Runner Supported Portion Engages Shaft Transmission Train (e.g., Peripheral Gear Drive, Etc.) Patents (Class 415/124.1)
  • Patent number: 11002194
    Abstract: The present disclosure relates to a geared gas turbine engine for an aircraft. Example embodiments include a gas turbine engine for an aircraft including: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox that receives an input from the core shaft to drive the fan at a lower rotational speed than the core shaft, the gearbox having a gear ratio of around 3.4 or higher, wherein the gas turbine engine is configured such that a jet velocity ratio between a first jet velocity exiting from a bypass duct of the engine and a second jet velocity exiting from an exhaust nozzle of the engine core is within a range from around 0.75 to around 0.82.
    Type: Grant
    Filed: June 18, 2019
    Date of Patent: May 11, 2021
    Assignee: ROLLS-ROYCE plc
    Inventor: Craig W Bemment
  • Patent number: 10787971
    Abstract: A gas turbine engine includes a non-rotatable flexible coupling having Stiffnesses A, B, C, D and E, which are defined herein, and at least ratio of a frame lateral stiffness FLS as follows: FLS/Stiffness A in a range of about 6.0 to about 25.0, FLS/Stiffness B in a range of about 10.0 to about 40.0, FLS/Stiffness C in a range of about 1.5 to about 7.0, FLS/Stiffness D in a range of about 0.25 to about 0.50, or FLS/Stiffness E in a range of about 6.0 to about 40.0.
    Type: Grant
    Filed: October 1, 2018
    Date of Patent: September 29, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: William G. Sheridan, John R. Otto
  • Patent number: 10781798
    Abstract: A nacelle component for a nacelle of a wind turbine, comprising a mainframe module and a power electronics module. The mainframe module and the power electronics module in each case have a length greater than a width. In the assembled state of the nacelle component, the mainframe module is oriented with its longitudinal axis parallel to a vertical plane which extends through the axis of a rotor shaft. The longitudinal axis of the power electronics module intersects the vertical plane which extends through the axis of the rotor shaft. A method for mounting such a nacelle component is also disclosed.
    Type: Grant
    Filed: May 18, 2018
    Date of Patent: September 22, 2020
    Assignee: Senvion GmbH
    Inventor: Alf Trede
  • Patent number: 10641182
    Abstract: A geared gas turbine engine for an aircraft includes: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; and a gearbox that receives an input from the core shaft to drive the fan at a lower rotational speed than the core shaft, the gearbox having a gear ratio of around 3.6 or lower, wherein the gas turbine engine is configured such that a jet velocity ratio between a first jet velocity exiting from a bypass duct of the engine and a second jet velocity exiting from an exhaust nozzle of the engine core is within a range from around 1 to around 1.3 at cruise conditions.
    Type: Grant
    Filed: June 11, 2019
    Date of Patent: May 5, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Craig W Bemment
  • Patent number: 10563591
    Abstract: A power extraction system for a gas turbine engine may comprise a high spool transmission, a low spool transmission, and an accessory gearbox. The accessory gearbox may comprise a starter-generator, a low spool starter-generator gear, a high spool gear, and a clutch configured to selectively engage and disengage the low spool starter-generator gear and the high spool gear. The low spool starter-generator gear may be configured to transfer torque between the starter-generator and the low spool transmission for accessory power generation. The high spool gear may be configured to transfer torque to the high spool transmission for engine starting. The clutch may be controlled by a variable transmission and may allow accessories to be driven by the low spool after starting.
    Type: Grant
    Filed: January 17, 2018
    Date of Patent: February 18, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Marc J Muldoon
  • Patent number: 10473084
    Abstract: Device for generating energy making use of the current of a river (2), with a self-floating paddlewheel (13) and an electric generator set (17) that is coupled to the paddlewheel (13), whereby the device (1) is provided with an immersed housing (3) with an open bottom (4) in which the paddlewheel (13) is rotatably affixed and whereby there is a unit (10) to control the flow of the river (2) at the level of the paddlewheel (13), whereby the speed of the generator set (17) is kept constant by controlling the water level (9) in the housing (3) by placing its internal space (7) under pressure and/or by controlling the aforementioned unit (10).
    Type: Grant
    Filed: June 11, 2015
    Date of Patent: November 12, 2019
    Inventor: Boudewijn Gabriel Van Rompay
  • Patent number: 10465769
    Abstract: An integral transmission for a transmission turbomachine has two gearwheels which are in mesh with a large wheel and which are each connected to a shaft that can be connected to an input and/or output unit. A housing, in which the gearwheels or the shafts connected thereto are supported and at least two partial housing units which can be connected by a main joint that extends through the support region of at least one gearwheel in mesh at least indirectly with the large wheel or of the shaft connected to the gearwheel. Accordingly, one of the two partial housing units is formed from at least three housing parts including a central housing part, which is assigned to the large wheel, and two side housing parts. The central housing part can be connected to an individual side housing part by a joint aligned at an angle to the main joint.
    Type: Grant
    Filed: November 20, 2015
    Date of Patent: November 5, 2019
    Assignee: Voith Patent GmbH
    Inventors: Arne Zimmermann, Joachim Rasch, Sabine Germann
  • Patent number: 10358982
    Abstract: A fan drive gear system for a turbofan engine includes a geared architecture and a gear controller supporting the geared architecture and controlling rotation of the geared architecture relative a static structure.
    Type: Grant
    Filed: July 3, 2014
    Date of Patent: July 23, 2019
    Assignee: United Technologies Corporation
    Inventors: John R. Otto, James B. Coffin
  • Patent number: 10352250
    Abstract: An equipment support including at least one attachment including an output shaft, an input gear wheel, the input gear wheel being both rotated by the motor shaft at a main speed and also connected to the output shaft of the attachment in order to rotate it at a determined output speed, an input shaft, rotated by the input gear wheel at a determined input speed, and a reducer with magnetic gears, arranged between the input shaft and the output shaft, such that the input speed is different from the output speed.
    Type: Grant
    Filed: October 15, 2015
    Date of Patent: July 16, 2019
    Assignee: SAFRAN TRANSMISSION SYSTEMS
    Inventors: Maxence Guillemont, Stephane Prunera-Usach, Julien Viel, Antoine Barbe
  • Patent number: 10309407
    Abstract: This compressor system is provided with: a driving machine having a rotary-driven first output shaft and a second shaft that is rotary driven so as to reach the same speed as the first output shaft; a working-fluid-compressing first compressor to which the rotation of the first output shaft is transmitted; a working-fluid-compressing second compressor to which the rotation of the second output shaft is transmitted; a variable-speed step-up gear for increasing the speed of the first output shaft and transmitting the increased speed to the first compressor, said step-up gear being capable of varying the increased speed; and a constant-speed step-up gear for increasing the speed of the second output shaft and transmitting the increased speed to the second compressor, said step-up gear keeping the increased speed constant.
    Type: Grant
    Filed: September 18, 2014
    Date of Patent: June 4, 2019
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Masahiro Kobayashi, Yasushi Mori, Takeshi Hataya
  • Patent number: 10119548
    Abstract: What is described is an aircraft engine with a compressor device and with a fan device. In the area of a compressor shaft, the compressor device is connected via an epicyclic gear to a fan shaft. A planetary web is operatively connected via bearing devices to the planetary gears. A ring gear is coupled with the fan shaft and a sun gear of the epicyclic gear is coupled with the compressor shaft, while the planetary carrier is held at the housing side in a torque-proof manner. The ring gear is connected via a flexible connection device to the fan shaft and/or the planetary carrier is connected via a flexible connection device to the housing. In the area of the connection device, movements between the ring gear and the planetary gears and/or between the planetary carrier and the housing can be at least approximately compensated in the radial and the axial direction.
    Type: Grant
    Filed: September 24, 2015
    Date of Patent: November 6, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Gideon Venter
  • Patent number: 10100803
    Abstract: An ocean wave-crest powered electrical generator comprises a buoyant vessel anchored to the sea floor by mooring chains. The vessel defines a substantial opening at the bow leading to a paddle wheel such that ocean wave crests flow past the paddle wheel while passing through the generator thereby capturing the power of the continuous wave crests passing through the bow opening. The paddle wheel transforms energy from the breaking wave crests into kinetic energy that in turn activates an electric power generator. The wave crest electrical generator is permanently moored near the beach and allowed to rise and fall with the tide thus allowing for a continuous flow of ocean waves to be converted into power. Pumped storage provides a sustained flow of energy that is easy to regulate and this can be accomplished in combination with “energetic marinas” by constructing a reservoir on top of a near-by cliff, hill or tall building.
    Type: Grant
    Filed: September 7, 2016
    Date of Patent: October 16, 2018
    Inventor: Alfredo Alvarado
  • Patent number: 10012149
    Abstract: A gearbox mounting link between a gas turbine engine structure and a gearbox mounting location comprises an engine attachment piece rotatably secured to the gas turbine engine structure. The engine attachment piece comprises first and second plates extending in parallel planes and separated by a gap having a gap width. A gearbox attachment piece is situated between the parallel plates, and is secured to the gearbox. A breakable primary retention fastener extends snugly through the parallel plates and the gearbox attachment piece, thereby rigidly retaining the gearbox with respect to the gas turbine engine in two degrees of freedom so long as the breakable primary retention fastener remains intact. A durable secondary retention fastener extending snugly through the parallel plates, and extends with clearance through the gearbox attachment piece via an oversized fastener passage, thereby constraining the gearbox attachment piece in the event that the breakable primary retention fastener breaks.
    Type: Grant
    Filed: March 14, 2016
    Date of Patent: July 3, 2018
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Yiwei Jiang, Michael R. Blewett
  • Publication number: 20150125258
    Abstract: An aircraft (1) having a rotary wing (2) and turboshaft engines (11, 12, 13) for driving said rotary wing (2). The aircraft then includes two main engines (11, 12) that are identical, each capable of operating at at least one specific rating associated with a main power (maxTOP, OEIcont), and a secondary engine (13) capable of operating at at least one specific rating by delivering secondary power (maxTOP?, OEIcont?) proportional to the corresponding main power (maxTOP, OEIcont) in application of a coefficient of proportionality (k) less than or equal to 0.5, said aircraft having a control system (20) for driving the rotary wing by causing each main engine (11, 12) to operate continuously throughout a flight, and by using the secondary engine (13) as a supplement during at least one predetermined specific stage of flight.
    Type: Application
    Filed: November 20, 2013
    Publication date: May 7, 2015
    Applicant: EUROCOPTER
    Inventor: Bernard Certain
  • Publication number: 20150125259
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an engine axis with a plurality of fan blades rotatable about a fan blade axis. A geared architecture is in communication with the fan and driven by a turbine section. The fan rotates at a first speed and the turbine section rotates at a second speed different from the first speed and a fixed area fan nozzle in communication with the fan section.
    Type: Application
    Filed: February 24, 2014
    Publication date: May 7, 2015
    Applicant: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • Publication number: 20150107245
    Abstract: The invention relates to a device comprising at least one vertical pump (3) and at least one associated turbine (4) for transporting, over a level difference, a heat-transfer fluid brought to a high temperature, wherein the device further comprises a device for mechanically coupling the turbine (4) with the pump (3), comprising a gearbox (21) with a gimbal coupling (41) located on the turbine (4) side, allowing the mechanical energy produced by the turbine (4) to be reused to actuate the pump (3).
    Type: Application
    Filed: May 23, 2013
    Publication date: April 23, 2015
    Inventor: Alfred Dethier
  • Patent number: 8998570
    Abstract: Methods of moving a rotating device of a wind turbine during transportation or standstill are provided. The methods include securing at least one auxiliary device to a position and connecting the device to one or more shafts of the rotating device at transportation or standstill. The auxiliary device is able to store, generate and/or convert energy during transportation, transferring energy continuously from at least one auxiliary device to one or more shafts of the rotating device during transportation or standstill, and moving one or more shafts of the rotating device continuously or discontinuously from a position to another. Also provided is a nacelle for a wind turbine, an auxiliary device, a control system for controlling moving of a rotating device of a wind turbine nacelle during transportation of the nacelle and use thereof.
    Type: Grant
    Filed: June 14, 2011
    Date of Patent: April 7, 2015
    Assignee: Vestas Wind Systems A/S
    Inventors: Søren Damgaard, Arne Haarh, Nils Bjørn Jensen
  • Publication number: 20150071765
    Abstract: A supercharger transmission includes a first chamber having timing gears operatively disposed therein. A second chamber has transmission gears operatively disposed therein. An oil fill level is defined in the second chamber. A bearing retention wall is disposed between the first chamber and the second chamber. The bearing retention wall includes a return port to allow fluid communication between the first chamber and the second chamber. The return port is an aperture defined in the bearing retention wall below the oil fill level. The bearing retention wall also includes a crosstalk port to allow fluid communication between the first chamber and the second chamber. The crosstalk port is an aperture defined in the bearing retention wall above the oil fill level.
    Type: Application
    Filed: November 18, 2014
    Publication date: March 12, 2015
    Inventor: Jon P. Trudeau
  • Patent number: 8967944
    Abstract: A buffer air pump provides pressurized cooling air for cooling components of the gas turbine engine. The buffer air pump is supported on and/or within an accessory gearbox and draws bypass air in through an inlet manifold. An impeller supported within a scroll housing pressurizes the incoming bypass air and directs the pressurized air through passages to a component requiring cooling. The buffer air pump draws in relatively cool air from the bypass flow, pressurizes the air with the impeller and sends the air through conduits and passages within the gas turbine engine to the component that requires cooling such as a bearing assembly.
    Type: Grant
    Filed: August 29, 2011
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jorn A. Glahn, Brian D. Merry, Christopher M. Dye
  • Fan
    Patent number: 8961109
    Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.
    Type: Grant
    Filed: October 6, 2008
    Date of Patent: February 24, 2015
    Assignee: Bronswerk Heat Transfer B.V.
    Inventor: Augustinus Wilhelmus Maria Bertels
  • Patent number: 8961113
    Abstract: An example turbomachine geared architecture support assembly includes a subpart having a more compliant portion and a less compliant portion. The less compliant portion includes a stop that limits axial movement of a geared architecture within a turbomachine.
    Type: Grant
    Filed: April 7, 2014
    Date of Patent: February 24, 2015
    Assignee: United Technologies Corporation
    Inventor: John R. Otto
  • Publication number: 20140369818
    Abstract: 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 and a second race. A second bearing for rotation is within the first bearing including a first opening in registration with the first race such that lubricant may flow from the first race through the first opening into a first conduit. There is a rotating carrier for supporting at least one planetary gear. The second bearing extends from the rotating carrier about an axis. A first spray bar is disposed on the carrier. The second bearing has a second opening in registration with the second race and a second conduit for passing lubricant to the spray bar.
    Type: Application
    Filed: September 2, 2014
    Publication date: December 18, 2014
    Inventors: Michael E. McCune, William G. Sheridan, Lawrence E. Portlock
  • Publication number: 20140366548
    Abstract: A gas turbine engine comprises a fan, a compressor, a combustor, and a fan drive turbine rotor. The fan drive turbine drives the fan through a gear reduction. The gear reduction includes at least two double helical gears in meshed engagement. Each of the at least two double helical gears are disposed to rotate about respective axes, and each have a first plurality of gear teeth axially spaced from a second plurality of gear teeth by a spacer. Each of the first plurality of gear teeth has a first end facing the spacer and each of the second plurality of gear teeth has a first end facing the spacer. Each first end of the first plurality of gear teeth is circumferentially offset from each first end of the second plurality of gear teeth. A method is also disclosed.
    Type: Application
    Filed: August 28, 2014
    Publication date: December 18, 2014
    Inventor: Michael E. McCune
  • Patent number: 8899916
    Abstract: A fan drive gear system for a gas turbine engine includes a torque frame and a journal bearing. The torque frame has an arm that extends therefrom, the journal bearing is mounted on the arm. When the fan drive gear system is in an unloaded condition an outer circumferential surface of the journal bearing is disposed at an angle so that it is non-parallel with respect to an axis of the arm. When the fan drive gear system is in a loaded condition the outer circumferential surface is disposed substantially parallel to the axis of the arm. In another aspect, the journal bearing includes a main body, a first wing, and a second wing. The first and second wings extend from the main body and are asymmetric with respect to one another.
    Type: Grant
    Filed: August 30, 2011
    Date of Patent: December 2, 2014
    Assignee: United Technologies Corporation
    Inventors: Michael E. McCune, William G. Sheridan
  • Publication number: 20140314541
    Abstract: An example turbomachine thrust balancing system includes a member coupled in rotation with a turbine for transferring rotational power therefrom. A load carrying device rotatably supports the member. The load carrying device is configured to counteract substantially all of the thrust load generated by the turbine.
    Type: Application
    Filed: December 21, 2012
    Publication date: October 23, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: United Technologies Corporation
  • Publication number: 20140314546
    Abstract: A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of mounts connecting the gearbox to the case. Each of the mounts includes a linkage and a fuse joint. The linkage extends towards the case substantially in a first direction. The fuse joint is configured to substantially prevent movement between the gearbox and the case when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the gearbox and the case when the loading is greater than the threshold. The fuse joint of a first of the mounts has a different configuration than the fuse joint of a second of the mounts.
    Type: Application
    Filed: December 23, 2012
    Publication date: October 23, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: UNITED TECHNOLOGIES CORPORATION
  • Publication number: 20140301828
    Abstract: The described embodiments relate generally to improving performance characteristics of a low profile fan. More specifically configurations having sloped fan blade edges are disclosed. By applying a gradual slope to each of the fan blades, performance of the fan can be increased without risking contact or rubbing between the fan blades and a fan housing. In some embodiments, the sloped fan blades can be configured to prevent contact when bearings of the fan include a certain amount of tilt play.
    Type: Application
    Filed: May 3, 2013
    Publication date: October 9, 2014
    Applicant: Apple Inc.
    Inventors: Anthony Joseph Aiello, Jesse T. Dybenko, Richard A. Herms
  • Patent number: 8851830
    Abstract: A gear arrangement is disclosed herein. The gear arrangement includes a housing. The gear arrangement also includes a plurality of gears at least partially disposed in the housing and engaged with respect to one another. The gear arrangement also includes a support post mounted to the housing. The support post supports at least one of the gears. The support post has a first portion extending away from the housing and encircled by one of the gears. The support post also has a pin projecting away from the first portion. The first portion and the pin are eccentric to one another such that the first portion is centered on a first axis and the pin is centered on a second axis. The first and second axes are parallel to and spaced from one another. The gear arrangement also includes a plurality of pin apertures defined by the housing.
    Type: Grant
    Filed: October 8, 2010
    Date of Patent: October 7, 2014
    Assignee: Rolls-Royce Corporation
    Inventors: Neil Brink, Leonard L. Haas
  • Patent number: 8845275
    Abstract: A cranking pad assembly for a gearbox of a turbomachine including a cranking pad shaft rotatably secured in a gearbox housing and engageable with a gearbox drivetrain when urged inwardly into the gearbox housing. The cranking pad shaft includes an interface for a cranking tool. An interlock pin retains the cranking tool at the cranking pad shaft and a disconnect spring is operably connected to the gearbox housing to bias the cranking pad shaft outwardly from the gearbox housing.
    Type: Grant
    Filed: November 11, 2010
    Date of Patent: September 30, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Keith E. Short, Jeff A. Brown
  • Publication number: 20140286755
    Abstract: A turbine engine includes a fan section including a plurality of fan blades, a turbine section, and an epicyclic gear train coupled between the turbine section and the fan section for providing a speed reduction between turbine section and the fan section. The epicyclic gear train includes a plurality of intermediate gears. A carrier supports the plurality of intermediate gears. A sun gear meshes with the plurality of intermediate gears and a ring gear surrounding and meshing with the plurality of intermediate gears. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions of the ring gear have an outer circumferential surface opposite the teeth that provides a first thickness, a second thickness greater than the first thickness and axially inward from the first thickness, and a flange extending radially away from the axis. An epicyclic gear train for a turbine engine and method of designing an epicyclic gear train are also disclosed.
    Type: Application
    Filed: June 2, 2014
    Publication date: September 25, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael E. McCune, Lawrence E. Portlock
  • Patent number: 8827633
    Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A viscous damper is provided between the torque frame and the flex support at the location.
    Type: Grant
    Filed: September 25, 2013
    Date of Patent: September 9, 2014
    Assignee: United Technologies Corporation
    Inventors: James B. Coffin, John R. Otto
  • Patent number: 8827634
    Abstract: Provided is a gear-driven turbo compressor capable of increasing a natural frequency of a shaft by shortening the length of an overhang from a radial bearing to a shaft end, reducing an effort of replacing lubricant and an environmental burden by greatly reducing the amount of the lubricant, and reducing the necessity for maintenance by reducing a problem of the radial bearing caused by depleted materials of the lubricant. The gear-driven turbo compressor includes: a gas bearing 32 which is in communication with a compressed gas compressed by an impeller 16 and rotatably supports both ends of a pinion shaft 13; and an inner gas seal 34 which is positioned between the gas bearing and a thrust collar, maintains the gas bearing to be compressed by the compressed gas, and prevents intrusion of lubricant for gears due to the compressed gas.
    Type: Grant
    Filed: February 2, 2010
    Date of Patent: September 9, 2014
    Assignee: IHI Corporation
    Inventor: Naomichi Omori
  • Publication number: 20140241855
    Abstract: A run-of-the-river or ocean current turbine may comprise a hatch and a slanted block having protector ribs for directing water flow to a waterwheel. The hatch may be controlled by a plurality of Transgear™ gear assemblies for varying the amount of water flow to the waterwheel from extreme drought to flood conditions so that the waterwheel may turn at rated speeds and within a predetermined range. The Transgear gear assemblies may comprise an accumulator for accumulating a rough and a fine tuned waterwheel speed. The Transgear assemblies may comprise embodiments of power take-off switches for, for example, bi-directional or clockwise and counterclockwise waterwheel shaft rotation. The turbine may be aligned for top-feed, side-feed or bottom feed of water and may comprise a tail wing or first and second turbines facing in opposite directions to capture high and low tidal flow.
    Type: Application
    Filed: April 17, 2014
    Publication date: August 28, 2014
    Applicant: DIFFERENTIAL DYNAMICS CORPORATION
    Inventor: Kyung Soo Han
  • Patent number: 8814503
    Abstract: A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines a flexible support lateral stiffness with respect to the support lateral stiffness. An input to the gear system defines an input lateral stiffness with respect to the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.
    Type: Grant
    Filed: January 27, 2014
    Date of Patent: August 26, 2014
    Assignee: United Technologies Corporation
    Inventors: Michael E. McCune, Jason Husband
  • Patent number: 8814505
    Abstract: A mechanical arrangement for an engine having two propeller stages, including: a first epicyclic gear stage including a sun gear, a planet gear, a planet carrier and an annulus, wherein the sun gear is driven by a shaft of the engine, the planet carrier is stationary and thereby permits static structure to be located there through, and the annulus outputs torque and/or drive; a second epicyclic gear stage including a second sun gear, a second planet gear, a second planet carrier and a second annulus, wherein the second sun gear is driven by the annulus of the first epicyclic gear stage and is annular to accommodate the static structure, the second planet carrier includes the output to one of the propeller stages and the second annulus includes the output to the other of the propeller stages; wherein the static structure provides mounting for static components on one or both sides of each epicyclic gear stage.
    Type: Grant
    Filed: February 22, 2010
    Date of Patent: August 26, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Mark J. E. Bellis
  • Publication number: 20140234078
    Abstract: A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0.
    Type: Application
    Filed: March 11, 2014
    Publication date: August 21, 2014
    Applicant: United Technologies Corporation
    Inventors: William G. Sheridan, Karl L. Hasel
  • 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: 8801368
    Abstract: A gear transmission having at least one gear wheel stage, wherein at least one of the gear wheels is fastened coaxially on a hollow shaft that is rotatably mounted in a transmission housing via at least two shaft bearings. An outside-radial stage offset is formed on the hollow shaft as a seat for a broad rim gear wheel that approaches the plant radially on the inside.
    Type: Grant
    Filed: February 17, 2010
    Date of Patent: August 12, 2014
    Assignee: Robert Bosch GmbH
    Inventors: Klaus Noller, Gerhard Bauer, Guenter Berger
  • Publication number: 20140219775
    Abstract: Provided is a compression system including: at least one impeller; a gear train configured to the at least one impeller; a main drive shaft configured to drive the gear train; and a housing comprising an impeller container configured to house the at least one impeller and a gear train container configured to house the gear train.
    Type: Application
    Filed: July 29, 2013
    Publication date: August 7, 2014
    Applicant: SAMSUNG TECHWIN CO., LTD.
    Inventors: Bong-Gun SHIN, Jin-Soo LEE, Jong-Jae CHO, Seung-hoon LEE
  • Publication number: 20140205439
    Abstract: A gas turbine engine includes a housing including 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. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.
    Type: Application
    Filed: March 19, 2014
    Publication date: July 24, 2014
    Applicant: United Technologies Corporaiton
    Inventors: Brian D. Merry, Gabriel L. Suciu, Karl L. Hasel
  • Publication number: 20140205438
    Abstract: Please replace the abstract with the following rewritten abstract. No new matter has been added. An example gas turbine engine includes, among other things, a geared architecture rotatably coupling a fan drive shaft to an engine fan, the geared architecture having a speed reduction ratio that is greater than or equal to 2.4. The gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90.
    Type: Application
    Filed: January 21, 2013
    Publication date: July 24, 2014
    Applicant: United Technologies Corporation
    Inventor: Karl L. Hasel
  • Patent number: 8770922
    Abstract: A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.
    Type: Grant
    Filed: January 22, 2014
    Date of Patent: July 8, 2014
    Assignee: United Technologies Corporation
    Inventors: Michael E. McCune, Jason Husband
  • Publication number: 20140186158
    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: Application
    Filed: August 28, 2013
    Publication date: July 3, 2014
    Applicant: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, Karl L. Hasel
  • Publication number: 20140178180
    Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.
    Type: Application
    Filed: February 26, 2014
    Publication date: June 26, 2014
    Inventor: William G. Sheridan
  • Publication number: 20140161588
    Abstract: A centrifugal compressor, the capacity of which can be increased with keeping the diameter of the impeller at minimum, is provided. The centrifugal compressor includes: a drive gear (11); a drive shaft (3) protruding from one side of the drive gear (11) in a central axis direction of the drive gear (11); a no. 1 driven pinion gear (12) configured for rotation of the drive gear (11) to be transmitted thereto; a no. 1 driven pinion shaft (5) protruding from both sides of the no. 1 driven pinion gear (12) in a central axis direction of the no. 1 driven pinion gear (12); and a couple of first stage compressor sections (7a, 7b), each of which is provided in each end of the no. 1 driven pinion shaft (5) and is configured to compress fluid by rotation of the no. 1 driven pinion shaft (5).
    Type: Application
    Filed: January 30, 2012
    Publication date: June 12, 2014
    Applicant: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Hiroyuki Miyata, Naoto Yonemura
  • Publication number: 20140127000
    Abstract: A gas turbine AGB has a front lateral face, a rear lateral face opposite from the front lateral face, and a peripheral rim closing the box. At least one gear train is mounted in the AGB and is made up of a plurality of gearwheels meshing together, and designed to be coupled to a drive shaft for driving an accessory. The AGB further comprises, mounted between a central shaft carrying each gearwheel and the drive shaft, a decoupling unit for decoupling the accessory and constituted by a dog clutch having axial teeth co-operating with complementary teeth of the central shaft. The dog clutch includes internal fluting engaged with the corresponding external fluting of the drive shaft. The decoupling unit is controlled by an electric actuator acting on the movement of a plunger pin having one end co-operating with an outer helical groove in the dog clutch.
    Type: Application
    Filed: July 2, 2012
    Publication date: May 8, 2014
    Applicant: HISPANO SUIZA
    Inventors: Vincent Abousleiman, Romaric Fritz
  • Patent number: 8702373
    Abstract: The present disclosure is applicable to all gear trains using a journal bearing as a means of supporting gear shaft rotation. It is related in some embodiments to a system and method for supplying lubricant to the journal bearings of a gear-turbofan engine gear train when the fan rotor is subjected to a wind-milling condition in both directions, either clockwise or counter-clockwise.
    Type: Grant
    Filed: August 29, 2013
    Date of Patent: April 22, 2014
    Assignee: United Technologies Corporation
    Inventors: Christopher M. Valva, Brian P. Cigal
  • Publication number: 20140003915
    Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s?5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed.
    Type: Application
    Filed: September 3, 2013
    Publication date: January 2, 2014
    Applicant: United Technologies Corporation
    Inventors: David A. Topol, Bruce L. Morin
  • Publication number: 20130323015
    Abstract: A lubricant pump assembly for use with a power distribution unit for a vehicle, comprising a pump, a first rotating component, a second rotating component, and a lubricant. The pump has an inlet and an outlet. The inlet and the outlet are in fluid communication with a housing of the power distribution unit. The first rotating component is disposed in the housing of the power distribution unit. The second rotating component is disposed in the housing of the power distribution unit adjacent the first rotating component. The lubricant is disposed within the housing of the power distribution unit. The pump transfers a portion of the lubricant from the inlet to the outlet. The outlet is disposed adjacent the first rotating component and the second rotating component to dispose a portion of the lubricant therebetween.
    Type: Application
    Filed: May 10, 2013
    Publication date: December 5, 2013
    Inventor: Gregory DeWald
  • Publication number: 20130312419
    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. 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 supporting the shaft relative to the inlet case. The second bearing is arranged radially outward from the shaft.
    Type: Application
    Filed: May 29, 2013
    Publication date: November 28, 2013
    Inventors: Brian D. Merry, Gabriel L Suciu