Bleed Patents (Class 60/795)
  • Patent number: 10267326
    Abstract: An example variable vane scheduling method includes adjusting variable vanes from a position based on a first schedule to a position based on a different, second schedule in response to a control feature. An example method of controlling flow through a compressor of a turbomachine includes moving variable vanes to positions that allow more flow into the compressor in response to bleed air being communicated away from the compressor.
    Type: Grant
    Filed: November 6, 2012
    Date of Patent: April 23, 2019
    Assignee: United Technologies Corporation
    Inventors: Matthew D. Teicholz, Paul H. Spiesman, Kerri A. Wojcik, John R. Gendron, Glenn D. Bartkowski, Sean D J Blake, William G. Tempelman
  • Patent number: 9170024
    Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion chamber, and a plurality of fuel injectors are circumferentially arranged around the flow sleeve to provide fluid communication through the flow sleeve to the combustion chamber. A distribution manifold circumferentially surrounds the plurality of fuel injectors, and a fluid passage through the distribution manifold provides fluid communication through the distribution manifold to the plurality of fuel injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid from a compressor through a combustion chamber and diverting a portion of the working fluid through a distribution manifold that circumferentially surrounds a plurality of fuel injectors circumferentially arranged around the combustion chamber.
    Type: Grant
    Filed: January 6, 2012
    Date of Patent: October 27, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Lucas John Stoia, Patrick Benedict Melton
  • Patent number: 9038398
    Abstract: A gas turbine engine includes a heat exchanger, a bearing compartment, and a nozzle assembly in fluid communication with the bearing compartment. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The bearing compartment is in fluid communication with the heat exchanger. A first passageway communicates the conditioned airflow from the heat exchanger to the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment to the nozzle assembly.
    Type: Grant
    Filed: February 27, 2012
    Date of Patent: May 26, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Ioannis Alvanos
  • Patent number: 9027353
    Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure.
    Type: Grant
    Filed: March 19, 2014
    Date of Patent: May 12, 2015
    Assignee: United Technologies Corporation
    Inventors: Jorn A. Glahn, Clifton J. Crawley, Jr., Philip S. Stripinis, William K. Ackermann
  • Patent number: 9027354
    Abstract: A system includes a gas turbine, an inlet bleed circuit, and a controller. The gas turbine includes a compressor and a turbine. The compressor is configured to produce pressurized air and bleed air. The turbine is configured to produce a first output. The inlet bleed circuit includes a turbo-expander configured to produce a second output from a non-zero first portion of the bleed air. The inlet bleed circuit is also configured to direct a part of the bleed air to an inlet of the compressor. The controller is configured to adjust the gas turbine and the inlet bleed circuit to control the second output of the turbo-expander.
    Type: Grant
    Filed: July 30, 2012
    Date of Patent: May 12, 2015
    Assignee: General Elecric Company
    Inventor: Tomas Antonio Velez
  • Patent number: 9003766
    Abstract: There is disclosed a gas cooler 20 for providing high-pressure sealing gas to a bearing chamber. The cooler comprises a turbine 22; a turbine inlet 24 arranged to receive gas to drive the turbine and a turbine outlet 26 arranged to deliver gas output from the turbine; a compressor 28 arranged to be driven by the turbine 22; a compressor inlet 30 arranged to receive gas to be compressed by the compressor and a compressor outlet 32 arranged to deliver gas output from the compressor 28; and a cooler outlet 36 in fluid communication with the turbine outlet 26 and the compressor outlet 32 so as to deliver high-pressure sealing gas comprising gas merged from the turbine outlet 26 and the compressor outlet 32.
    Type: Grant
    Filed: April 4, 2012
    Date of Patent: April 14, 2015
    Assignee: ROLLS-ROYCE plc
    Inventors: Paul W. Ferra, Yi Wang
  • Patent number: 8991191
    Abstract: A thermally actuated venting system includes a thermally actuated vent for opening a vent outlet in a gas turbine engine associated compartment with a passive thermal actuator located in the compartment based on a temperature of the compartment. Outlet may be located at or near a top of a core engine compartment, a fan compartment, or a pylon compartment. Actuator may be operably connected to a hinged door of vent for opening outlet. Actuator may be actuated by a phase change material disposed in a chamber and having a liquid state below a predetermined actuation temperature and a gaseous state above the predetermined actuation temperature. Actuator may include a thermal fuse for closing door during a fire. Thermal fuse may include at least a portion of piston rod or a cylinder wall of actuator being made of a fuse material having a melting point substantially above the predetermined actuation temperature.
    Type: Grant
    Filed: November 24, 2009
    Date of Patent: March 31, 2015
    Assignee: General Electric Company
    Inventors: Carlos Enrique Diaz, Daniel Jean-Louis Laborie, Stephen Dennis Geary
  • Patent number: 8984894
    Abstract: The invention relates to a method for operation of a combined-cycle power plant with cogeneration, in which method combustion air is inducted in at least one gas turbine, is compressed and is supplied to at least one combustion chamber for combustion of a fuel, and the resultant exhaust gas is expanded in at least one turbine, producing work, and in which method the exhaust gas emerging from the at least one turbine is passed through a heat recovery steam generator in order to generate steam, which generator is part of a water-steam circuit with at least one steam turbine, a condenser, a feedwater tank and a feedwater pump, wherein heat is provided by extracting steam from the at least one steam turbine.
    Type: Grant
    Filed: April 16, 2013
    Date of Patent: March 24, 2015
    Assignee: ALSTOM Technology Ltd
    Inventors: Francois Droux, Dario Ugo Breschi, Karl Reyser, Stefan Rofka, Johannes Wick
  • Patent number: 8973372
    Abstract: A shell air recirculation system for use in a gas turbine engine includes one or more outlet ports located at a bottom wall section of an engine casing wall and one or more inlet ports located at a top wall section of the engine casing wall. The system further includes a piping system that provides fluid communication between the outlet port(s) and the inlet port(s), a blower for extracting air from a combustor shell through the outlet port(s) and for conveying the extracted air to the inlet port(s), and a valve system for selectively allowing and preventing air from passing through the piping system. The system operates during less than full load operation of the engine to circulate air within the combustor shell but is not operational during full load operation of the engine.
    Type: Grant
    Filed: September 5, 2012
    Date of Patent: March 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ching-Pang Lee, Evan C. Landrum, Jiping Zhang
  • Patent number: 8959927
    Abstract: A pneumatically actuated valve includes a valve body, a pneumatic actuator, and a pitot tube. The valve body includes a valve disc positioned in a valve housing that defines a flow passage with a flow passage diameter. The pneumatic actuator rotates the valve disc in the valve housing. The pitot tube is connected to the pneumatic actuator and has a tip extending into the flow passage. The tip is spaced apart from the valve housing by at least 1/20 of the flow passage diameter. The tip is substantially free of downstream obstructions for a distance equal to at least ½ of the flow passage diameter when the valve is in an open position.
    Type: Grant
    Filed: January 31, 2011
    Date of Patent: February 24, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Josh Kamp, Kevin Arthur Roberg
  • Patent number: 8938973
    Abstract: An aircraft air system includes a gas turbine engine, a bleed air duct directing compressed air bled from a compressor to an inner compartment within the aircraft, and an air contamination detector located downstream of the gas turbine engine compressor. The air contamination detector includes a visual indicator which detects the presence of a fluid contaminant within the bleed air.
    Type: Grant
    Filed: February 11, 2010
    Date of Patent: January 27, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Kevin Allan Dooley, Kiritkumar Patel
  • Patent number: 8935926
    Abstract: An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.
    Type: Grant
    Filed: October 28, 2010
    Date of Patent: January 20, 2015
    Assignee: United Technologies Corporation
    Inventors: Joel H. Wagner, Shankar S. Magge, Keith A. Santeler
  • Patent number: 8931284
    Abstract: A flow discharge device, such as a compressor bleed outlet discharging into a bypass duct of a gas turbine engine, comprises an outlet panel 46 which is perforated by openings 48, 50 disposed in an array which tapers in the downstream direction with respect to the flow B in the bypass duct. The configuration of the array of openings 48, 50 creates a plume 60 of tapering form, which enables the bypass flow B to come together downstream of the plume 60 with minimal wake generation, to provide a shield of cooler air so as to avoid contact between the hot gas plume 60 and a wall of 27 of the bypass duct 22. The resulting aerofoil-shaped cross section of the plume 60 also reduces any blocking effect in the bypass duct 22, with consequent performance benefits for the engine fan.
    Type: Grant
    Filed: February 12, 2010
    Date of Patent: January 13, 2015
    Assignee: Rolls-Royce PLC
    Inventors: Zahid M Hussain, Jonathan G Bird
  • Patent number: 8925330
    Abstract: The present invention relates to a flow discharge device (30) for discharging a flow of gas (F) from a first gaseous fluid (A) into a second gaseous fluid (B) which is of a lower pressure than the first gaseous fluid. The discharge device comprises a valve (34) disposed between the first and second gaseous fluids and arranged to regulate the discharge flow (F) and a swirler means (50) disposed between the valve (34) and the second gaseous fluid. The swirler means (50) comprises a plurality of radially extending circumferentially spaced vanes (61, 63, 65). In use the swirler means (50) swirls the discharge flow (F). This acts to reduce the energy, and therefore the pressure of the discharge flow. This results in quieter operation.
    Type: Grant
    Filed: December 14, 2010
    Date of Patent: January 6, 2015
    Assignee: Rolls-Royce PLC
    Inventors: Kevin M. Britchford, Nicolas L. Balkota
  • Patent number: 8904805
    Abstract: An environmental control system includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with a gas turbine engine. A lower pressure tap is associated with a lower pressure location, which is at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into the turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section of the turbocompressor and the turbine section intermix and pass downstream to be delivered to an aircraft use.
    Type: Grant
    Filed: January 9, 2012
    Date of Patent: December 9, 2014
    Assignee: United Technologies Corporation
    Inventors: Harold W. Hipsky, Gabriel L. Suciu, Christopher M. Dye
  • Publication number: 20140305130
    Abstract: A system and method for controlling bleed air flow into an air cycle machine that includes a bleed air inlet and a conditioned air outlet is provided. The system and method include discharging bleed air from an operating gas turbine engine, sensing exhaust gas temperature (EGT) of the gas turbine engine, sensing conditioned air temperature at the conditioned air outlet, and controlling bleed air flow into the air cycle machine based on the sensed EGT and on the sensed conditioned air temperature.
    Type: Application
    Filed: April 10, 2013
    Publication date: October 16, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: HONEYWELL INTERNATIONAL INC.
  • Patent number: 8833053
    Abstract: A cooling system is provided for an aero gas turbine engine. The system has a duct which diverts a portion of a bypass air stream of the engine. A heat exchanger located in the duct receives cooling air for cooling components of the engine. The cooling air is cooled in the heat exchanger by the diverted bypass air stream. After cooling the cooling air, the spent diverted air stream is routed to a tail cone located at the exit of the engine and ejected through a nozzle at the tail cone.
    Type: Grant
    Filed: February 12, 2010
    Date of Patent: September 16, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Adam P Chir, Andrew M Rolt
  • Patent number: 8820091
    Abstract: A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.
    Type: Grant
    Filed: November 7, 2012
    Date of Patent: September 2, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Kok-Mun Tham, Ching-Pang Lee, Vincent P. Laurello, Abdullatif M. Chehab, David A. Kemp, John A. Fussner, Yan Yin, Bijay K. Sultanian, Weidong Cai
  • Patent number: 8813472
    Abstract: A system includes a controller configured to control a semi-closed power cycle system. The controller is configured to receive at least one of a first signal indicative of an oxygen concentration within a first gas flow through a primary compressor, a second signal indicative of power output by the semi-closed power cycle system, a third signal indicative of a temperature of a second gas flow through a turbine, and a fourth signal indicative of a mass flow balance within the semi-closed power cycle system. The controller is also configured to adjust at least one of the first gas flow through the primary compressor, a fuel flow into a combustor, a fraction of the first gas flow extracted from the primary compressor, and an air flow through a feed compressor based on the at least one of the first signal, the second signal, the third signal, and the fourth signal.
    Type: Grant
    Filed: October 21, 2010
    Date of Patent: August 26, 2014
    Assignee: General Electric Company
    Inventors: James Anthony West, Alan Meier Truesdale
  • Patent number: 8752393
    Abstract: One embodiment according to the present invention is a unique system for gas turbine engine control. Other embodiments include unique apparatuses, systems, devices, and methods relating to gas turbine engines. Further embodiments, forms, objects, features, advantages, aspects, and benefits of the present invention shall become apparent from the following description and drawings.
    Type: Grant
    Filed: December 22, 2009
    Date of Patent: June 17, 2014
    Assignee: Rolls-Royce Corporation
    Inventor: Ray F. Bowman
  • Patent number: 8661832
    Abstract: The present invention relates to control of engine variable of a gas turbine engine to regulate the surge margins of at least two compressors. A controller (20) receives data measured from engine sensors (22, 23) and uses said data to determine an indication of surge margin for each of at least two compressors (6, 7) of the gas turbine engine. The controller (20) uses the indications of surge margin for each of the compressors to determine a control strategy that balances the requirements of each compressor. In one embodiment a surge margin operating map divided into different control domains (40, 43, 43) is used. The indication of surge margin determined for each compressor is plotted to determine which control domains the current operating point on the surge margin operating map falls within.
    Type: Grant
    Filed: July 27, 2010
    Date of Patent: March 4, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Ian A. Griffin, Arthur L. Rowe
  • Patent number: 8590308
    Abstract: Problems can arise with regard to noise created by bleed valve arrangements in gas turbine engines. It is known to utilize pressure differential inducing elements such as pepper pots and perforated surfaces in order to attenuate noise from bleed valves. However, these arrangements tend to have a portion which expands such that the exit aperture into a bypass duct wall can significantly affect mechanical strength and operational performance. By providing internally created pepper pots or other pressure differential inducing elements within a path of an arrangement and a constriction to an exit noise attenuation is still achieved but with less detrimental effect with regard to bypass duct wall strength and aerodynamic losses altering operational performance.
    Type: Grant
    Filed: June 5, 2009
    Date of Patent: November 26, 2013
    Assignee: Rolls-Royce PLC
    Inventor: Stuart J. Kirby
  • Patent number: 8572984
    Abstract: A gas turbine engine comprising a nacelle and a breather duct. The breather duct provides communication between a component of the engine within the nacelle and the exterior of the nacelle and opens at an exhaust port on the external surface of the nacelle. There is a clean air outlet slot located downstream of the exhaust port and arranged to expel, in use, a sheet flow of clean air to form an aerodynamic barrier between the external surface of the nacelle and a flow of breather air expelled from the exhaust port.
    Type: Grant
    Filed: April 27, 2010
    Date of Patent: November 5, 2013
    Assignee: Rolls-Royce PLC
    Inventors: Christopher T J Sheaf, Zahid M Hussain
  • Patent number: 8572985
    Abstract: A gas turbine engine pneumatic system for controlling an air bleed valve includes a variable orifice device for controllably discharging air from the pneumatic system in order to reduce a maximum air pressure applied to the air bleed valve, to a predetermined level. A filter device is provided to filter the air discharged from the variable orifice.
    Type: Grant
    Filed: June 26, 2009
    Date of Patent: November 5, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: David Waddleton
  • Patent number: 8516826
    Abstract: The invention relates to a bleed air supply system and a safety device for closing a valve in at least one of the several bleed air supply lines depending on an alarm signal that indicates an opening in at least one of the several bleed air supply lines. To stop the supply of bleed air irrespective of the type of the bleed air source, the safety device comprises a filter device for generating the alarm signal depending on the ground connection signal and on an opening signal from an opening signal device that indicates any opening of the bleed air supply line that is connected to the high-pressure ground connection.
    Type: Grant
    Filed: October 17, 2006
    Date of Patent: August 27, 2013
    Assignee: Airbus Operations
    Inventors: Norbert Rostek, Jürgen Rehbock
  • Patent number: 8511056
    Abstract: Breather air, containing oil mist, is discharged from a nacelle 4 of a gas turbine engine through an exhaust port 26 at a surface 22 of the nacelle 4. Energized air, at relatively high velocity is discharged from a clean air outlet 28, and forms a barrier between the breather air and the external surface 22, so preventing contamination of the surface 22 by oil deposited from the breather air.
    Type: Grant
    Filed: April 27, 2010
    Date of Patent: August 20, 2013
    Assignee: Rolls-Royce PLC
    Inventors: Brian A Handley, Andrew J Mullender, Zahid M Hussain
  • Patent number: 8495883
    Abstract: A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.
    Type: Grant
    Filed: February 4, 2010
    Date of Patent: July 30, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: Adam M. Foust, Raymond S. Nordlund, Nitin Chhabra, David A. Little
  • Patent number: 8490409
    Abstract: A fluid-conveying device including an inner tubular member with a circumferential end portion, a non-elastomeric ring received in a depression of the end portion, and an outer tubular member. The ring has a peripheral surface with a rounded contour defined along a longitudinal direction configured to remain out of the depression to engage the outer tubular member and facilitate sealing thereof.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: July 23, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Tania Pucovsky, Paul Aitchison, Brian Healey
  • Publication number: 20130167551
    Abstract: A turbine includes a compressor to intake a fluid and to compress the fluid, a combustion chamber to heat the fluid from the compressor, a turbine section to rotate a shaft with the heated fluid from the combustion chamber, and a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section.
    Type: Application
    Filed: January 4, 2012
    Publication date: July 4, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Moorthi Subramaniyan, Umesh Garg, Joshy John, Lakshmanan Valliappan
  • Patent number: 8474266
    Abstract: A gas turbine system comprising, a diffuser operative to diffuse an airstream output from a compressor, a fuel nozzle operative to receive fuel and emit the fuel in a combustor, and at least one bleed duct operative to direct bleed air from down stream of the combustor to the fuel nozzle.
    Type: Grant
    Filed: July 24, 2009
    Date of Patent: July 2, 2013
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Geoffrey David Myers
  • Patent number: 8474270
    Abstract: A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.
    Type: Grant
    Filed: February 15, 2012
    Date of Patent: July 2, 2013
    Assignee: General Electric Company
    Inventors: Carl Gerard Schott, Kevin W. Kinzie, John Joseph Lynch, David W. Ball, Gunnar Leif Siden, Kenneth Neil Whaling
  • Patent number: 8459040
    Abstract: In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.
    Type: Grant
    Filed: July 9, 2012
    Date of Patent: June 11, 2013
    Assignee: United Technologies Corporation
    Inventors: Jorn A. Glahn, Peter M. Munsell, Steven B. Johnson
  • Patent number: 8402771
    Abstract: A combustor (14) is placed next to a turbine (16), on the side opposite a compressor (12). A heat insulation device (20) for reducing the transmission of heat from the high-temperature side to the low-temperature side is provided between the combustor/turbine and the compressor. A connection shaft (18) has an axial hole (18a) open on the inlet side of the compressor and axially extending to near a turbine impeller, and also has a radial hole (18b) open near the turbine impeller to the outside of the connection shaft and radially extending to be in communication with the axial hole.
    Type: Grant
    Filed: June 19, 2012
    Date of Patent: March 26, 2013
    Assignee: IHI Corporation
    Inventor: Kosuke Isomura
  • Patent number: 8381532
    Abstract: The present subject matter provides a system for modifying static pressure recoveries and emissions formation within a gas turbine. The system includes a bled diffuser positioned downstream from a compressor section of the gas turbine and a bleed duct extending from the bled diffuser. The bleed duct may be configured to direct bleed air from the pressurized airflow exiting the compressor section to a secondary combustion system located downstream from the main combustion system in a combustor. The bleed air flowing into the secondary combustion system may be mixed with fuel to form an air/fuel mixture.
    Type: Grant
    Filed: January 27, 2010
    Date of Patent: February 26, 2013
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Michael John Hughes
  • Patent number: 8240153
    Abstract: A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine including: extracting compressed air from a low pressure and a high pressure stage of the compressor; adding in an ejector the compressed air from the low pressure stage to the air from the high pressure stage and discharging the combined air as turbine cooling air; bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage; in response to turning on the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air, and adjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point.
    Type: Grant
    Filed: May 14, 2008
    Date of Patent: August 14, 2012
    Assignee: General Electric Company
    Inventors: Priscilla Childers, Mark Disch, Curtis Newton, III, David Wesley Ball, Jr., Kenneth Neil Whaling, Alan Meier Truesdale
  • Patent number: 8136361
    Abstract: A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.
    Type: Grant
    Filed: May 4, 2006
    Date of Patent: March 20, 2012
    Assignee: General Electric Company
    Inventors: Carl Gerard Schott, Kevin W. Kinzie, John Joseph Lynch, David W. Ball, Gunnar Leif Siden, Kenneth Neil Whaling
  • Patent number: 8083466
    Abstract: A turbomachine system includes a compressor having a compressor intake and a compressor extraction outlet, and an inlet system fluidly connected to the compressor intake and the compressor extraction outlet. The inlet system includes a plenum having a first end portion that extends to a second end portion through an intermediate portion. The inlet system also includes a heating system having a plurality of conduits extending horizontally through the intermediate portion of the plenum and arranged in a vertical relationship. Heated air from the compressor extraction outlet passes through the plurality of conduits and raises a temperature of ambient air passing through the plenum and into the compressor intake.
    Type: Grant
    Filed: March 13, 2009
    Date of Patent: December 27, 2011
    Assignee: General Electric Company
    Inventors: Hua Zhang, David Wesley Ball, Jr., Valery Ivanovich Ponyavin, Douglas Scott Byrd
  • Patent number: 8069672
    Abstract: An embodiment of the present invention may provide a variable speed booster, which receives air from a compressor of a gas turbine through an intercooler, to supply air at a relatively constant pressure to an air processing unit. An embodiment of the present invention may provide a speed adjustable booster turbine to energize a variable speed booster; which provides air at a relatively constant pressure to an air processing unit.
    Type: Grant
    Filed: December 22, 2008
    Date of Patent: December 6, 2011
    Assignee: General Electric Company
    Inventor: Ping Yu
  • Patent number: 8033118
    Abstract: A simplified air bleed balancing control system for a pair of aircraft gas turbine engines reduces the number of pressure transducers and differential pressure transducers. Advantages include lower weight, less expensive system, better total system MTBF (mean time before failure), acceptable differential pressure transducer drift identification and compensation by the digital controller, and fewer maintenance tasks.
    Type: Grant
    Filed: January 31, 2008
    Date of Patent: October 11, 2011
    Assignee: EMBRAER—Empresa Brasileira de Aeronautica S.A.
    Inventors: Oswaldo Barthel Monteiro, Vinicius Jorge Tin, Bernardo Campos da Silva Franco, Ricardo Jose Barbosa
  • Patent number: 8024935
    Abstract: A bleed air duct that preferably includes an inlet section configured to include a flush scoop and a louver. The louver is located and configured such that in the desired operating flow range of the duct, the fluid entering the flush scoop is disturbed and as a result creates a low pressure region downstream of the louver. The low pressure region substantially eliminates the generation of any pressure pulses and acoustic resonance also known as Helmholtz resonance.
    Type: Grant
    Filed: November 21, 2008
    Date of Patent: September 27, 2011
    Assignee: Honeywell International Inc.
    Inventors: Robert Hoover, Morris Anderson, Robert Romano, Jeff Mendoza, Dan Judd, Don Weir
  • Patent number: 8015824
    Abstract: A method and system for regulating a cooling fluid within a turbomachine in real time. The system may an external flow conditioning system for adjusting at least one property of the cooling fluid, wherein the external flow conditioning system comprises an inlet portion and an outlet portion. The system may also include at least one heat exchanger; at least one control valve; at least one bypass orifice; at least one stop valve; and a control system.
    Type: Grant
    Filed: May 1, 2007
    Date of Patent: September 13, 2011
    Assignee: General Electric Company
    Inventors: Sivaraman Vedhagiri, Ravi Meenaksh, Jesse E. Trout, Jun Yang
  • Patent number: 8015826
    Abstract: Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.
    Type: Grant
    Filed: April 5, 2007
    Date of Patent: September 13, 2011
    Assignee: Siemens Energy, Inc.
    Inventors: Gerald A. Myers, David A. Little
  • Patent number: 7997084
    Abstract: A gasifying furnace gasifies solid fuel or liquid fuel. A gas turbine drives a turbine to generate power by using combustion gas generated by burning mixed gas of compressed air compressed in a compressor and gas generated in the gasifying furnace in a combustor. A booster boosts compressed air bled from the compressor, and feed the compressed air to the gasifying furnace. A bleed source valve is provided in a bleed line between the compressor and the booster. An abnormality stop controller stops the booster and the gas turbine, based on an opening angle of the bleed source valve or a bleed pressure on an upstream side of the bleed source valve.
    Type: Grant
    Filed: December 14, 2006
    Date of Patent: August 16, 2011
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Satoru Kamohara, Akihiko Saito, Takashi Sonada, Yasuhiro Takashima, Satoko Fujii
  • Patent number: 7980083
    Abstract: An embodiment of the present invention may provide a variable speed booster, which receives air from a compressor of a gas turbine through an intercooler, to supply air at a relatively constant pressure to an air processing unit. An embodiment of the present invention may provide an external power source to energize the variable speed booster; which provides air at a relatively constant pressure to an air processing unit.
    Type: Grant
    Filed: December 22, 2008
    Date of Patent: July 19, 2011
    Assignee: General Electric Company
    Inventor: Ping Yu
  • Publication number: 20110167834
    Abstract: The present invention relates to a flow discharge device (30) for discharging a flow of gas (F) from a first gaseous fluid (A) into a second gaseous fluid (B) which is of a lower pressure than the first gaseous fluid. The discharge device comprises a valve (34) disposed between the first and second gaseous fluids and arranged to regulate the discharge flow (F) and a swirler means (50) disposed between the valve (34) and the second gaseous fluid. The swirler means (50) comprises a plurality of radially extending circumferentially spaced vanes (61, 63, 65). In use the swirler means (50) swirls the discharge flow (F). This acts to reduce the energy, and therefore the pressure of the discharge flow. This results in quieter operation.
    Type: Application
    Filed: December 14, 2010
    Publication date: July 14, 2011
    Applicant: ROLLS-ROYCE PLC
    Inventors: Kevin M. BRITCHFORD, Nicolas L. BALKOTA
  • Patent number: 7975490
    Abstract: A method and system for operating a gas turbine engine power system are provided. The system includes a gas turbine engine system that includes a gas turbine engine coupled to an electrical generator through a first shaft wherein the gas turbine engine includes a compressor, a combustion chamber, and a turbine drivingly coupled to the compressor and the electrical generator. The system also includes a variable speed electrical motor coupled to a load through a second shaft and a variable speed drive selectably couplable to the electrical generator during a starting sequence of the gas turbine engine system in a first configuration of the gas turbine engine power system and to the variable speed motor in a second configuration of the gas turbine engine power system.
    Type: Grant
    Filed: July 28, 2008
    Date of Patent: July 12, 2011
    Assignee: General Electric Company
    Inventor: Ping Yu
  • Patent number: 7972105
    Abstract: A method of starting up a turbine with a compressor have an inlet guide vane, a number of bleed valves, and a number of blades so as to limit the duration in a rotating stall window. The method may include starting rotation of the blades, increasing the speed of the rotation of the blades, closing one or more bleed valves so as to shift the rotating stall window to a higher rotational speed, partially opening the inlet guide vane to a position outside the rotating stall window, and opening the bleed valves while partially closing the inlet guide vane such that the number of blades pass through the rotating stall window.
    Type: Grant
    Filed: May 10, 2007
    Date of Patent: July 5, 2011
    Assignee: General Electric Company
    Inventors: Timothy Dejoris, Michael J. Dutka, Nick Martin, Steven M. Schirle
  • Patent number: 7966831
    Abstract: An apparatus and method for suppressing dynamic instability in a bleed duct of a gas turbine engine includes a fan bypass duct configured to permit a flow of air through the gas turbine engine. The fan bypass duct defines a fan duct surface, and the bleed duct has an inlet in fluid communication with the fan bypass duct and a flow control valve having an opened position and a closed position. A flow diverter is positioned on the fan duct surface proximate the inlet of the bleed duct and diverts the flow of air from the inlet when the flow control valve is closed, while permitting a portion of the flow of air to enter the inlet when the flow control valve is opened.
    Type: Grant
    Filed: August 28, 2007
    Date of Patent: June 28, 2011
    Assignee: General Electric Company
    Inventors: Robert Eugene Kraft, William Andrew Bailey, William Charles Groll
  • Patent number: 7926289
    Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to provide thereto pressurized primary air. A second interstage bleed circuit is joined in flow communication between a second preultimate stage of the compressor and the turbine blades to provide thereto pressurized secondary air at a lower pressure than the primary air.
    Type: Grant
    Filed: November 10, 2006
    Date of Patent: April 19, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
  • Patent number: 7870743
    Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.
    Type: Grant
    Filed: November 10, 2006
    Date of Patent: January 18, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando