Method Of Operation Patents (Class 415/1)
  • 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: 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: 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: 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
  • 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
  • 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
  • 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: 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
  • 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
  • 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
  • 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: 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: 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: 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: 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: 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: 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: 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
  • 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: 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
  • Patent number: 8944748
    Abstract: A fluid pump device, in particular for a medical application, is described having a compressible pump housing and rotor, as well as with a drive shaft which runs in a sleeve and on whose end the fluid pump is arranged. In order to utilize all possibilities of a space-saving arrangement of the respective pump housing of the rotor, which is compressible per se, and as the case a bearing arrangement, the mentioned elements are displaceable to one another in the axial direction compared to an operation position. In particular these elements may be end-configured by way of an axial movement of the drive shaft after the assembly.
    Type: Grant
    Filed: April 29, 2010
    Date of Patent: February 3, 2015
    Assignee: ECP Entwicklungsgesellschaft mbH
    Inventor: Reiner Liebing
  • Patent number: 8944746
    Abstract: A turboexpander-compressor system includes an expander configured to expand an incoming gas, a first set of moveable inlet guide vanes configured to control a pressure of the incoming gas, a compressor configured to compress a gas received from the expander, a shaft configured to support and rotate an expander impeller and a compressor impeller, a second set of moveable inlet guide vanes attached to the compressor and configured to control a pressure of the gas input into the compressor, and a controller configured to acquire information about a rotating speed of the shaft, a pressure and a temperature of the incoming gas, a pressure and a temperature of the gas output from the expander, and to control the second set of moveable inlet guide vanes to maximize a ratio between the rotating speed of the shaft and a drop of an enthalpy across the expander, in off-design conditions.
    Type: Grant
    Filed: June 23, 2011
    Date of Patent: February 3, 2015
    Assignee: Nuovo Pignone S.p.A.
    Inventors: Gabriele Mariotti, Alberto Scotti Del Greco, Stefano Ghiraldo
  • Patent number: 8944749
    Abstract: An oil purge system for a mid turbine frame (MTF) of a gas turbine engine has an oil transfer tube surrounded by a heat shield tube. The oil transfer and heat shield tubes extend at their respective inner ends downwardly from an oil port of a bearing housing and terminate at their respective outer ends projecting outwardly from an annular wall of an outer case of the MTF. Oil leaked from the oil port is purged by pressurized air through an annular cavity formed between the oil transfer and heat shield tubes, and is discharged out of the MTF.
    Type: Grant
    Filed: January 24, 2012
    Date of Patent: February 3, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, John Pietrobon, Zenon Szlanta, Roger Huppe
  • Patent number: 8944747
    Abstract: An actuation system includes a driving ring configured to rotate and having a groove on an internal face facing a central point of the driving ring; at least a linkage attached with a first end to an inside of the groove; and at least a lever arm attached to a second end of the at least a linkage. At least a portion of the at least a linkage stays inside the groove when the driving ring rotates.
    Type: Grant
    Filed: August 26, 2011
    Date of Patent: February 3, 2015
    Assignee: Nuovo Pignone S.p.A.
    Inventors: Franco Sarri, Giuseppe Iurisci, Marco Pelella
  • Publication number: 20150030430
    Abstract: This invention is relates to water turbine power. In particular, the invention relates to a water turbine for generating power in a body of water. There is provided a turbine for operation in a body of water for the generation of power, the turbine comprising: (a) a housing having an inlet for receiving water and an outlet for allowing water to exit; and (b) a power generation unit disposed in the housing and intermediate the inlet and outlet, the power generation unit comprising two propellers for rotation about an axis in response to water flow, wherein the inlet comprises a flared outer end for channelling the water towards the power generation unit, and a truncated cone disposed within the flared outer end of the inlet, the flared portion of the truncated cone protrudes the inlet.
    Type: Application
    Filed: December 12, 2011
    Publication date: January 29, 2015
    Applicant: ENGTEK PTE LTD
    Inventors: Chee Wah Hon, Bert De Wijs
  • Publication number: 20150030429
    Abstract: The invention is a device which uses stored pressure to pump waste and a corresponding method of use. Waste is stored in a first chamber and the chamber is subsequently sealed by a valve and pressurised prior to a second valve opening. The pressurised waste is thereby ejected from the pressure chamber down an outlet pipe.
    Type: Application
    Filed: January 17, 2013
    Publication date: January 29, 2015
    Inventor: Andrew SMITH
  • Publication number: 20150030431
    Abstract: A blade ring for an axial turbomachine is provided, having an outer surface that is arranged on an outer ring and faces radially inwards, and an inner surface that is arranged on an inner ring and faces radially outwards, the surfaces being arranged concentrically and parallel to one another and delimiting an annular flow channel that tapers in the main flow direction of the axial turbomachine, as well as at least one adjustment blade that is arranged so as to be displaceable, in the flow channel, parallel to a surface line of one of the surfaces by a guiding device, and that is able to be fixed, in a predetermined position, to at least one of the rings.
    Type: Application
    Filed: November 7, 2012
    Publication date: January 29, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventor: Armin de Lazzer
  • Publication number: 20150030428
    Abstract: A method for servicing a gas turbine engine to enhance the power output of the gas turbine engine including a control system, inlet guide vanes, and a third stage power turbine nozzle is disclosed. The control system includes an inlet guide vane module. The method includes increasing an operating range of each inlet guide vane to at least 62 degrees. The method also includes modifying a total flow area of the third stage power turbine nozzle by 2% to 12%, the total flow area including flow areas between adjacent airfoils in the third stage power turbine nozzle.
    Type: Application
    Filed: July 25, 2013
    Publication date: January 29, 2015
    Applicant: SOLAR TURBINES INCORPORATED
    Inventors: Daniel William Burnes, Daniel Joseph Reitz, Jamaal A. Sanders
  • Publication number: 20150027708
    Abstract: In one aspect an apparatus for performing a downhole operation is disclosed that in one non-limiting embodiment may include a downhole tool that contains a hydraulically-operated motor and a flow control device that in one position allows a fluid to pass through the motor while preventing the fluid to flow to the motor and in another position allows the fluid to flow to the motor to operate the motor.
    Type: Application
    Filed: July 24, 2013
    Publication date: January 29, 2015
    Applicant: BAKER HUGHES INCORPORATED
    Inventor: Jacob R. Honekamp
  • Patent number: 8939707
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of stepped first ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Each stepped first ridge has a first portion proximal the substrate surface with a pair of first opposed lateral walls terminating in a plateau, and a second portion terminating in a ridge tip. These ridge or rib embodiments have first lower and second upper wear zones. The lower zone, which at and below first portion height, optimizes engine airflow characteristics, while the upper zone, between the plateau and the second portion ridge is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Gm Salam Azad, Zhihong Gao, Neil Hitchman, David G. Sansom, Barrry L. Allmon
  • Patent number: 8939709
    Abstract: A system for operating a turbine includes a rotating component and a non-rotating component separated from the rotating component by a clearance. A first actuator is connected to the non-rotating component, and the first actuator comprises a shape-memory alloy. A method for operating a turbine includes sensing a parameter reflective of a clearance between a non-rotating component and a rotating component and generating a parameter signal reflective of the clearance. The method further includes generating a control signal to at least one actuator based on the parameter signal and moving at least a portion of the non-rotating component relative to the rotating component to change the clearance.
    Type: Grant
    Filed: July 18, 2011
    Date of Patent: January 27, 2015
    Assignee: General Electric Company
    Inventors: Biju Nanukuttan, Rakesh Adoor, Hariharan Sundaram, James Adaickalasamy, Prasad Punna
  • Patent number: 8939705
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of first ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. The abradable component embodiments have a multi-depth grooves formed in the abradable substrate surface between pairs of elongated continuous tip surface first ridges. These ridge and multi-depth groove embodiments have first lower and second upper wear zones. The lower zone, in the deeper grooves, optimizes engine airflow characteristics, while the upper zone, in the shallower grooves, is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Kok-Mun Tham
  • Patent number: 8939706
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of ridges in planform patterns, establishing upper and lower wear zones. The lower wear zone reduces, redirects and/or blocks blade tip downstream airflow leakage, while the upper wear zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone. An elongated first ridge in the lower wear zone terminates in a continuous surface plateau. A plurality of second ridges or nibs, separated by grooves, project from the plateau, forming the upper wear zone. Each of the second ridges has a planform cross section smaller than the plateau planform cross section and a height smaller than the first ridge height. Some embodiments of the second ridges have spacing, planform cross sections, heights and separating groove dimensions selected for shearing when contacted by turbine blade tips.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Gm Salam Azad, Zhihong Gao, Neil Hitchman, David G. Sansom, Barrry L. Allmon, Jonathan E. Shipper, Jr., Cora Schillig, Gary B. Merrill, Dimitrios Zois, Ramesh Subramanian
  • Patent number: 8939704
    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: Grant
    Filed: November 23, 2009
    Date of Patent: January 27, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventor: Georg Winkes
  • Publication number: 20150023777
    Abstract: A compressor is disclosed herein. The compressor may include a shroud cavity. The compressor also may include a flow directing device positioned within the shroud cavity. The flow directing device may be configured to direct a flow within the shroud cavity.
    Type: Application
    Filed: July 19, 2013
    Publication date: January 22, 2015
    Inventor: Gerald Austin Rawcliffe
  • Publication number: 20150023776
    Abstract: A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path. Further included is at least one strut operatively coupling the inner structure to the outer structure. Yet further included is at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut.
    Type: Application
    Filed: July 18, 2013
    Publication date: January 22, 2015
    Inventors: Lubomir A. Ribarov, James S. Elder, Leo J. Veilleux, JR.
  • Patent number: 8936429
    Abstract: A method and system for controlling clearance between the tips of blades of a turbine rotor in a gas turbine airplane engine and a turbine ring of a casing surrounding the blades. A valve is controlled to act on a flow rate and/or a temperature of air directed against the casing. The valve is of the on/off type for switching between an open state and a closed state in a determined reaction time, the valve control module including a corrector for determining a first binary control signal that can take a first value corresponding to an open state and a second value corresponding to a closed state of the valve. The corrector includes a time-delay module for determining a binary control signal, with the duration between two successive changes of state in the control signal being not less than the reaction time of the valve.
    Type: Grant
    Filed: February 1, 2012
    Date of Patent: January 20, 2015
    Assignee: SNECMA
    Inventors: Bruno Robert Gaully, Cedrik Djelassi, Cecile Marot
  • Publication number: 20150016944
    Abstract: A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn.
    Type: Application
    Filed: December 27, 2013
    Publication date: January 15, 2015
    Inventors: Peter L. Vandervaart, Jeffrey F. Rhodes, Okey Kwon, Tab M. Heffernan
  • Publication number: 20150016949
    Abstract: A method of controlling tip clearance of rotor blades from a surrounding casing in a gas turbine engine. The method comprising the steps of performing a first run of the gas turbine engine, shutting down the gas turbine engine and starting the gas turbine engine for a second run. The method further comprises measuring at least one performance parameter during or after the first engine run but before a time selected at which air within the gas turbine engine, soaked to the approximate temperature of one or more surrounding engine components, is substantially displaced as a consequence of the second run. The thermal condition of at least part of the engine in accordance with the measured performance parameters is then recorded. Finally the recorded thermal condition is retrieved and the temperature of the casing is controlled during at least part of the second run in a manner dependent on it.
    Type: Application
    Filed: June 16, 2014
    Publication date: January 15, 2015
    Inventor: Marcus Donegan Wood SMITH
  • Publication number: 20150016954
    Abstract: An 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 inward from the main support member toward the blade outer air seal. The support tab 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 main support member.
    Type: Application
    Filed: October 2, 2014
    Publication date: January 15, 2015
    Inventors: Anne-Marie B. Thibodeau, Bruce E. Chick, Thurman Carlo Dabbs, James N. Knapp, Dmitriy A. Romanov, Russell E. Keene, Jeffrey Vincent Anastas
  • Publication number: 20150016948
    Abstract: A demand-based load balancing function may be provided by one or more drive controllers that takes advantage of the affinity laws to linearize the control of the variable of interest (e.g., flow, pressure, etc.). Each drive controller may be set up by the user simply inputting a few values into the drive controller. Based on the inputs, the drive controllers may interpolate control points using an assumed linear relationship between the variable to be controlled (e.g., pressure) and the current driven to the pump. Feedback data from the system may be used to continually update the drive controllers so as to potentially allow them to better balance power usage to each pump.
    Type: Application
    Filed: August 26, 2011
    Publication date: January 15, 2015
    Applicant: TOSHIBA INTERNATIONAL CORPORATION
    Inventors: Kurt Allen Bihler, David Liu, Mark Douglas Rayner
  • Publication number: 20150016945
    Abstract: An embodiment of a gas turbine engine having a liner and casing is disclosed. The liner is disposed between the casing and a rotatable turbomachinery component. In one form, the rotatable turbomachinery component is a turbofan engine. The liner can be thin relative to a distance between the liner and the casing. Protrusions can be used between the liner and the casing. The protrusions can be a rib and can extend from the casing or the liner. An insert, such as an abradable surface, can be used with the liner. A filler can be used in the space between the liner and the casing.
    Type: Application
    Filed: December 27, 2013
    Publication date: January 15, 2015
    Inventors: Matthew J. Kappes, Matthew A. Scott, Chris J. Winfield, Jared J. Schnieder
  • Publication number: 20150016953
    Abstract: A compressor assembly that has a compressed air tank having a vibration absorption member. The vibration absorption member can exert a pressure on a portion of the compressed air tank. A method of controlling sound emitted from a compressor assembly, by using a vibration absorber which applies a force against the compressed gas tank. Controlling the sound level of the compressed gas tank is accomplished by absorbing vibration from the compressed gas tank by which exerting a pressure on a portion of the compressed gas tank.
    Type: Application
    Filed: September 23, 2014
    Publication date: January 15, 2015
    Inventors: Stephen J. VOS, Scott D. CRAIG
  • Publication number: 20150016947
    Abstract: An apparatus and method for cooling a dual, walled component is disclosed herein. An augmented cooling system according to the present disclosure includes transporting a cooling fluid through one wall of a cooling pathway formed between two opposing spaced apart walls of the dual walled component. The cooling fluid can be deflected away from one wall of the cooling pathway with a first trip strip as the cooling fluid traverses along the cooling pathway. The cooling fluid can be deflected away from the opposing wall of the cooling pathway with a second trip strip as the cooling fluid continues traversing along the cooling pathway. The cooling fluid can then be discharged from the cooling pathway through the opposing wall of the dual walled component.
    Type: Application
    Filed: December 31, 2013
    Publication date: January 15, 2015
    Inventor: Okey Kwon