.
    Type: Grant
    Filed: August 29, 2011
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jorn A. Glahn, Brian D. Merry, Christopher M. Dye
  • Patent number: 8967945
    Abstract: A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion.
    Type: Grant
    Filed: December 23, 2013
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Craig A. Nordeen, James W. Norris
  • Publication number: 20150056057
    Abstract: A radial inflow turbine may include a wheel, a first set of nozzle vanes surrounding the wheel and a second set of nozzle vanes surrounding the wheel. A first circumferential spacing between two adjacent nozzle vanes of the first set may differ from a second circumferential spacing between another two of the nozzle vanes of the first set.
    Type: Application
    Filed: August 20, 2013
    Publication date: February 26, 2015
    Applicant: HONEYWELL INTERNATIONAL, INC.
    Inventors: Frank Lin, Davis Jensen, Marshall Saville, Phil McAfee, David G. Elpern
  • Publication number: 20150056058
    Abstract: A propeller system for an aircraft includes an assembly for modifying a sound field of the propeller system. The propeller system includes a rotor supported for rotation about a rotor axis. The rotor has a central hub and a plurality of blades each extending outwardly from the hub to a tip. The rotor and blades are operable to propel an aircraft to travel in a direction. The rotor blades define a rotor plane perpendicular to the rotor axis. The blade tips define a circumferential rotational path as the blades are rotated by the rotor. The propeller system includes an acoustic resonator or multiple resonators having openings disposed within a distance to the propeller blade tip that is small compared to the wavelength of the propeller's fundamental blade tone and proximate to the rotor plane. The resonators are excited by tip flow of the blade as it passes the opening.
    Type: Application
    Filed: October 15, 2013
    Publication date: February 26, 2015
    Applicant: KCF TECHNOLOGIES, INC.
    Inventors: Michael D. GRISSOM, Gary H. KOOPMAN
  • Publication number: 20150056060
    Abstract: A vacuum pump system for evacuating at least five volumes comprising a turbomolecular pump and a forevacuum pump arranged to pump an output of the turbomolecular pump arrangement to atmosphere. The turbomolecular pump has at least five pumping stages separated by rotor blades. Not more than three pumping stages have pumping speeds in excess of ? of the highest pumping speed when under vacuum and/or a pumping port cross section in excess of ? of the highest pumping port cross section, and at least two pumping stages have pumping speeds less than ¼ of the highest pumping speed when under vacuum and/or a pumping port cross section of less than ¼ of the biggest pumping port cross section. The ratio of pressures between the pumping stage with the highest pressure and the pumping stage with the lowest pressure is at least 100000:1 when under vacuum.
    Type: Application
    Filed: August 13, 2014
    Publication date: February 26, 2015
    Inventors: Alexander MAKAROV, Wilko BALSCHUN
  • Publication number: 20150056059
    Abstract: A control system controls the output capacity of a compressor to avoid surge conditions in the compressor. The control system determines a capacity control output for the compressor and then modifies the capacity control output in view of any output limiters or overrides as determined by system operating parameters and to maintain a minimum frequency of operation for the compressor.
    Type: Application
    Filed: April 26, 2013
    Publication date: February 26, 2015
    Inventor: Curtis Christian Crane
  • Patent number: 8961100
    Abstract: An exemplary valve device for controlling flow of a turbomachine fluid includes a housing and a flow control assembly within the housing. The housing has a first inlet, a second inlet, and an outlet. Movement of the housing to a first orientation causes the flow control assembly to move to a first position to restrict flow of a turbomachine fluid into the housing through the second inlet. Movement of the housing to a second orientation causes the flow control assembly to move to a second position to restrict flow of the turbomachine fluid into the housing through the first inlet.
    Type: Grant
    Filed: August 29, 2011
    Date of Patent: February 24, 2015
    Assignee: United Technologies Corporation
    Inventors: Enzo DiBenedetto, Francis Parnin, Robert E. Peters
  • Patent number: 8961102
    Abstract: A system and method for sealing a shaft disposed for rotation within a casing, where two axially-spaced seal rings of an oil film seal extend around the shaft and define a clearance therebetween. Oil is pumped into the clearance from an oil reservoir and a portion of the oil is received in an annular port defined in the casing between an outer labyrinth seal and one of the axially-spaced seal rings. The oil mixes with a process gas to for an oil and gas mixture. A blower is in fluid communication with the annular port and circulates the oil and gas mixture to a trap where the oil is separated from the process gas and a separated process gas is returned back to the annular port.
    Type: Grant
    Filed: June 6, 2012
    Date of Patent: February 24, 2015
    Assignee: Dresser-Rand Company
    Inventor: Philippe Auber
  • Patent number: 8961101
    Abstract: A system of operating a wind turbine that is capable of extending electricity production, such as in low and high wind speed environments. In accordance with various embodiments, a wind turbine speed maintenance system has a wind turbine with at least one turbine blade that has a trailing edge with a speed feature. The speed feature is connected to a controller and a pressure vessel, the controller selectively activating the speed feature in response to the turbine blade reaching a predetermined radial velocity.
    Type: Grant
    Filed: November 17, 2011
    Date of Patent: February 24, 2015
    Inventor: Larry Jeffus
  • Patent number: 8961111
    Abstract: According to one aspect of the invention, a turbine airfoil includes a first cavity inside the turbine airfoil configured to receive a fluid and a second cavity inside the turbine airfoil. The turbine airfoil also includes a passage inside the turbine airfoil that provides fluid communication between the first and second cavities, wherein the passage includes a curved portion configured to separate particulates from the fluid as the fluid flows through the passage.
    Type: Grant
    Filed: January 3, 2012
    Date of Patent: February 24, 2015
    Assignee: General Electric Company
    Inventors: Adebukola Oluwaseun Benson, Gary Michael Itzel, Kevin Richard Kirtley
  • Publication number: 20150050120
    Abstract: Methods and systems for fan speed control based on memory margin are disclosed. According to an aspect, a method includes determining an operating margin of a memory interface. The method also includes determining whether the operating margin of the memory interface meets a predetermined condition. Further, the method includes controlling a speed of a computing system cooling fan based on the operating margin in response to determining the operating margin meets the predetermined condition.
    Type: Application
    Filed: August 13, 2013
    Publication date: February 19, 2015
    Applicant: International Business Machines Corporation
    Inventors: Michael DeCesaris, James J. Parsonese, Luke D. Remis, Philip L. Weinstein
  • Publication number: 20150050121
    Abstract: A fan control system for processor is provided. The system has: a fan, configured to cool the processor; a power measurement module, coupled between the processor and a power supply of the processor, configured to measure the power of the processor; and a control module, coupled between the fan and the power measurement module, configured to control a speed of the fan according to the power of the processor, wherein when the power is higher than a predetermined power upper limit, the control module control the fan to increase the rotation speed.
    Type: Application
    Filed: January 9, 2014
    Publication date: February 19, 2015
    Applicant: Wistron Corp.
    Inventor: Te-Lung Wu
  • Publication number: 20150044016
    Abstract: A fuel system incorporating a boost pump unit, a boost pump unit and method of pumping fuel are provided. The fuel system and boost pump unit are preferably self-priming and do not utilize an airframe mounted pump for supplying fuel for an aircraft combustor. The boost pump unit includes a liquid ring pump and an air/fuel separator. The air/fuel separator has an inlet and first and second outlet ports. The inlet is operably fluidly coupled to an outlet of the liquid ring pump. The air/fuel separator has an arcuate flow path. The first outlet port is in fluid communication with a radially outer portion of the arcuate flow path and the second outlet port is in fluid communication with a radially inner portion of the arcuate flow path. A return line connected to the first outlet port is configured to return fuel to the liquid ring pump.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 12, 2015
    Applicant: WOODWARD, INC.
    Inventors: Austin Wade Mueller, Dmitriy Baryshnikov
  • Publication number: 20150044015
    Abstract: A liquid ring pump is provided. The liquid ring pump is designed to reduce the overall envelop of the ring pump. The liquid ring pump includes a housing and an impeller. The housing defines an impeller cavity. The impeller cavity has an inlet port and a discharge port. The impeller is positioned within the impeller cavity for rotation about a central rotational axis. The impeller includes a central hub defining a conical outer surface and a plurality of angularly spaced apart main vanes extending radially outward from the conical outer surface relative to the central rotational axis. The inlet and discharge ports may be located on a same side of the impeller housing.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 12, 2015
    Applicant: Woodward, Inc.
    Inventor: Austin Wade Mueller
  • Publication number: 20150044020
    Abstract: A method for avoiding pump surges in a compressor is provided, wherein a plurality of parameters of the compressor are monitored during operation and a desired value range for the plurality of parameters is predetermined, wherein a reaction that counteracts the pump surge is triggered if a number of parameters from the desired value range are exceeded or fallen below. The method also reliably prevents pumping of the compressor during a comparatively high running performance. For this purpose, the plurality of parameters has a parameter assigned to the rotational noise of the compressor.
    Type: Application
    Filed: December 12, 2012
    Publication date: February 12, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventor: Claus Grewe
  • Publication number: 20150044017
    Abstract: Embodiments of the invention relate generally to turbomachines and, more particularly, to the positioning of airfoils to reduce pressure variations entering a diffuser. One embodiment includes a turbomachine comprising a diffuser, a plurality of airfoil rows, including a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of stationary vanes and rotating blades, a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type, and a third airfoil row of the first type adjacent the second airfoil row, wherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine.
    Type: Application
    Filed: August 9, 2013
    Publication date: February 12, 2015
    Applicant: General Electric Company
    Inventor: Paul Kendall Smith
  • Publication number: 20150044019
    Abstract: A compressor may include a crankshaft, a lower bearing, an oil sump, an oil pump and a pressure equilibrium tube. The crankshaft may include an oil supply passage formed therethrough. The lower bearing may rotatably support a lower part of the crankshaft. The oil sump may be disposed proximate the lower part of the crankshaft. The oil pump may include an inlet, an outlet, an intake chamber and a discharging chamber. The inlet may be positioned below a level of oil in the oil sump and in fluid communication with the intake chamber. The discharging chamber may be in fluid communication with the oil supply passage at the lower part of the crankshaft through the outlet. The pressure equilibrium tube provides fluid communication between a space above the level of oil in the oil sump and the intake chamber.
    Type: Application
    Filed: March 30, 2012
    Publication date: February 12, 2015
    Applicant: EMERSON CLIMATE TECHNOLOGIES, INC.
    Inventors: Jibao Wu, Qingfeng Sun
  • Publication number: 20150044022
    Abstract: Methods, devices and systems capable of performing a hot restart of a compressor driven by a turbine are provided. The turbine has a high speed shaft and a low speed shaft connected to the compressor. A base slow roll speed at which a speed of the low speed shaft is in a slow roll range is maintained at the high speed shaft for a predetermined time. Then, when a vibration amplitude of the compressor is larger than a vibration limit, the maintaining is repeated. Otherwise, a set speed of the high speed shaft is increased, until a current speed of the low speed shaft reaches a minimum operating speed. If, while increasing the set speed, the vibration amplitude becomes larger than the vibration limit, the maintaining is repeated.
    Type: Application
    Filed: October 23, 2014
    Publication date: February 12, 2015
    Inventors: Gianni Bagni, Antonio Baldassarre, Leonardo Baldassarre, Michele Fontana
  • Publication number: 20150044021
    Abstract: A turbine system and a method for operating a work machine are provided herein. The turbine system including: a first, a second, and a third turbine, a central gearbox mechanically coupled on the input side to the three turbines and having a mechanical connection on the output side for connecting a work machine, a first fluid line for conveying a working fluid from the first turbine to the second turbine, a second fluid line for conveying the working fluid from the second turbine to the third turbine, a first connecting unit designed such that a first partial mass flow of the working fluid can be removed from the first fluid line or supplied to the first fluid line, and a second connecting unit designed such that a second partial mass flow of the working fluid can be removed from the second fluid line or supplied to the second fluid line.
    Type: Application
    Filed: March 15, 2013
    Publication date: February 12, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventors: Thomas Müller, Volker Neumann, Marc Overath, Matthias Schleer
  • Publication number: 20150044018
    Abstract: One embodiment of the present disclosure is a unique active seal system. Another embodiment is another unique active seal system. Another embodiment is a unique method for operating a turbomachine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for active seal systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Application
    Filed: December 4, 2013
    Publication date: February 12, 2015
    Inventor: Douglas D. Dierksmeier
  • Publication number: 20150037135
    Abstract: A gas turbine engine (10) comprising a fan (14) and an acoustic absorption intake and/or fan case liner (40). The liner (40) comprises at least four liner sections (42) demarcated by circumferentially spaced inhomogeneities (50). The inhomogeneities (50) cause scattering of a fan tone acoustic field when the gas turbine engine (10) is in use. To be accompanied when published by FIG. 3.
    Type: Application
    Filed: July 17, 2014
    Publication date: February 5, 2015
    Inventor: Andrew John KEMPTON
  • Publication number: 20150037134
    Abstract: The invention relates to mechanical engineering, in particular to air-driven, gas-driven and steam-driven turbines having increased power generation efficiency and reduced weight and dimensions. The invention can be used in electrical power generators, propulsion systems, refrigeration compressors, heat pumps, turbo-jet apparatuses and the like. A jet turbine according to the invention comprises a centrifugal wheel having blades and rotatably mounted on a shaft, for compressing a working medium, which is further directed via centrifugal passages having outlet openings into a toroid collector having a circular opening extending along its inner circumference and being sealingly attached to the centrifugal wheel, so that the outlet openings of the centrifugal passages in the wheel are in fluid connection with the inner chamber of the toroid collector, wherein the collector further has exhaust openings with jet nozzles mounted therein, arranged substantially along the outer circumference of the toroid collector.
    Type: Application
    Filed: February 5, 2014
    Publication date: February 5, 2015
    Inventors: Andrey Valer'evlch SHRAMKO, Sergei Konstantinovich ISAEV, Dmitri Georgievich GITA, Valeriy Igorevich OMAROV
  • Publication number: 20150037133
    Abstract: A system for passively varying an axial position of an inner casing of a gas turbine pursuant to changing pressure in a flowpath during transient engine operation. The system may include: a connection assembly slidably connecting the inner casing to the outer casing for axial movement of the inner casing between a first position and a second position; means for pressurizing the annulus relative to a flowpath pressure; biasing means for axially preloading the inner casing toward the first position; and an inner casing receiving surface configured to receive a pressure in the annulus for axially loading the inner casing in opposition to the axial preload of the biasing means.
    Type: Application
    Filed: July 31, 2013
    Publication date: February 5, 2015
    Applicant: General Electric Company
    Inventors: Matthew Stephen Casavant, David Martin Johnson