Selectively Connectable Patents (Class 60/39.163)
  • Patent number: 10890115
    Abstract: A disclosed 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 a superposition gearbox including a sun gear, 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 is selectively coupled to the sun gear through a starter clutch. A first clutch selectively couples the first tower shaft to the ring gear and a second clutch selectively couples the ring gear to a static structure of the engine. An accessory gearbox is driven by an output of the superposition gearbox.
    Type: Grant
    Filed: September 28, 2018
    Date of Patent: January 12, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Joseph H. Polly, Nicholas D. Leque
  • Patent number: 10823080
    Abstract: The present disclosure is directed to a gas turbine engine including an engine shaft rotatable with at least one of a fan section, a compressor section, or a turbine section, and an accessory gearbox assembly including a towershaft, a first gearbox, a torque transfer assembly, and a second gearbox. The towershaft is rotatable with the engine shaft and extended therefrom and mechanically coupled to the first gearbox. The first gearbox transmits mechanical energy from the engine shaft via a first shaft defining a first end and a second end. The first shaft extends at the first end from the first gearbox and through the torque transfer assembly and coupled thereto. The first shaft extends from the torque transfer assembly to the second gearbox at the second end and is coupled thereto. The first gearbox and the second gearbox each are coupled to one or more gearbox accessories.
    Type: Grant
    Filed: May 31, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventor: Mark Gregory Wotzak
  • Patent number: 10815900
    Abstract: A gas turbine engine comprises a gearbox including a first epicyclic gearbox and a second epicyclic gearbox. The first epicyclic gearbox comprises a first sun gear meshing with the first planet gears and the first planet gears meshing with a first annulus gear. The second epicyclic gearbox comprises a second sun gear meshing with the second planet gears and the second planet gears meshing with a second annulus gear. An input shaft is arranged to drive the first sun gear and a first planet gear carrier is arranged to drive a propulsor. The first and second annulus gears are fixed to a static structure. A first clutch is arranged between the first planet gear carrier and the second planet gear carrier and a second clutch is arranged between the second sun gear and the input shaft. The gearbox is more efficient at cruise conditions.
    Type: Grant
    Filed: May 4, 2018
    Date of Patent: October 27, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Jason J. Madge
  • Patent number: 10767568
    Abstract: A turbofan engine according to an exemplary embodiment of this disclosure includes, among other possible things, 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; a superposition gearbox including a sun gear, a plurality of intermediate gears engaged to the sun gear and supported in a carrier and a ring gear circumscribing the intermediate gears, wherein the second tower shaft is engaged to drive the sun gear; a first clutch for selectively coupling the first tower shaft to the ring gear; a second clutch for selectively coupling the sun gear to the carrier; and an accessory gearbox driven by an output of the superposition gearbox.
    Type: Grant
    Filed: September 11, 2018
    Date of Patent: September 8, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Nicholas D. Leque, Joseph H. Polly
  • Patent number: 10465611
    Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.
    Type: Grant
    Filed: November 15, 2016
    Date of Patent: November 5, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Keith Morgan, Lazar Mitrovic, Jean Dubreuil, Martin Poulin
  • Patent number: 10415482
    Abstract: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator, characterized in that it comprises a device (40) for controlled mechanical coupling of said gas generator (5) and said free turbine (6) that is capable of connecting said gas generator (5) and said free turbine (6) mechanically and on demand as soon as the rotational speed of said gas generator (5) reaches a predetermined threshold speed.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: September 17, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick Marconi, Romain Thiriet, Camel Serghine
  • Patent number: 10371062
    Abstract: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator (5), characterized in that it comprises a device (20) for spontaneously mechanically coupling said gas generator (5) and said free turbine (6) that is capable of mechanically and spontaneously connecting said gas generator (5) and said free turbine (6) as soon as the ratio of the rotational speed (NGG) of said gas generator to the rotational speed (NTL) of said free turbine reaches a predetermined threshold value.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: August 6, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Patrick Marconi, Romain Thiriet, Olivier Bedrine
  • Patent number: 10329955
    Abstract: An oil system of a turbine engine and a method for driving an oil pump of such oil system are disclosed. In various embodiments, the oil system comprises an oil pump for fluid communication with one or more lubrication loads of the turbine engine, a first source of motive power and a coupling device. The first source of motive power is drivingly engaged to the oil pump for driving the oil pump during a first mode of operation. The coupling device is configured to drivingly disengage a second source of motive power from the oil pump during the first mode of operation and drivingly engage the second source of motive power with the oil pump to drive the oil pump during a second mode of operation.
    Type: Grant
    Filed: January 27, 2016
    Date of Patent: June 25, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: David Menheere, Andrew Marshall
  • Patent number: 10294870
    Abstract: An accessory drive system for an aircraft gas turbine engine is disclosed. The system may comprise an engine case including a core engine cowl and at least a first accessory drive gearbox disposed within the core engine cowl. The at least first accessory drive gearbox may be operatively connected to one or more accessories remotely located therefrom.
    Type: Grant
    Filed: December 18, 2013
    Date of Patent: May 21, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Gary D. Roberge
  • Patent number: 10294857
    Abstract: The present invention discloses an internal combustion engine, comprising a compressor, a combustion chamber, a pipeline, a spray pipe, an oil feeder, a driving device, a first safety device, a second safety device, an electric ignition device, a rack, a first bracket arranged on a top of the rack, a second bracket arranged on an upper part of the rack, a third bracket arranged on a lower part of the rack and a fourth bracket arranged on a left part of the rack. The compressor comprises an inner shell and an outer shell, wherein the inner shell comprises an upper pressing plate and a cylindrical plate; the cylindrical plate can move up and down in the cylindrical plate slot; and an outlet is formed in a non-protruding part at the bottom of the outer shell. The internal combustion engine has simple structure and high efficiency.
    Type: Grant
    Filed: July 21, 2017
    Date of Patent: May 21, 2019
    Inventor: Xiaohui Chen
  • Patent number: 10247108
    Abstract: A propulsion unit of an aircraft including a turbine (15), at least one fan (10) with an axis offset relative to the axis of the turbine and a power transmission mechanism between the turbine and the fan. The power transmission mechanism includes a speed reducing gear (20) with an input and a movement output, the input being in the extension of the axis (16) of the turbine and the output connected to the fan.
    Type: Grant
    Filed: October 3, 2016
    Date of Patent: April 2, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Augustin Marc Michel Curlier, Sebastien Courtois
  • Patent number: 10113482
    Abstract: A gearbox for an aircraft engine including first and second gears in driving engagement through planet gears supported by a carrier. Selective application of a brake and a blocking member permit operation in a speed change configuration and a direct drive configuration.
    Type: Grant
    Filed: November 15, 2016
    Date of Patent: October 30, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Martin Poulin
  • Patent number: 9759094
    Abstract: A pump for a gas turbine engine is provided. The pump includes a first drive track having a spline and a first gear each rigidly attached to a first driveshaft. The pump also includes a second drive track having a second gear rigidly attached to a second driveshaft. The second gear is mechanically coupled to the first gear. Additionally, a first lubrication supply pump is mechanically coupled to the first driveshaft and a second lubrication supply pump is mechanically coupled to the second driveshaft. The first and second lubrication supply pumps are together configured to provide a desired amount of lubrication to the gas turbine engine.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: September 12, 2017
    Assignee: General Electric Company
    Inventor: Walter Decania Hutto, Jr.
  • Patent number: 9506422
    Abstract: A gas turbine engine includes a spool, a turbine coupled to drive the spool, and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 20 of the propulsor blades.
    Type: Grant
    Filed: July 5, 2011
    Date of Patent: November 29, 2016
    Assignee: United Technologies Corporation
    Inventors: Edward J. Gallagher, Byron R. Monzon
  • Patent number: 9297305
    Abstract: A free-turbine turboshaft engine including a gas generator including at least one compressor supplied with air, a combustion chamber receiving the compressed air at the output of the compressor, and at least one generator turbine mechanically connected to the compressor by a drive shaft and driven by gases from combustion of fuel carried out in the combustion chamber, and including a free turbine supplied by the gases from the combustion after passing through the generator turbine and which drives a power shaft positioned non-coaxially relative to the drive shaft of the gas generator and supplying the power of the turboshaft engine via a reduction gear. The combustion chamber is a substantially cylindrical or frusto-conical chamber, coaxial with the axis of the generator turbine, and includes a single injector.
    Type: Grant
    Filed: September 29, 2010
    Date of Patent: March 29, 2016
    Assignee: TURBOMECA
    Inventors: Antoine Drachsler, Alain Michel Perbos, Joel Silet
  • Patent number: 9062611
    Abstract: A gas turbine engine includes a spool, a first accessory gearbox, a second accessory gearbox, and a scavenge pump. The first accessory gearbox is connected to and driven by the spool. The second accessory gearbox is connected to and driven by the first accessory gearbox. The scavenge pump is connected between the first accessory gearbox and the second accessory gearbox. The first accessory gearbox drives the second accessory gearbox through the scavenge pump.
    Type: Grant
    Filed: October 19, 2011
    Date of Patent: June 23, 2015
    Assignee: United Technologies Corporation
    Inventor: William G. Sheridan
  • Patent number: 9045996
    Abstract: A method of increasing the operational efficiency of an operating gas turbine engine includes supplying mechanical power from a first spool of the operating gas turbine engine to a first electrical machine to thereby generate electrical power using the first electrical machine and supplying mechanical power from a second spool of the operating gas turbine engine to a second electrical machine to thereby generate electrical power using the second electrical machine. The method further includes sensing one or more operational parameters of the operating gas turbine engine and, based on the one or more sensed operational parameters, ceasing to generate electrical power using the second electrical machine, and instead supplying at least a part of the electrical power generated by the first electrical machine to the second electrical machine to operate in motoring mode and to thereby generate and supply mechanical output power to the second spool of the engine.
    Type: Grant
    Filed: November 20, 2012
    Date of Patent: June 2, 2015
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Cristian Anghel, Wayne Pearson, Jens Gehrke, Kevin Condon
  • Patent number: 9038366
    Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
    Type: Grant
    Filed: October 30, 2013
    Date of Patent: May 26, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brian D. Merry, Gabriel L. Suciu, Lisa I. Brilliant, Becky E. Rose, Yuan Dong, Stanley J. Balamucki
  • 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
  • Patent number: 8943839
    Abstract: A gas turbine engine includes a first spool, a first gear system connected to and driven by the first spool, a second spool, and a second gear system connected to and driven by the second spool. A first starter-generator has a first shaft with a switchable coupling connected to the first shaft. The switchable coupling selectively couples the first starter-generator to the first gear system when the switchable coupling is in a first position and selectively couples the first starter-generator to the second gear system when the switchable coupling is in a second position.
    Type: Grant
    Filed: August 26, 2011
    Date of Patent: February 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu
  • 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: 8935912
    Abstract: A gas turbine engine has a variable overall pressure rate (“OPR”). The engine includes a high pressure compressor having at least a primary stage having a set of primary rotors and a secondary stage having a set of secondary rotors. A clutch is provided to selectively engage the secondary rotors with the primary rotors. Engagement of the clutch may be controlled based on the vehicle travel mode, such as disengaging during a takeoff mode to reduce turbine entry temperature and engaging during a loiter mode to increase OPR.
    Type: Grant
    Filed: December 9, 2011
    Date of Patent: January 20, 2015
    Assignee: United Technologies Corporation
    Inventors: James W. Norris, Daniel B. Kupratis, Gary M. Stetson
  • Patent number: 8887485
    Abstract: An adaptive cycle gas turbine engine is disclosed having a number of features. A fan arrangement is provided having counter-rotating fan stages, one fan stage is operable to be clutched and decoupled from the other stage. A high pressure compressor bypass is also provided. A clutch is provided to at least partially drive an intermediate pressure compressor with a high pressure turbine when the high pressure compressor is bypassed. A partial bypass of the high pressure turbine may be provided.
    Type: Grant
    Filed: October 20, 2009
    Date of Patent: November 18, 2014
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Robert A. Ress, Jr.
  • 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: 8863491
    Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
    Type: Grant
    Filed: August 28, 2013
    Date of Patent: October 21, 2014
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, Karl L. Hasel
  • Publication number: 20140290265
    Abstract: A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g. connected to a compressor rotor) is engaged to the driving member. First and second power transfer devices are engaged to the first spool and the selectively rotatable member, respectively. A circuit interconnects the power transfer devices and allows a power transfer therebetween, and a control unit controls the power being transferred between the power transfer devices. Power can thus be transferred between the first spool and the selectively rotatable member to change the speed ratio between the first spool and the rotatable shaft.
    Type: Application
    Filed: January 30, 2013
    Publication date: October 2, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: PRATT & WHITNEY CANADA CORP.
  • Patent number: 8807477
    Abstract: A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: August 19, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • Patent number: 8800914
    Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: August 12, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • 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
  • Patent number: 8701381
    Abstract: A system for aircraft propulsion is disclosed herein. The system includes a power plant. The system also includes an open rotor module operable to rotate. The open rotor module has a plurality of variable-pitch blades. The system also includes a first linkage extending between the power plant and the open rotor module. The first linkage is operable to transmit rotational power to the open rotor module for rotating the plurality of variable-pitch blades. The system also includes an actuator operable to change a pitch of the plurality of variable-pitch blades. The system also includes a generator operable to generate electric power. The system also includes a second linkage extending between the power plant and the generator. The second linkage is operable to transmit rotational power to the generator. The generator is operable to convert the rotational power to electrical power. The system also includes a controller operably coupled to the actuator to vary a pitch of the plurality of variable-pitch blades.
    Type: Grant
    Filed: November 24, 2010
    Date of Patent: April 22, 2014
    Assignee: Rolls-Royce Corporation
    Inventor: David John Howard Eames
  • Patent number: 8701380
    Abstract: A turbine engine including two respectively upstream and downstream external impellers that are nonstreamlined, coaxial, and contrarotating is provided. The downstream impeller is retractable so as to reduce its diameter. The blades of the downstream impeller are mounted so as to pivot about a pivot, the axis of which forms a nonzero angle, notably perpendicular, with the axis of rotation of the impeller, the blades in the retracted position being tilted about the pivot.
    Type: Grant
    Filed: July 1, 2011
    Date of Patent: April 22, 2014
    Assignee: SNECMA
    Inventor: Alexandre Alfred Gaston Vuillemin
  • Patent number: 8695920
    Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: April 15, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • Patent number: 8684303
    Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four (4) stages.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: April 1, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson
  • Patent number: 8640437
    Abstract: A mini combined cycle power plant with a mini gas turbine engine that operates at around 20,000 to 30,000 rpm and is connected to an electric generator through a speed reduction gear box, a low pressure steam turbine connected directly to the gas turbine engine, a high pressure steam turbine connected to the low pressure steam turbine through a smaller gear box so that the high pressure steam turbine can operate at around 70,000 to 100,000 rpm, and a heat recovery steam generator to use the turbine exhaust to produce high pressure steam for the two steam turbines. Leftover heat from the HRSG is used to heat homes or buildings in the local area to the power plant to improve the overall efficiency of the plant.
    Type: Grant
    Filed: February 24, 2011
    Date of Patent: February 4, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Joseph D Brostmeyer
  • Patent number: 8615980
    Abstract: A rotary-wing aircraft includes a retractable port movable between a closed position and an open position to selectively control flow of combustion gases into a bypass passage to change a power distribution between a rotor system and a secondary propulsion system.
    Type: Grant
    Filed: October 11, 2011
    Date of Patent: December 31, 2013
    Assignee: United Technologies Corporation
    Inventors: Rajendra K. Agrawal, Steven J. Sirica, William F. Schneider
  • 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
  • Patent number: 8561383
    Abstract: A gas turbine engine (10) provides a differential gear system (58) coupling the turbine (20) to the bypass fan (14) and the compressor (16). In this manner, the power/speed split between the bypass fan and the compressor can be optimized under all conditions. In the example shown, the turbine drives a sun gear (74), which drives a planet carrier (78) and a ring gear (80) in a differential manner. One of the planet carrier and the ring gear is coupled to the bypass fan, while the other is coupled to the compressor.
    Type: Grant
    Filed: December 1, 2004
    Date of Patent: October 22, 2013
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Gino J. Pagluica, Loc Quang Duong, Lawrence E. Portlock
  • Patent number: 8534074
    Abstract: A dual clutch arrangement is disclosed herein. The dual clutch arrangement includes a first input rotatable member. The dual clutch arrangement also includes an output rotatable member. The dual clutch arrangement also includes a first clutch coupling the first input rotatable member and the output rotatable member such that the first input rotatable member drives the output rotatable member in rotation. The first clutch is operable to be overrun. The dual clutch arrangement also includes a second input rotatable member. The dual clutch arrangement also includes a second clutch operable to selectively couple the second input rotatable member and the output rotatable member such that the second input rotatable member drives the output rotatable member in rotation. The first clutch is overrun when the second clutch is engaged.
    Type: Grant
    Filed: May 13, 2009
    Date of Patent: September 17, 2013
    Assignee: Rolls-Royce Corporation
    Inventor: Andrew D. Copeland
  • Patent number: 8522526
    Abstract: With an engine for aircraft with high electric power demand, the power of the low-pressure shaft (7) operating in a lower speed range is transmitted to the high-pressure shaft (6) by an electromagnetic clutch (10). In the clutch element (14) on the side of the low-pressure shaft a frequency-controllable rotary field is generated, which drives a magnet (13) connected to the high-pressure shaft.
    Type: Grant
    Filed: June 1, 2007
    Date of Patent: September 3, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co.
    Inventor: Metin Talan
  • Patent number: 8511604
    Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.
    Type: Grant
    Filed: May 31, 2012
    Date of Patent: August 20, 2013
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • Patent number: 8511605
    Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.
    Type: Grant
    Filed: May 31, 2012
    Date of Patent: August 20, 2013
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • Patent number: 8511058
    Abstract: A convertible gas turbine propulsion system operates in multiple output modes. The convertible gas turbine propulsion system comprises a gas generator, a first power turbine, a secondary propulsion system and an exhaust duct. The gas generator is configured to produce exhaust gas. The first power turbine is aligned with the gas generator to receive the exhaust gas. The secondary propulsion system is in series with the gas generator and the first power turbine. The exhaust duct coaxially extends from the first power turbine to the secondary propulsion system. The exhaust duct includes an exhaust port for opening the exhaust duct to ambient air pressure and permitting exhaust gas to bypass the secondary propulsion system. In various embodiments of the invention, the first power turbine is connected to a first rotary propulsion system, and the secondary propulsion system comprises a second power turbine or a nozzle.
    Type: Grant
    Filed: November 29, 2007
    Date of Patent: August 20, 2013
    Assignee: United Technologies Corporation
    Inventors: Rajendra K. Agrawal, Steven J. Sirica, William F. Schneider
  • Patent number: 8511061
    Abstract: A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. The shaft includes a main shaft and a flex shaft having bellows. The flex shaft is secured to the main shaft at a first end and includes a second end opposite the first end. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supports the shaft relative to the inlet case. The second bearing is arranged radially outward from the flex shaft.
    Type: Grant
    Filed: February 8, 2013
    Date of Patent: August 20, 2013
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L Suciu
  • Publication number: 20130192199
    Abstract: A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. The shaft includes a main shaft and a flex shaft having bellows. The flex shaft is secured to the main shaft at a first end and includes a second end opposite the first end. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supports the shaft relative to the inlet case. The second bearing is arranged radially outward from the flex shaft.
    Type: Application
    Filed: February 8, 2013
    Publication date: August 1, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: United Technologies Corporation
  • Patent number: 8448895
    Abstract: A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
    Type: Grant
    Filed: May 31, 2012
    Date of Patent: May 28, 2013
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
  • Patent number: 8425372
    Abstract: A gearbox has a first rotative component and a second rotative component, the gearbox having a rotary input and a rotary output, a first brake for braking the first rotative component of the gearbox against rotation thereof, and a second brake for braking the second rotative component of the gearbox against rotation thereof. The rotary input drives the rotary output if the first brake brakes the first rotative component of the gearbox and the rotary output drives the first rotative component of the gearbox if the second brake brakes the second rotative component of the gearbox.
    Type: Grant
    Filed: July 14, 2010
    Date of Patent: April 23, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Glenn C. Lemmers, Jr.
  • Patent number: 8424280
    Abstract: A gas turbine engine arrangement comprises a first gas turbine engine, a second gas turbine engine, a differential gearbox and an electrical generator. The differential gearbox has a first input drive, a second input drive and an output drive. The output drive of the differential gearbox is arranged to drive the electrical generator via an external, accessory, gearbox. The external, accessory, gearbox drives other accessories. The first gas turbine is arranged to drive the first input drive of the differential gearbox and the second gas turbine engine is arranged to drive the second input drive of the differential gearbox. The electrical generator and accessories are driven at a constant frequency speed/frequency.
    Type: Grant
    Filed: February 25, 2009
    Date of Patent: April 23, 2013
    Assignee: Rolls-Royce, PLC
    Inventors: Gareth E Moore, David R Trainer, David P Scothern, David S Knott, Paul Simms
  • Patent number: 8402741
    Abstract: A gas turbine engine includes a core housing providing a core flowpath. A shaft supports a compressor section arranged within the core flowpath. First and second bearings support the shaft relative to the core housing and are arranged radially inward of and axially overlapping with the compressor section.
    Type: Grant
    Filed: January 31, 2012
    Date of Patent: March 26, 2013
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu
  • Publication number: 20130008144
    Abstract: A gas turbine engine includes a spool, a turbine coupled to drive the spool and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the spool drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 16 of the propulsor blades.
    Type: Application
    Filed: July 5, 2011
    Publication date: January 10, 2013
    Inventors: Edward J. Gallagher, Jun Jiang, Becky E. Rose, Jason Elliott, Anthony R. Bifulco
  • Patent number: 8350398
    Abstract: An open-rotor gas turbine engine comprising a starter/generator, a first spool and a second spool, the second spool is of a lower pressure than the first spool; wherein the starter/generator is connected to the first and second spools via first and second clutches respectively. The method of operating the open-rotor engine comprises the step of supplying power to the starter/generator to drive the first spool via the first clutch to start the engine and, once the engine is self-propelling, a step of driving the starter/generator from the second spool via the second clutch to generate electricity.
    Type: Grant
    Filed: October 28, 2009
    Date of Patent: January 8, 2013
    Assignee: Rolls-Royce, PLC
    Inventor: David C. Butt