Having Means To Effect A Variable Bypass Ratio Patents (Class 60/226.3)
  • Patent number: 10378477
    Abstract: An exhaust system or nozzle for use in a gas turbine engine is disclosed herein. The exhaust system is adapted to adjust various streams of pressurized air produced by the gas turbine engine to control operation of the gas turbine.
    Type: Grant
    Filed: February 26, 2016
    Date of Patent: August 13, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Kenneth M. Pesyna
  • Patent number: 10094281
    Abstract: A gas turbine engine comprises a fan on an engine central axis. Plural gas generators are downstream of the fan, each along a respective central axis, mutually offset, and offset from the engine central axis. A fan drive turbine is on the engine central axis, downstream of the dual gas generators, and driven by output from the dual gas generators, to drive the fan.
    Type: Grant
    Filed: January 13, 2015
    Date of Patent: October 9, 2018
    Assignee: United Technologies Corporation
    Inventors: Jesse M. Chandler, Gabriel L. Suciu
  • Patent number: 10001084
    Abstract: A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat area for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.
    Type: Grant
    Filed: June 14, 2012
    Date of Patent: June 19, 2018
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Kenneth M. Pesyna, Bryan Henry Lerg, Michael Abraham Karam
  • Patent number: 9995174
    Abstract: A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed.
    Type: Grant
    Filed: March 23, 2012
    Date of Patent: June 12, 2018
    Assignee: United Technologies Corporation
    Inventors: Michael E. McCune, William G. Sheridan, Lawrence E. Portlock
  • Patent number: 9920710
    Abstract: An exhaust system for a variable cycle aircraft engine. The exhaust system comprises a core exhaust for bypass air and hot gases of combustion. The core exhaust includes a convergent-divergent nozzle. The convergent-divergent nozzle is formed from a plurality of flaps and seals. The exhaust system comprises a third air duct for a third stream of air. The third stream of air is selectively exhausted from the third duct through a secondary nozzle or divergent slots in the convergent-divergent nozzle, or both depending upon the flight mode. A diverter valve is positioned in the third stream duct to selectively control the flow of third stream air through the secondary nozzle, the divergent slots and combinations thereof.
    Type: Grant
    Filed: May 7, 2013
    Date of Patent: March 20, 2018
    Assignee: General Electric Company
    Inventors: David Lynn Dawson, Erin Lee Lariviere, Brian Joseph Petersen, Robert Jerome Ellerhorst
  • Patent number: 9915229
    Abstract: A bypass duct has a support unit comprising a pair of aerofoils arranged as an “A” frame. A bleed duct assembly is provided on the radially inner wall of the bypass duct annulus and the aerofoils project from the surface and extend across the annulus between the inner wall and an outer wall of the annulus. The aerofoils lean at an acute angle to the surface with the first flank facing toward the inner wall and adjoining a bleed duct opening. The bleed duct having a bleed duct passage and a submerged scoop.
    Type: Grant
    Filed: August 8, 2014
    Date of Patent: March 13, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag Todorovic
  • Patent number: 9816442
    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: Grant
    Filed: December 17, 2014
    Date of Patent: November 14, 2017
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu, Daniel Bernard Kupratis, William K. Ackermann
  • Patent number: 9739206
    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: Grant
    Filed: December 29, 2016
    Date of Patent: August 22, 2017
    Assignee: United Technologies Corporation
    Inventors: David P. Houston, Daniel Bernard Kupratis, Frederick M. Schwarz
  • Patent number: 9695751
    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: December 30, 2016
    Date of Patent: July 4, 2017
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • Patent number: 9624828
    Abstract: A turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air. A power turbine converts the gas stream flow into shaft power. The power turbine rotates at a first rotational speed. A speed reduction device is driven by the power turbine. A propulsor section includes a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The fan includes a tip diameter greater than about fifty (50) inches and an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.30 at a take-off condition.
    Type: Grant
    Filed: April 26, 2013
    Date of Patent: April 18, 2017
    Assignee: United Technologies Corporation
    Inventor: Jayant Sabnis
  • Patent number: 9624827
    Abstract: A turbofan engine includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in the ambient air and a power turbine that converts the gas stream flow into shaft power. The turbofan engine further includes a propulsor section including a fan driven by the power turbine through a geared architecture at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. An Engine Unit Thrust Parameter defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.15 at a take-off condition.
    Type: Grant
    Filed: April 1, 2013
    Date of Patent: April 18, 2017
    Assignee: United Technologies Corporation
    Inventor: Jayant Sabnis
  • Patent number: 9624870
    Abstract: An adaptive fan system for a variable cycle turbofan engine having at least one turbine, includes a shaft structured to receive mechanical power from a turbine in the variable cycle turbofan engine and a first fan stage that is coupled directly to the shaft and is driven directly by the shaft. A transmission system is coupled to the shaft and a second fan stage is coupled to the shaft via the transmission system and is driven by the shaft via the transmission system. The transmission system is structured to selectively vary a speed between high and low speeds at which power is supplied from the shaft to the second fan stage relative to at least one of the shaft and the first fan stage, wherein the first fan stage and the second fan stage are configured to rotate in the same direction and at the same high speed to increase the mechanical power of the turbine.
    Type: Grant
    Filed: March 27, 2011
    Date of Patent: April 18, 2017
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Robert A. Ress, Jr., Steve Stratton, Matthew J. Starr
  • Patent number: 9562687
    Abstract: The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles.
    Type: Grant
    Filed: February 6, 2013
    Date of Patent: February 7, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Thomas Edward Johnson, Willy Steve Ziminsky, Heath Michael Ostebee, Christopher Paul Keener
  • Patent number: 9506424
    Abstract: A device and a method for bleeding compressor air in an engine includes at least one actuator and at least one closing element linked to the actuator for closing or partially closing a bypass duct via which compressor air can be bled off. It is provided here that the closing element is designed to be successively moved into the bypass duct, with the airflow passing through the bypass duct being settable by the position of the closing element. Furthermore, an air guiding device linked to the closing element is provided and has air guiding surfaces which adjoin the closing element downstream, the spatial alignment of the air guiding surfaces being dependent on the position of the closing element.
    Type: Grant
    Filed: August 4, 2014
    Date of Patent: November 29, 2016
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Jean-Marc Siering
  • Patent number: 9488101
    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: Grant
    Filed: March 12, 2014
    Date of Patent: November 8, 2016
    Assignee: United Technologies Corporation
    Inventor: Daniel Bernard Kupratis
  • Patent number: 9394805
    Abstract: A rotor has a rotor body with at least one slot receiving a blade. The blade has an outer surface, at least at some areas, formed of a first material and having an airfoil extending from a dovetail. The dovetail is received in the slot. A diode is in contact with a portion of the dovetail formed of a second material that is more electrically conductive than the first material. The diode is in contact with a rotating element that rotates with the rotor. The rotating element is formed of a third material. The first material is less electrically conductive than the third material. The diode and the rotating element together form a ground path from the portion of the dovetail into the rotor. An engine and a fan blade are also disclosed.
    Type: Grant
    Filed: December 14, 2012
    Date of Patent: July 19, 2016
    Assignee: United Technologies Corporation
    Inventors: James O. Hansen, Thomas J. Garosshen, Thomas J. Watson
  • Patent number: 9261019
    Abstract: One embodiment of the present invention is a unique variable cycle gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for variable cycle gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: December 27, 2011
    Date of Patent: February 16, 2016
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Craig Heathco
  • Patent number: 9194331
    Abstract: A gas turbine jet engine having a main flow channel and a housing structure which radially surrounds this main flow channel. A housing gas flow flows in the same direction as the main flow in the main flow channel, the housing structure having a flow conducting assembly. The flow of the housing gas flow to and/or along the main flow channel may be adjusted by adjusting a flow conducting sheet.
    Type: Grant
    Filed: July 15, 2013
    Date of Patent: November 24, 2015
    Assignee: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Norbert Schinko, Christian Eichler, Sandra Muschkorgel
  • Patent number: 9140213
    Abstract: A turbine engine fuel delivery system includes a mounting platform, a spray bar assembly and a leaf spring damper with a stack of a plurality of leaf springs. The stack includes a base segment connected longitudinally between a first spray bar contact segment and a second spray bar contact segment. The base segment is connected to the mounting platform and is located a first distance from the spray bar assembly. The first spray bar contact segment engages the spray bar assembly and is located a second distance from the mounting platform. The second spray bar contact segment engages the spray bar assembly and is located a third distance from the mounting platform.
    Type: Grant
    Filed: December 6, 2011
    Date of Patent: September 22, 2015
    Assignee: United Technologies Corporation
    Inventors: Andreas Sadil, Marc J. Muldoon, Bessem Jlidi
  • Patent number: 9140214
    Abstract: A system and method of reducing noise caused by jet engines is provided. The method comprises the steps of using the afterburner to heat the exhaust gas flow while simultaneously reducing power to the core engine. Together these two operations reduce the pressure of the exhaust gas in the nozzle area while holding the exhaust gas velocity constant, which maintains engine thrust while decreasing engine noise. The method may be supplemented by altering the location of the afterburner flames to create an inverted exhaust velocity profile, thereby decreasing engine noise even further.
    Type: Grant
    Filed: February 28, 2012
    Date of Patent: September 22, 2015
    Assignee: United Technologies Corporation
    Inventor: Alfred M. Stern
  • Patent number: 9140188
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a combustor section, a low spool including a fan section and an intercooling turbine section along an engine axis aft of the fan section and forward of a combustor section. The fan section and the intercooling turbine section are coaxial with the low spool. A high spool along the engine axis includes a high pressure compressor section and a high pressure turbine section, the high pressure compressor section is aft of the intercooling turbine section and forward of the combustor section, and the high pressure turbine section is aft of the combustor section. The high pressure compressor section and the high pressure turbine section are coaxial with the high spool. A method of operating a gas turbine engine is also disclosed.
    Type: Grant
    Filed: November 1, 2011
    Date of Patent: September 22, 2015
    Assignee: United Technologies Corporation
    Inventor: Daniel B. Kupratis
  • Patent number: 9109810
    Abstract: This ventilation system (1), notably for a gas turbine, comprises at least one fan (2) opening into an air extraction duct (5). It comprises at least one device (6) for varying the pressure drop in the air extraction duct (5), comprising a means (8) of regulating the air flow rate in the air extraction duct (5).
    Type: Grant
    Filed: January 25, 2011
    Date of Patent: August 18, 2015
    Assignee: GE Energy Products France SNC
    Inventors: Pascal Dominiak, Joel Coudrieeau, Philippe Carles
  • 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: 20150128561
    Abstract: An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream of air is peeled off of the first stream to form a low pressure fan bypass air stream. The third stream of air traverses along the engine casing and is passed over a flap assembly to aid in cooling. The flaps are operable converge/diverge to control the multiple streams of air.
    Type: Application
    Filed: March 13, 2014
    Publication date: May 14, 2015
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventors: Kenneth M. Pesyna, Anthony F. Pierluissi, Bryan H. Lerg, Justin N. Moore
  • Patent number: 9027323
    Abstract: An adjustable bloom mixer for a turbofan engine for setting a mixing ratio, adapted to the respective flight condition, between cold airflow in the bypass duct and hot airflow in the core flow duct includes an air-guiding element (13) arranged upstream of a thin-walled, corrugated part (6b) of the bloom mixer (6) for branching off a cold partial airflow and/or a hot partial airflow from the bypass duct and from the core flow duct of the engine. An air control device (14) is assigned to the air-guiding element (13) for leading the branched-off cold airflow or hot airflow along the inner surface and/or the outer surface of the bloom mixer (6) in order to deflect its corrugated part (6b) radially inwards or outwards on the basis of a temperature difference between an inner and an outer surface effected by the hot and/or cold partial airflow.
    Type: Grant
    Filed: September 13, 2011
    Date of Patent: May 12, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Robert Thies
  • Publication number: 20150121841
    Abstract: A gas turbine engine includes a core engine, a first bypass passage disposed about the core engine and a second bypass passage disposed about the first bypass passage. A flow control is disposed within the second bypass for controlling bypass airflow through the second bypass. The flow control translates axially between an open position and a closed position to vary and control airflow through the second bypass passage.
    Type: Application
    Filed: March 12, 2014
    Publication date: May 7, 2015
    Applicant: United Technologies Corporation
    Inventors: Felix Izquierdo, Robert H. Bush, Timothy J. McAlice
  • Patent number: 9021813
    Abstract: An apparatus installed on an aircraft, comprising: a sleeve or duct having a trailing lip area; a plurality of petals arranged side by side with gaps therebetween, one end of each petal being attached or pivotably coupled to the lip area; and a plurality of elastomeric seals configured and disposed to close the gaps between adjacent petals. Each elastomeric seal comprises a first portion that moves with a portion of a first petal that is in contact therewith, a second portion that moves with a portion of a second petal that is in contact there, and a third portion which is stretched as the first and second petals move further apart from each other. Petal deflection is actuated by a system comprising a flexible member, a motor, a shaft driven by the motor, and an arm projecting from the shaft. One end of the flexible member is attached to the arm, the flexible member being movable to deflect the petals inward in response to a shaft rotation.
    Type: Grant
    Filed: September 6, 2011
    Date of Patent: May 5, 2015
    Assignee: The Boeing Company
    Inventors: Christopher Jasklowski, Michael L. Sangwin, David William Foutch, Mehmet Bahadir Alkislar, Matthew Anthony Dilligan
  • Publication number: 20150113941
    Abstract: A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.
    Type: Application
    Filed: October 24, 2014
    Publication date: April 30, 2015
    Applicant: United Technologies Corporation
    Inventors: John R. Buey, Robert H. Bush, Felix Izquierdo
  • Publication number: 20150107223
    Abstract: A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.
    Type: Application
    Filed: November 13, 2014
    Publication date: April 23, 2015
    Inventors: Daryl B. Mountz, Theodore W. Kapustka, Glenn Levasseur, Marcus Borg, Joakim Berglund, Anders Svahn, Johan Ockborn, Bengt Pettersson
  • Patent number: 9010085
    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: Grant
    Filed: August 30, 2012
    Date of Patent: April 21, 2015
    Assignee: United Technologies Corporation
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 8997494
    Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
    Type: Grant
    Filed: October 31, 2012
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventors: Sue-Li Chuang, Yuan Dong, Sanjay S. Hingorani, Dilip Prasad
  • Patent number: 8991151
    Abstract: The invention relates to a system for actuating a plurality of actuators (15) that can move a mobile panel of an aircraft nacelle. Said system comprises at least two motors (16) that can drive the actuators (15), the two motors (16) being controlled and supplied by at least two separate control units (33, 35), and the actuators (15) being mechanically interconnected by a mechanical transmission (37). The invention also relates to a nacelle comprising such an actuating system.
    Type: Grant
    Filed: April 7, 2010
    Date of Patent: March 31, 2015
    Assignees: Aircelle, Sagem Defense Securite
    Inventors: Hakim Maalioune, Vincent Le-Coq, Fernand Rodriguez, Pierre Moradell-Casellas
  • Patent number: 8978356
    Abstract: There is provided an actuation system for a gas turbine engine including a thrust reverser and a variable area fan nozzle. The system has a plurality of linear actuators each having a first outer piston concentric with a second inner piston. The first outer piston is operatively connected to a thrust reverser. The second inner piston is operatively connected to a variable area fan nozzle. The system further has a piston lock assembly for selectively locking the first outer piston to the second inner piston. The system further has a control system coupled to the plurality of linear actuators for operating the variable area fan nozzle between a stowed position and a deployed position.
    Type: Grant
    Filed: December 3, 2010
    Date of Patent: March 17, 2015
    Assignee: The Boeing Company
    Inventor: Michael John Burgess
  • Patent number: 8973364
    Abstract: A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.
    Type: Grant
    Filed: June 26, 2008
    Date of Patent: March 10, 2015
    Assignee: United Technologies Corporation
    Inventors: Jonathan Gilson, Dennis Cicon, Oliver V. Atassi
  • Publication number: 20150059315
    Abstract: A device and a method for bleeding compressor air in an engine includes at least one actuator and at least one closing element linked to the actuator for closing or partially closing a bypass duct via which compressor air can be bled off. It is provided here that the closing element is designed to be successively moved into the bypass duct, with the airflow passing through the bypass duct being settable by the position of the closing element. Furthermore, an air guiding device linked to the closing element is provided and has air guiding surfaces which adjoin the closing element downstream, the spatial alignment of the air guiding surfaces being dependent on the position of the closing element.
    Type: Application
    Filed: August 4, 2014
    Publication date: March 5, 2015
    Inventor: Jean-Marc SIERING
  • Patent number: 8955305
    Abstract: The invention relates to a method for the self-calibration of electric jacks (6a, 6b) capable of actuating a mobile member (2) of a turbojet nacelle (1) and connected to at least one position measuring member, characterized in that it comprises the steps of: moving the jack(s) into a retracted position corresponding to a first position of the mobile member, storing one or more position values fed back by the position measuring member for the jack(s) in said retracted position; moving the jack(s) into an extended position corresponding to a second position of the mobile member; storing one or mom position values fed back by the position measuring member for the jack(s) in said extended position.
    Type: Grant
    Filed: February 1, 2008
    Date of Patent: February 17, 2015
    Assignee: Aircelle
    Inventors: Thierry Marin Martinod, Hakim Maalioune
  • Patent number: 8955304
    Abstract: A separate propulsion unit incorporating a free turbine and a fan receives gases from a plurality of core engines. The core engines each include a compressor, a turbine and a combustion section. The core engines in combination pass gases across the free turbine. A method is also disclosed.
    Type: Grant
    Filed: February 10, 2012
    Date of Patent: February 17, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Joseph B. Staubach, Christopher M. Dye
  • Patent number: 8943793
    Abstract: The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterized in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.
    Type: Grant
    Filed: June 16, 2008
    Date of Patent: February 3, 2015
    Assignee: Aircelle
    Inventors: Eric Lecossais, Thierry Ledocte, Pascal Gerard Rouyer, Felix Carimali
  • Patent number: 8939864
    Abstract: A turbine engine includes a fan shaft and at least one tapered bearing mounted on the fan shaft. The fan shaft includes at least one radially extending passage adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear, and a ring gear that surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: January 27, 2015
    Assignee: United Technologies Corporation
    Inventors: Michael E. McCune, Lawrence E. Portlock, Frederick M. Schwarz
  • Patent number: 8938943
    Abstract: One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and bypass mixers. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: August 5, 2011
    Date of Patent: January 27, 2015
    Assignee: Rolls-Royce North American Technoloies, Inc.
    Inventors: Kaare Erickson, Randall E. Yount
  • Patent number: 8935073
    Abstract: A turbofan engine control system and method includes a core nacelle housing (12), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan nacelle (34). A bypass flow path (39) is arranged downstream from the turbofan between the core and fan nacelles. The bypass flow path includes a nozzle exit area (40). A controller (50) detects at least one of a take-off condition and a landing condition. The controller changes effectively the nozzle exit area to achieve a thrust vector in response to the take-off and landing conditions.
    Type: Grant
    Filed: October 12, 2006
    Date of Patent: January 13, 2015
    Assignee: United Technologies Corporation
    Inventors: Wayne Hurwitz, Ashok K. Jain
  • Patent number: 8925295
    Abstract: An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).
    Type: Grant
    Filed: September 19, 2011
    Date of Patent: January 6, 2015
    Assignee: Airbus Operations
    Inventors: Guillaume Bulin, Thierry Surply
  • Patent number: 8919096
    Abstract: A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices.
    Type: Grant
    Filed: February 13, 2009
    Date of Patent: December 30, 2014
    Assignee: Snecma
    Inventors: Nicolas Alain Bader, Rachid Boudyaf, Thomas Deguin, Antoine Jean Baptiste Stutz
  • Publication number: 20140366554
    Abstract: A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path, and a variable area fan nozzle in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section downstream of the first fan nacelle section. The first fan nacelle section and the second fan nacelle section are axially movable relative to one another to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The auxiliary port is defined between the first fan nacelle section and the second fan nacelle section. The first fan nacelle section comprises a first acoustic system which provides an acoustic impedance configured to attenuate a noise characterized by a leading edge of the second fan nacelle section.
    Type: Application
    Filed: August 29, 2014
    Publication date: December 18, 2014
    Inventors: Jonathan Gilson, Andre M. Hall, Oliver V. Atassi, Ramons A. Reba
  • Patent number: 8904750
    Abstract: A turbofan gas turbine engine (10) comprises a variable area exhaust nozzle (12) arranged at the downstream end of a casing (17). A control unit (66) analyzes the power produced by the gas turbine engine (10), the flight speed of the gas turbine engine (1) and/or the altitude of the gas turbine engine (10). The control unit (66) configures the variable area nozzle (12) at a first cross-sectional area (70A) when the flight speed of the gas turbine engine (10) is less than a first predetermined value. The control unit (66) configures the variable area nozzle (12) at a second, smaller, cross-sectional area (70B) when the flight speed of the gas turbine engine (10) is greater than the first predetermined value and the power produced by the gas turbine engine (10) is greater than a second predetermined value.
    Type: Grant
    Filed: September 2, 2009
    Date of Patent: December 9, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Malcolm L. Hillel, Stephen G. Brown
  • Patent number: 8904795
    Abstract: A noise reducing device in a jet engine that has a cylindrical casing, a cylindrical partition wall that is inserted in the casing while protruding partially from a trailing edge of the casing, and a compressor that compresses air that is taken into the cylindrical partition wall, with the inside of the cylindrical partition wall serving as a duct in which a core stream of high-speed air flows, and the space between the cylindrical partition wall and the casing serving as a duct in which a bypass stream of low-speed air flows, and being connected with a wing of an airplane by a pylon that has a projection portion that extends beyond the casing to the downstream of the core stream and the bypass stream, the noise reducing device includes a nozzle, disposed at the pylon on the downstream of the core stream, that injects a fluid toward a noise generation source that is produced from the mutual approach of an ambient air stream that is produced outside of the bypass stream and the core stream.
    Type: Grant
    Filed: February 25, 2009
    Date of Patent: December 9, 2014
    Assignee: IHI Corporation
    Inventors: Tsutomu Oishi, Yoshinori Oba
  • Publication number: 20140345254
    Abstract: A third stream duct producing a third air stream at reduced pressure that is exhausted through a separate nozzle that is concentric with the main or primary engine nozzle. The third stream exhaust air from the separate concentric nozzle is exhausted to a location at which pressure is ambient or sub-ambient. The location at which the third stream air is exhausted contributes to the thrust of the aircraft. The airstream from the third air duct is exhausted through an exhaust nozzle of the third duct that is positioned at the interface between the aft of the airframe and the leading edge of the engine outer flaps. This location is a low pressure region that has a recirculation zone. The exhaust of third stream air to this low pressure region substantially reduces or eliminates this recirculation zone and associated boat tail drag, thereby improving the efficiency of the engine.
    Type: Application
    Filed: May 7, 2013
    Publication date: November 27, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: GENERAL ELECTRIC COMPANY
  • Publication number: 20140345253
    Abstract: An exhaust system for a variable cycle aircraft engine. The exhaust system comprises a core exhaust for bypass air and hot gases of combustion. The core exhaust includes a convergent-divergent nozzle. The convergent-divergent nozzle is formed from a plurality of flaps and seals. The exhaust system comprises a third air duct for a third stream of air. The third stream of air is selectively exhausted from the third duct through a secondary nozzle or divergent slots in the convergent-divergent nozzle, or both depending upon the flight mode. A diverter valve is positioned in the third stream duct to selectively control the flow of third stream air through the secondary nozzle, the divergent slots and combinations thereof.
    Type: Application
    Filed: May 7, 2013
    Publication date: November 27, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: General Electric Company
  • Patent number: 8887487
    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: November 18, 2014
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • Patent number: 8875518
    Abstract: The present invention relates to a jet engine nacelle (1) comprising an aft section (5) having an internal structure (9) intended to surround an aft portion of an engine compartment and to define, with an exhaust nozzle (6), a calibrated outlet section for the ventilation of the engine compartment by way of spacing means arranged in the outlet section, characterized in that the spacing means are divided into rigid spacing means (11) designed to provide a constant spacing and into compensating means (13) designed so as to be able to adapt to the relative movements of the jet engine with respect to the nacelle.
    Type: Grant
    Filed: June 19, 2008
    Date of Patent: November 4, 2014
    Assignee: Aircelle
    Inventor: Thierry Jacques Albert Le Docte