Multi-spool Turbocompressor Patents (Class 60/792)
  • Patent number: 10858999
    Abstract: The invention relates to a removable reactivation pack for a turboshaft engine of a helicopter, comprising a gas generator equipped with a drive shaft, said turboshaft engine (6) being capable of operating in at least one standby mode during a stable flight of the helicopter, said removable pack comprising: a removable gearbox comprising a gearbox output shaft; controlled means for rotating said gearbox output shaft, referred to as reactivation means of said turboshaft engine; mechanical means for reversibly coupling said gearbox output shaft to said drive shaft of said gas generator.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: December 8, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick Marconi, Romain Thiriet, Camel Serghine, Caroline Seve, Pierre Darfeuil
  • Patent number: 10830144
    Abstract: A gas turbine engine includes devices, systems, and methods for providing bleed air from the compressor impeller to the turbine for cooling and/or other use. The bleed air may include compressor cooling air that is routed through the diffuser and external to an outer bypass duct and/or internally to a forward wheel cavity of the turbine.
    Type: Grant
    Filed: September 8, 2016
    Date of Patent: November 10, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Tony A. Lambert, Behram V. Kapadia, Ron Hall
  • Patent number: 10794467
    Abstract: A planetary gear mechanism has a rotatable planet carrier, a device for conducting oil, and a housing-fixed oil collecting duct. The oil collecting duct surrounds an area of the planet carrier in the circumferential direction. Oil centrifuged off by the planet carrier is collected in the oil collecting duct. In the installation position of the oil collecting duct, the oil is conducted by a gravitational force in the direction of a lower collection area formed with an outlet through which oil can be discharged. A further outlet, through which oil can be conducted, is provided in front of the collection area with respect to the rotational direction of the planet carrier between an upper area of the oil collecting duct, as it appears in the installation position of the oil collecting duct, and the outlet. Also, an aircraft gas turbine with the planetary gear mechanism.
    Type: Grant
    Filed: January 24, 2019
    Date of Patent: October 6, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Wolfram Kurz-Hardjosoekatmo, Carsten Wolf
  • Patent number: 10648368
    Abstract: A drive assembly for a gas turbine engine according to an exemplary embodiment includes, among other things, an epicyclic gear train having an input and an output, the input coupled to a first turbine, the output coupled to an accessory drive shaft, and at least one engagement feature on a component of the gear train. An actuator is engageable with the at least one engagement feature to cause the accessory drive shaft to rotate. A method of driving a section of a gas turbine engine is also disclosed.
    Type: Grant
    Filed: March 29, 2017
    Date of Patent: May 12, 2020
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Matthew Allen Slayter, Tyler L. Klipp
  • Patent number: 10634064
    Abstract: A turbofan engine includes a first spool including a first turbine; a second spool including a second turbine disposed axially forward of the first turbine, a first tower shaft engaged to the first spool, a second tower shaft engaged to the second spool and an accessory gearbox supporting a plurality of accessory components and a superposition gear system disposed within the accessory gearbox. The superposition gear system includes a plurality of intermediate gears engaged to the sun gear and supported in a carrier and a ring gear circumscribing the intermediate gears. The second tower shaft is engaged to drive the sun gear; a starter selectively coupled to the sun gear through a starter clutch; a first clutch for selectively coupling the first tower shaft to the ring gear; a second clutch for selectively coupling the ring gear to a static structure of the engine.
    Type: Grant
    Filed: October 11, 2018
    Date of Patent: April 28, 2020
    Assignee: United Technologies Corporation
    Inventors: Joseph H. Polly, Nicholas D. Leque
  • Patent number: 10605173
    Abstract: A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.
    Type: Grant
    Filed: June 28, 2019
    Date of Patent: March 31, 2020
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Hung Duong, Jonathan F. Zimmitti, William G. Sheridan, Michael E. McCune, Brian Merry
  • Patent number: 10502232
    Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism operable to move between an open position and a closed position. The inlet-adjustment mechanism includes a plurality of blades disposed about the compressor air inlet and located within an annular space within the air inlet wall. The blades are pivotable about respective pivot points such that the blades extend radially inward from the annular space into the air inlet when the blades are in the closed position so as to form an orifice of reduced diameter relative to a nominal diameter of the inlet. Upstream surfaces of the blades include swirl inducers that are structured and arranged to impart either pre-swirl or counter-swirl to the air passing through the orifice into the compressor wheel.
    Type: Grant
    Filed: March 1, 2018
    Date of Patent: December 10, 2019
    Assignee: Garrett Transportation I Inc.
    Inventors: Hani Mohtar, Stephane Pees, Alain Lombard
  • Patent number: 10480519
    Abstract: A compressor for a gas turbine engine is disclosed. The compressor includes a first compression stage mounted for rotation about a central axis that includes a plurality of first-stage blades. The compressor also includes a second compression stage mounted along the central axis aft of the first compression stage to receive air compressed by the first compression stage. The second compression stage includes a plurality of second-stage blades.
    Type: Grant
    Filed: March 25, 2016
    Date of Patent: November 19, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: William B. Bryan
  • Patent number: 10330016
    Abstract: According to an aspect, a system for a gas turbine engine includes a reduction gear train operable to drive rotation of a starter gear train that interfaces to an accessory gearbox of the gas turbine engine. The reduction gear train includes a starter interface gear that engages the starter gear train, a core-turning clutch operably connected to the starter interface gear, and a plurality of stacked planetary gear systems operably connected to the core-turning clutch and a core-turning input. The system also includes a mounting pad including an interface to couple a core-turning motor to the core-turning input of the reduction gear train.
    Type: Grant
    Filed: July 5, 2016
    Date of Patent: June 25, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Benjamin T. Harder, Matthew Allen Slayter, Brian McMasters, James Vandung Nguyen, Dwayne Leon Wilson, Paul F. Fox, Richard Alan Davis, Richard R. Hergert, Jeffrey Todd Roberts, Jeff A. Brown, Daniel Richard Walker
  • Patent number: 10227928
    Abstract: A gas turbine engine comprises a fan, a compressor, a turbine having first stage blades and second stage blades, the first stage blades rotates in a first direction and the second stage blades rotates in a second direction opposite the first direction. The first stage blades are directly adjacent to one another, a drive in operable input connection with the fan and in operable output connection with the first stage blades and the second stage blades, the first stage blades and the second stage blades driving the fan through the drive.
    Type: Grant
    Filed: January 14, 2014
    Date of Patent: March 12, 2019
    Assignee: General Electric Company
    Inventors: Craig Miller Kuhne, Christopher Charles Glynn, Randy M. Vondrell, Andrew Breeze-Stringfellow, Kurt David Murrow, Darek T. Zatorski, Donald Scott Yeager, Nicholas Rowe Dinsmore, Samuel Jacob Martin, Donald Albert Bradley
  • Patent number: 9482156
    Abstract: An engine may have a recuperator that may be powered by an electrical generator driven by the engine. The recuperator may be disposed within or incorporated into a compressor discharge of the engine, such as in the form of a vane or tube. The engine may be configured to operate in a variety of modes at least some of which may use thermal energy from the recuperator to heat a fluid flow stream of the engine. An energy storage device may be used with an electrical generator to provide power to a load.
    Type: Grant
    Filed: December 27, 2013
    Date of Patent: November 1, 2016
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Carl D. Nordstrom, Rigoberto J. Rodriguez
  • Patent number: 9359956
    Abstract: The method and apparatus for in-flight relighting of a turbofan engine involve in one aspect selectively controlling an accessory drag load on one or more windmilling rotors to permit control of the windmill speed to an optimum value for relight conditions.
    Type: Grant
    Filed: October 1, 2014
    Date of Patent: June 7, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Kevin Allan Dooley
  • Patent number: 9347367
    Abstract: A turbocharger is disclosed for use with an engine system. The turbocharger may have a housing at least partially defining a compressor shroud and a turbine shroud. The turbine shroud may form a first volute and a second volute, each having an inlet configured to receive exhaust from an exhaust manifold of the engine in a tangential direction, and an axial channel disposed downstream of the inlet. The turbocharger may also have a turbine wheel disposed within the turbine shroud and configured to receive exhaust from the axial channels of the first and second volutes, a compressor wheel disposed within the compressor shroud, and a shaft connecting the turbine wheel to the compressor wheel. The turbocharger may further have a nozzle ring in fluid communication with the axial channels of the first and second volutes at a location upstream of the turbine wheel.
    Type: Grant
    Filed: July 10, 2013
    Date of Patent: May 24, 2016
    Assignee: Electro-Motive Diesel, Inc.
    Inventors: Shakeel Nasir, Joshua David Schueler
  • Patent number: 9297304
    Abstract: One embodiment of the present invention is a unique gas turbine engine with a bleed air powered auxiliary engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for bleed air powered auxiliary engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: December 30, 2010
    Date of Patent: March 29, 2016
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Carl David Nordstrom, Ray F. Bowman
  • Patent number: 9080578
    Abstract: A compressor has an impeller and an inlet delivering air to the impeller. A variable diffuser is positioned downstream of the impeller and includes a plurality of pivoting vanes. A drive arrangement pivots the vanes, and includes an electric motor causing a pinion gear to rotate. The pinion gear has gear teeth engaging gear teeth on a rack section. Rotation of the rack section causes the vanes to pivot.
    Type: Grant
    Filed: September 2, 2008
    Date of Patent: July 14, 2015
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Craig M. Beers, John M. Beck
  • Patent number: 9068506
    Abstract: A gas turbine engine recuperator system includes a heat recuperator positioned in a gas turbine exhaust gas duct for recovering heat from turbine exhaust gases to preheat a compressor flow being supplied to the combustor. A continuous bleed flow of the turbine exhaust gases is provided to bypass the heat recuperator. The continuous bleed flow of the turbine exhaust gases is adjustable to reduce turbine exhaust gas pressure loss at a high engine operation level and to provide efficient heat recovery at low and/or medium engine operation levels.
    Type: Grant
    Filed: March 30, 2012
    Date of Patent: June 30, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, Daniel Alecu, David Menheere
  • Patent number: 9062607
    Abstract: A method of operating a gas turbine power plant with a first gas turbine group, including a first turbine assembly, and a second gas turbine group, including a compressor assembly and a second turbine assembly which are mechanically coupled to one another, and useful work is extracted by a device being included in the plant, where a flue gas stream is produced by a combustion device, which is placed in a gas flow stream upstream of the second turbine assembly, where the second turbine assembly and compressor assembly are balanced to each other such that work produced by the second turbine assembly is consumed by the compressor assembly, and where the first turbine assembly is balanced to the device for the extraction of useful work such that work produced by the first turbine assembly is consumed by the device for the extraction of useful work.
    Type: Grant
    Filed: February 24, 2010
    Date of Patent: June 23, 2015
    Assignee: EURO-TURBINE AB
    Inventor: Hans-Erik Hansson
  • Publication number: 20150143794
    Abstract: A three-spool turbofan engine (20) has a variable fan nozzle (35). The fan blades have a peak tip radius RT and an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of RH to RT is less than about 0.40.
    Type: Application
    Filed: September 25, 2014
    Publication date: May 28, 2015
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, William G. Sheridan
  • Patent number: 9038362
    Abstract: A turbofan engine (10) employs a flow control device (41) that changes an effective exit nozzle area (40) associated with a bypass flow path (B) of the turbofan engine. A spool (14) couples a fan (20) to a generator (52). The turbofan emergency power system includes a controller (50) that communicates with the flow control device (41). Upon sensing an emergency condition, the controller manipulates the flow control device to reduce the effective nozzle exit area (40) of the bypass flow path, which chokes the flow through the bypass flow path thereby increasing the rotational speed of the fan. In this manner, the generator is driven at a higher rotational speed than if the flow through the bypass flow path was not choked, which enables a smaller generator to be utilized.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: May 26, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael Winter, Charles E. Lents
  • Publication number: 20150121844
    Abstract: A gas turbine engine includes a fan section and a compressor section. The compressor section includes both a first compressor section and a second compressor section. A turbine section includes at least one turbine and driving the second compressor section and a fan drive turbine driving at least a gear arrangement to drive the fan section. A power ratio is provided by the combination of the first compressor section and the second compressor section, with the power ratio being provided by a first power input to the first compressor section and a second power input to the second compressor section, the power ratio being equal to, or greater than, about 1.0 and less than, or equal to, about 1.4.
    Type: Application
    Filed: February 11, 2014
    Publication date: May 7, 2015
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • Publication number: 20150121893
    Abstract: A turbine engine includes a first fan including a plurality of fan blades rotatable about an axis and a reverse flow core engine section including a core turbine axially forward of a combustor and compressor. The core turbine drives the compressor about the axis and a transmission system. A geared architecture is driven by the transmission system to drive the first fan at a speed less than that of the core turbine. A second fan is disposed axially aft of the first fan and forwarded of the core engine and a second turbine is disposed between the second fan and the core engine for driving the second fan when not coupled to the transmission.
    Type: Application
    Filed: March 12, 2014
    Publication date: May 7, 2015
    Applicant: United Technologies Corporation
    Inventor: Daniel Bernard Kupratis
  • Publication number: 20150113943
    Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in a second direction opposed to the first direction.
    Type: Application
    Filed: January 9, 2015
    Publication date: April 30, 2015
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis
  • Publication number: 20150114002
    Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.
    Type: Application
    Filed: January 9, 2015
    Publication date: April 30, 2015
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis
  • Patent number: 9003808
    Abstract: A gas turbine engine comprises an outer engine case, a combustor, a high pressure spool and a low pressure spool. The combustor is disposed within the outer engine case. The high pressure spool is configured for rotation coaxially with the combustor. The low pressure spool is configured for rotation coaxially with the high pressure spool. The low pressure spool is configured to rotate at speeds faster than that of the high pressure spool during operation of the gas turbine engine. In one embodiment, the low pressure spool includes a gear system configured to rotate a low pressure compressor faster than a low pressure turbine. In another embodiment, the high pressure spool rotates outward of the combustor within the outer engine case. In another embodiment, the high pressure spool includes a drum having radially inward projecting blades and vanes and radially outward projecting fan blades.
    Type: Grant
    Filed: November 2, 2011
    Date of Patent: April 14, 2015
    Assignee: United Technologies Corporation
    Inventor: Daniel B. Kupratis
  • Publication number: 20150096303
    Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
    Type: Application
    Filed: December 17, 2014
    Publication date: April 9, 2015
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu, Daniel Bernard Kupratis, William K. Ackermann
  • Patent number: 8935913
    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
    Type: Grant
    Filed: October 5, 2012
    Date of Patent: January 20, 2015
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • Patent number: 8931285
    Abstract: In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations.
    Type: Grant
    Filed: May 1, 2014
    Date of Patent: January 13, 2015
    Assignee: United Technologies Corporation
    Inventors: Michael E. McCune, William G. Sheridan, Lawrence E. Portlock
  • Publication number: 20150000304
    Abstract: A gas turbine engine includes a nosecone assembly attached to a gas turbine engine. The nosecone assembly includes a support structure and a nosecone attached to the support structure. The nosecone includes at least a first tool hole extending through the nosecone. The first tool hole is structurally reinforced.
    Type: Application
    Filed: December 26, 2013
    Publication date: January 1, 2015
    Inventors: Anthony T. Lindsey, Arun Kumar Jayasingh, Herbert L. Walker
  • Patent number: 8919133
    Abstract: A double-body gas turbine engine, including a low-pressure body LP and a high-pressure body HP, rotatably mounted about a single shaft in a stationary casing, the low-pressure body LP including a compressor and a turbine connected by a low-pressure shaft LP. The low-pressure shaft LP is supported by an upstream LP bearing, a first downstream LP bearing, and an additional downstream LP bearing by the stationary casing, the high-pressure body being supported by an upstream HP bearing and a downstream HP bearing which is an inter-shaft bearing including an inner track rigidly connected to the HP turbine rotor and an outer track rigidly connected to the LP shaft.
    Type: Grant
    Filed: April 15, 2010
    Date of Patent: December 30, 2014
    Assignee: Snecma
    Inventors: Jacques René Bart, Didler René André Escure, Ornella Gastineau
  • Publication number: 20140360205
    Abstract: One embodiment of the present disclosure is a unique gas turbine engine. Another embodiment of the present disclosure is a unique machine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and electrical systems.
    Type: Application
    Filed: December 19, 2013
    Publication date: December 11, 2014
    Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Mat French, John T. Alt, Mark J. Blackwelder
  • Publication number: 20140338352
    Abstract: This invention relates to a multi-spool gas turbine engine, including: a first generator for providing electrical power to an electrical system, the generator being driveably connected to a first spool; a second generator for providing electrical power to the electrical system, the generator being driveably connected to a second spool; a disconnection device for disconnecting the second generator from the second spool; and, a controller configured to selectively operate the disconnection device under predetermined powered engine conditions.
    Type: Application
    Filed: November 1, 2013
    Publication date: November 20, 2014
    Inventors: Huw Llewelyn EDWARDS, Robert William SLATER
  • Patent number: 8881534
    Abstract: A gas turbine engine is provided that includes a gearbox operable to selectively couple a relatively high pressure spool shaft to a relatively low pressure spool shaft. In one form the gearbox includes a cone clutch that engages a male member of the cone clutch to a female member of the cone clutch during an engine start of the gas turbine engine. A relatively high pressure of a working fluid can be used to bring the male member and the female member together. A spring can also be used to urge the male member and the female member apart when the working fluid is at a relatively low pressure.
    Type: Grant
    Filed: December 11, 2009
    Date of Patent: November 11, 2014
    Assignee: Rolls-Royce Corporation
    Inventors: Andrew D. Copeland, Al Cookerly
  • Patent number: 8869504
    Abstract: A three-spool turbofan engine (20) has a variable fan nozzle (35). The fan blades have a peak tip radius RT and an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of RH to RT is less than about 0.40.
    Type: Grant
    Filed: November 22, 2013
    Date of Patent: October 28, 2014
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, William G. Sheridan
  • Patent number: 8857149
    Abstract: A turbofan engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a fan drive gear system including a carrier for supporting a plurality of gears. A torque frame is attached to the carrier. A plurality of connectors extends between the carrier and torque frame for securing the torque frame to the carrier. A scupper captures lubricant during gear operation and directing lubricant into a space between at least one of the plurality of connectors and at least one of the torque frame and the carrier.
    Type: Grant
    Filed: May 14, 2014
    Date of Patent: October 14, 2014
    Assignee: United Technologies Corporation
    Inventor: Marc J. Muldoon
  • Patent number: 8838359
    Abstract: Starter control valve failure prediction machines, systems, computer readable media, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic and to make predictions of starter control valve failures, are provided.
    Type: Grant
    Filed: January 24, 2013
    Date of Patent: September 16, 2014
    Assignee: Lockheed Martin Corporation
    Inventors: Hai Qiu, Naresh Sundaram Iyer, Weizhong Yan
  • 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
  • Publication number: 20140230452
    Abstract: In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations.
    Type: Application
    Filed: May 1, 2014
    Publication date: August 21, 2014
    Applicant: United Technologies Corporation
    Inventors: Michael E. McCune, William G. Sheridan, Lawrence E. Portlock
  • Patent number: 8800298
    Abstract: A washer for a turbine engine combustor comprises a first surface, a second surface facing generally opposite from the first surface, a bore communicating through the first and second surfaces, and a cooling passage separate from the bore and communicating through the first and second surfaces.
    Type: Grant
    Filed: July 17, 2009
    Date of Patent: August 12, 2014
    Assignee: United Technologies Corporation
    Inventors: Scott A. Ladd, Kevin Joseph Low
  • Publication number: 20140182299
    Abstract: A system includes a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust flow path, at least one main combustor disposed upstream from the turbine, wherein the at least one main combustor is configured to combust a fuel with a first oxidant and an exhaust gas to generate the combustion products, at least one reheat combustor disposed in or between turbine stages of the turbine, wherein the at least one reheat combustor is configured to reheat the combustion products by adding a second oxidant to react with unburnt fuel in the combustion products, and an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route the exhaust gas from the turbine to the at least one main combustor along an exhaust recirculation path.
    Type: Application
    Filed: October 30, 2013
    Publication date: July 3, 2014
    Applicant: General Electric Company
    Inventors: John Farrior Woodall, Andrei Tristan Evulet, Samuel David Draper
  • Patent number: 8745991
    Abstract: A turbine system includes a compressor unit which compresses a fluid; a combustor unit which burns fuel with the compressed fluid; a turbine unit which is driven due to a combustion gas that is generated when the combustor unit burns the fuel; and a first device which receives power that is generated when the turbine unit is driven. The at least one compressor unit operates using at least the generated power, and is separately disposed from at least one of the turbine unit and the first device.
    Type: Grant
    Filed: July 7, 2010
    Date of Patent: June 10, 2014
    Assignee: Samsung Techwin Co., Ltd.
    Inventors: Myeong-hyo Kim, Min-seok Ko, Jong-sub Shin
  • Publication number: 20140102076
    Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.
    Type: Application
    Filed: August 30, 2012
    Publication date: April 17, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Publication number: 20140090388
    Abstract: An example method of allocating power within a gas turbine engine includes driving an off-take power delivery assembly using a first amount of power from a spool, the first amount of power corresponding to an off-take power requirement of a gas turbine engine; and driving the spool of the gas turbine engine using a second amount of power, wherein a ratio of the first amount of power to the second amount of power is greater than or equal to 0.009.
    Type: Application
    Filed: December 17, 2012
    Publication date: April 3, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: United Technologies Corporation
  • Patent number: 8667773
    Abstract: A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: March 11, 2014
    Assignee: United Technologies Corporation
    Inventor: Peter D. Silkowski
  • Patent number: 8607576
    Abstract: A gas turbine engine is provided, which includes a first compressor rotor coupled to a first shaft, a second compressor rotor downstream of the first compressor and coupled to a second shaft. A combustor is disposed downstream of the compressor rotors. A turbine is disposed downstream of the combustor and coupled to the second shaft. A gear is configured to be driven by the second shaft. The second shaft is configured for driving the first shaft through the gear, whereby the turbine drives the first compressor rotor at a different rotational speed than the turbine.
    Type: Grant
    Filed: June 7, 2012
    Date of Patent: December 17, 2013
    Assignee: United Technologies Corporation
    Inventor: Joseph T. Christians
  • Publication number: 20130318998
    Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor and three turbine sections. A fan drive drives the fan through a gear reduction. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. A second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area. A ratio of the first performance quantity to the second performance quantity is between about 0.5 and about 1.5.
    Type: Application
    Filed: May 31, 2012
    Publication date: December 5, 2013
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis
  • Publication number: 20130318999
    Abstract: An exemplary gas turbine engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The fan includes a first plurality of fan blades supported on a first fan support and a second plurality of fan blades supported on a second fan support. The first and second fan supports are rotatable about a fan axis independently of each other. A geared architecture includes at least one gear driven by the turbine section for rotating about a gear axis that is transverse to the fan axis. The gear drives the fan supports for rotating the respective pluralities of fan blades in opposite directions.
    Type: Application
    Filed: May 31, 2012
    Publication date: December 5, 2013
    Inventor: James L. Lucas
  • Patent number: 8596076
    Abstract: The present invention provides a variable pressure ratio gas turbine. In an embodiment, the engine is configured to selectively bypass all or a portion of a high pressure compressor and a high pressure turbine. In an embodiment, during bypass operation, all or a portion of the flow that would otherwise pass through the high pressure compressor and the high pressure turbine may be routed through a respective compressor bypass duct and turbine bypass duct.
    Type: Grant
    Filed: December 30, 2009
    Date of Patent: December 3, 2013
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Mark Gritton, Matthew J. Starr, Theodore J. Fritsch
  • Publication number: 20130305738
    Abstract: A system for providing hydrogen enriched fuel includes first and second gas turbines. The second gas turbine receives a fuel from a fuel supply and portion of compressed working fluid from the first gas turbine and produces a reformed fuel, and a fuel skid provides fluid communication between a turbine in the second gas turbine and a combustor in the first gas turbine. A method for providing hydrogen enriched fuel includes diverting a portion of a first compressed working fluid from a first compressor to a second compressor and providing a second compressed working fluid from the second compressor. Mixing a first portion of a compressed fuel with the second compressed working fluid in a reformer to produce a reformed fuel, flowing a second portion of the compressed fuel to a second turbine for cooling, and flowing the reformed fuel through the second turbine to cool the reformed fuel.
    Type: Application
    Filed: May 17, 2012
    Publication date: November 21, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Michael John Hughes, Jonathan Dwight Berry
  • Publication number: 20130255275
    Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.
    Type: Application
    Filed: April 12, 2012
    Publication date: October 3, 2013
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis
  • Publication number: 20130255274
    Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and coupling the first shaft to fan.
    Type: Application
    Filed: April 2, 2012
    Publication date: October 3, 2013
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz