Interdigitated, Oppositely Extending, Coaxial, Axially Spaced Blade Rows Patents (Class 415/65)
  • Patent number: 11873822
    Abstract: A centrifugal compressor includes a rotary shaft having a plurality of impellers and a casing having an intermediate discharge port. The casing has a plurality of diaphragms, an external casing, a return flow path that guides a flow direction of a working fluid to an inner side in a radial direction, and an intermediate scroll that guides part of the working fluid discharged from the impeller in an intermediate stage to the intermediate discharge port. The intermediate scroll has a scroll flow path formed on a second side in the axial direction with respect to the return flow path, and an introduction portion connecting the return flow path and the scroll flow path, and an outer flow path forming surface of the scroll flow path is formed by a casing inner peripheral surface facing an inner side of the external casing in the radial direction.
    Type: Grant
    Filed: January 30, 2023
    Date of Patent: January 16, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Akihiro Nakaniwa, Jo Masutani, Shinichiro Tokuyama, Yoshiaki Shoji
  • Patent number: 11753939
    Abstract: A gas turbine engine is provided including a turbine section including a turbine having a plurality of first speed turbine rotor blades; a compressor section including a compressor having a plurality of first speed compressor rotor blades and a plurality of second speed compressor rotor blades; a gearbox; and a first spool rotatable by the plurality of first speed turbine rotor blades, the first spool coupled to the plurality of first speed compressor rotor blades for driving the plurality of first speed compressor rotor blades in a first direction and to the plurality of second speed compressor rotor blades across the gearbox for driving the plurality of second speed compressor rotor blades in a second direction, opposite the first direction.
    Type: Grant
    Filed: February 20, 2019
    Date of Patent: September 12, 2023
    Assignee: General Electric Company
    Inventors: Alan Roy Stuart, Tsuguji Nakano, Thomas Ory Moniz, Andrew Breeze-Stringfellow, Richard Schmidt
  • Patent number: 11231039
    Abstract: A contra-rotating compressor includes a first shaft assembly disposed in a housing, the first shaft assembly including an outer shaft, and a first plurality of impellers coupled to the outer shaft, wherein the outer shaft includes a final stage that includes a final impeller of the first plurality of impellers. The compressor further includes a second shaft assembly disposed in the housing and rotatable about the longitudinal axis that has a second plurality of impellers, a first pair of annular seals between the final stage and an inner surface of the housing that are configured to permit relative rotation between the final stage and the housing, and a third annular seal positioned between the outer surface of the final stage and an inner surface of the second shaft assembly that is configured to permit contra-rotation between the final stage and the second shaft assembly.
    Type: Grant
    Filed: August 9, 2019
    Date of Patent: January 25, 2022
    Assignee: OneSubsea IP UK Limited
    Inventors: Hans Fredrik Kjellnes, â„«smund Valland, Joakim Almqvist, Thomas Bucher-Johannessen, Marius Askevold
  • Patent number: 11215123
    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including a circumferential array of fan blades, a low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area, and a fan duct annulus area outboard of the low pressure compressor section inlet, and a fan drive turbine section. The fan drive turbine section includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is equal to or greater than 0.35, and is less than 0.55.
    Type: Grant
    Filed: October 5, 2020
    Date of Patent: January 4, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 11098592
    Abstract: A turbomachine includes a spool; and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along an axial direction and rotatable with one another. The turbomachine also includes a first support member, the first plurality of turbine rotor blades coupled to the spool through the first support member; a second support member, the second plurality of turbine rotor blades supported by the second support member; and a bearing assembly including a first bearing and a second bearing, the first bearing and the second bearing each rotatably supporting the second support member and each being supported by the turbine center frame.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: August 24, 2021
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal
  • Patent number: 10823001
    Abstract: A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt, Bhaskar Nanda Mondal, Ramana Reddy Kollam
  • Patent number: 10823114
    Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section, a gearbox proximate to the turbine section, and a driveshaft. The turbine section includes a first rotating component interdigitated with a second rotating component along the longitudinal direction. The first rotating component includes an outer shroud defining a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction and one or more connecting airfoils coupling the outer shroud to a radially extended rotor. The second rotating component includes an inner shroud defining a plurality of inner shroud airfoils extended outward of the inner shroud along the radial direction. The second rotating component is coupled to an input shaft connected to an input gear of the gearbox.
    Type: Grant
    Filed: August 8, 2019
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Jeffrey Donald Clements, Darek Tomasz Zatorski, Alan Roy Stuart
  • Patent number: 10781717
    Abstract: A turbomachine includes a turbine frame and a turbine, the turbine including a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a first support member assembly including a first support member supporting the first plurality of turbine rotor blades; a second support member assembly including a second support member supporting the second plurality of turbine rotor blades; a frame support member assembly including a frame support member coupled to and extending from the turbine frame; and a bearing assembly including a first bearing and a second bearing. The first bearing is positioned between the first support member and the second support member, and the second bearing is positioned between the frame support member and one of the first support member or the second support member.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: September 22, 2020
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt
  • Patent number: 10260367
    Abstract: A power transmission for a turbine or a compressor has a housing, a first shaft rotatably mounted so as to be rotatable in one direction in the housing, a barrel rotatably mounted so as to be rotatable in a direction opposite to that of the first shaft within the housing, a first plurality of blades affixed to the first shaft and extending radially outwardly therefrom, and a second plurality of blades affixed to the barrel and extending inwardly therefrom. Each blade of the second plurality of blades is interposed between adjacent blades of the first plurality of blades. A second shaft is mounted exterior of the housing so as to drive the barrel in rotation.
    Type: Grant
    Filed: August 16, 2017
    Date of Patent: April 16, 2019
    Inventor: Jay Haskin
  • Patent number: 10077660
    Abstract: A turbine engine assembly is provided. The assembly includes a low-pressure turbine assembly including a first turbine section configured to rotate in a first rotational direction at a first rotational speed, and a second turbine section configured to rotate in a second rotational direction at a second rotational speed. The second rotational direction is opposite the first rotational direction and the second rotational speed is lower than the first rotational speed. The assembly also includes a first drive shaft coupled to the first turbine section, and a fan assembly including a first fan section coupled to the first drive shaft such that the first fan section rotates in the first rotational direction at the first rotational speed, and a second fan section coupled to the second turbine section such that the second fan section rotates in the second rotational direction at the second rotational speed.
    Type: Grant
    Filed: July 17, 2015
    Date of Patent: September 18, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Douglas Carl Hofer, Narendra Digamber Joshi, Michael Solomon Idelchik
  • Patent number: 9739205
    Abstract: A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a combustor section located axially upstream of the drive turbine, and a speed change mechanism located axially downstream of the combustor section and axially upstream of the drive turbine. An output of the speed change mechanism connects to the fan.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: August 22, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 9624834
    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: Grant
    Filed: January 8, 2015
    Date of Patent: April 18, 2017
    Assignee: United Technologies Corporation
    Inventors: David A. Topol, Bruce L. Morin
  • Patent number: 9494044
    Abstract: The present invention is a turbojet design that integrates power generation into the turbojet itself, rather than use separate generators attached to the turbojet for power generation. By integrating the power generation within the jet engine, the weight of the overall system is significantly reduced, increasing system efficiency. Also, by integrating the power generating elements of the system within the air flow of the jet engine, the present invention can use the heat generated by the power generating elements (which is simply expelled waste heat in current designs) to increase the engine performance.
    Type: Grant
    Filed: April 2, 2014
    Date of Patent: November 15, 2016
    Assignee: The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Kurt J Kloesel
  • Patent number: 9476427
    Abstract: A counter-rotating wet gas compressor for deployment and operation on the sea floor is described. The compressor has alternating rows of impellers, with each successive row of impellers being mounted a central hub or to an outer sleeve. According to some embodiments, no static diffusers are positioned between the alternating counter-rotating rows of impellers such that the design is structurally robust, compact and capable of compressing fluids that contain significant portions of liquid phase.
    Type: Grant
    Filed: November 28, 2012
    Date of Patent: October 25, 2016
    Assignee: FRAMO ENGINEERING AS
    Inventors: Bernt Helge Torkildsen, Per Gunnar Vikre, Hans Frederik Kjellnes
  • Publication number: 20150060691
    Abstract: A semiconductor process pump configured to mitigate losses in pump speed during operation. The semiconductor process pump may include a housing having an inlet port for receiving gas molecules therethrough, wherein a forward-most terminus of the inlet port defines an inlet face, one or more working surfaces disposed within the housing, and a mounting flange disposed on an exterior of the housing for facilitating attachment of the pump to a gas enclosure, wherein a forward-most terminus of the mounting flange defines a flange face. The flange face may be offset from the inlet face rearwardly along the housing by a distance d. Thus, when the semiconductor process pump is mounted to a wall of a gas enclosure, the housing may extend into the wall and the inlet face may be disposed within or immediately adjacent the interior of the gas enclosure.
    Type: Application
    Filed: August 29, 2013
    Publication date: March 5, 2015
    Applicant: Varian Semiconductor Equipment Associates, Inc.
    Inventor: Steven C. Borichevsky
  • Publication number: 20140369809
    Abstract: A turbomolecular pump has a rotor element in a housing. The rotor element is arranged on a rotor shaft. The rotor shaft is supported by two bearing elements in the housing. The bearing element on the high-vacuum side is constructed as a roller bearing. In order to guarantee a pressure in the area of the bearing element that is acceptable for the bearing element constructed as a roller bearing, the bearing element is arranged in a chamber. The chamber is connected via a channel to the pre-vacuum area and sealed relative to the high-vacuum area by a gasket.
    Type: Application
    Filed: January 8, 2013
    Publication date: December 18, 2014
    Applicant: Oerlikon Leybold Vacuum Gmbh
    Inventors: Christian Beyer, Holger Dietz, Gerhard Wilhelm Walter
  • Publication number: 20140348634
    Abstract: The invention relates to an adapter for vacuum pumps, characterized in that it comprises an annular inlet flange (15) intended to be coupled to an outlet orifice of a chamber and an outlet coupling (16) comprising at least two cylindrical outlet through-housings (21) and forming an at least partial pump casing for the case (4) of a respective turbomolecular vacuum pump (3), said turbomolecular vacuum pumps (3) being intended to be received in a respective cylindrical outlet housing (21). The invention also relates to a pumping device, characterized in that it comprises an adapter for vacuum pumps (2) as described hereinabove and at least two turbomolecular vacuum pumps (3) housed at least partially in a respective cylindrical outlet housing (21).
    Type: Application
    Filed: December 20, 2012
    Publication date: November 27, 2014
    Applicant: PFEIFFER VACUUM GMBH
    Inventors: Thibaut Bourrilhon, Rainer Mathes, Nicolas Varennes
  • Publication number: 20140294565
    Abstract: Provided is a vacuum pump in which the flexing of a rotating cylinder made of a fiber-reinforced resin can be reduced as much as possible to sufficiently reduce the gap between the rotating cylinder and a fixed cylinder, and exhaust performance can thereby be improved to great effect. A vacuum pump comprising a thread groove pump portion equipped with a fixed cylinder portion (2) having a spiraling thread groove portion (1) provided in an internal peripheral surface, and a rotating cylinder portion (3) placed inside the fixed cylinder portion (2), the thread groove pump portion exhausting through a spiraling exhaust flow channel due to the rotating cylinder portion (3) being caused to rotate, and the exhaust flow channel being formed from the thread groove portion (1) and an external peripheral surface of the rotating cylinder portion (3).
    Type: Application
    Filed: November 28, 2012
    Publication date: October 2, 2014
    Applicants: ARISAWA MFG. CO., LTD., EDWARDS JAPAN LIMITED
    Inventors: Takashi Kabasawa, Yuichi Kawai, Masaki Hori, Takahiro Iiyoshi
  • Publication number: 20140255153
    Abstract: Each of the stationary blade portions is formed by two or more divided stationary blade portions, and has abutting ends in both circumferential ends, the stationary blade portion is formed by abutting the abutting ends of the divided stationary blade portions with each other. Each of the divided stationary blade portions has an outer circumferential rim nipped by the spacers, an inner circumferential rim positioned in a front end on the inner circumferential side of the stationary blade portion, and a plurality of stator blades formed between the outer circumferential rim and the inner circumferential rim. In abutting ends of the outer circumferential rims where the plurality of divided stationary blade portions is abutted with each other, at least one of the outer circumferential rims has a cutout forming a gap together with the other facing outer circumferential rim.
    Type: Application
    Filed: March 5, 2014
    Publication date: September 11, 2014
    Applicant: Shimadzu Corporation
    Inventor: Shin SUMIMOTO
  • Patent number: 8814494
    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: Grant
    Filed: March 11, 2014
    Date of Patent: August 26, 2014
    Assignee: United Technologies Corporation
    Inventors: William G. Sheridan, Karl L. Hasel
  • Patent number: 8807916
    Abstract: A gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0.
    Type: Grant
    Filed: March 11, 2014
    Date of Patent: August 19, 2014
    Assignee: United Technologies Corporation
    Inventors: William G. Sheridan, Karl L. Hasel
  • Publication number: 20140205432
    Abstract: A rotary vacuum pump includes a first set of pumping stages having rotor discs with a first diameter and a second set of pumping stages having rotor discs with a second different diameter and further comprising an intermediate pumping stage that is particularly adapted for matching the change in the diameter of the pump rotor discs. According to the invention, the intermediate pumping stage comprises a rotor disc having an outer portion in the radial direction that is axially tapered from its inner diameter to its outer diameter and a corresponding stator stage including a spacer ring that is axially tapered from its periphery toward its center.
    Type: Application
    Filed: December 19, 2013
    Publication date: July 24, 2014
    Inventor: Enrico Emelli
  • Patent number: 8753065
    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 axis and a speed reduction device in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps.
    Type: Grant
    Filed: February 4, 2013
    Date of Patent: June 17, 2014
    Assignee: United Technologies Corporation
    Inventors: William G. Sheridan, Karl L. Hasel
  • Patent number: 8678743
    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 axis and a speed reduction device in communication with the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A fan blade tip speed of the fan is less than 1400 fps.
    Type: Grant
    Filed: February 4, 2013
    Date of Patent: March 25, 2014
    Assignee: United Technologies Corporation
    Inventors: William G. Sheridan, Karl L. Hasel
  • Patent number: 8667773
    Abstract: A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: March 11, 2014
    Assignee: United Technologies Corporation
    Inventor: Peter D. Silkowski
  • Patent number: 8272833
    Abstract: A turboprop having at least one propeller formed by a set of variable pitch blades. Each blade is swivel-mounted on a rotary support and carries a gearwheel meshing with an actuator annulus rotating on the rotary support and coupled to a control annulus via an epicyclic mechanism.
    Type: Grant
    Filed: January 24, 2008
    Date of Patent: September 25, 2012
    Assignee: SNECMA
    Inventor: Francois Gallet
  • Patent number: 8191352
    Abstract: A counter-rotatable low pressure turbine includes counter-rotatable outer and inner drum rotors. The outer drum rotor is connected to a sole shaft for transmitting torque and power out of the low pressure turbine. Low pressure outer drum turbine blade rows extend radially inwardly from an outer shell of the outer drum rotor. Low pressure inner drum turbine blade rows extend radially outwardly from the low pressure inner drum rotor. The outer drum turbine blade rows are interdigitated with the inner drum turbine blade rows. The drum rotors are geared together through an epicyclic gearbox for transmitting all the torque and power produced by the drum rotors to the shaft. The gearbox may be located aft of the drum rotors. A differential thrust bearing is disposed between the drum rotors. A single stage fan section of an engine is connected to the turbine by the shaft.
    Type: Grant
    Filed: December 19, 2008
    Date of Patent: June 5, 2012
    Assignee: General Electric Company
    Inventor: Jan Christopher Schilling
  • Publication number: 20120051883
    Abstract: Method, system and axial multistage expander including a casing and a plurality of stages. A stage includes a stator part connected to the casing and having plural statoric airfoils, and a rotor part configured to rotate relative to the stator part and having plural rotoric airfoils. The axial multistage expander also includes a support mechanism connected to the casing and configured to rotatably support the rotor part. Rotoric airfoils of at least one stage of the plurality of stages are configured to rotate with a speed different from rotoric airfoils of the other stages. The stator part, the rotor part and the support mechanism of the plurality of stages are provided inside the casing.
    Type: Application
    Filed: July 18, 2011
    Publication date: March 1, 2012
    Inventors: Michele D'Ercole, Simone Billi, Stefania Della Gatta
  • Patent number: 8100630
    Abstract: A fluid flow machine includes at least one casing 1 and at least one rotor drum 3 rotatable about a machine axis 4, with stator vanes 8 and rotor blades 7 being arranged in an annulus duct 2 formed between the casing 1 and the rotor drum 3 The annulus duct 2 is divided into an outer annular duct 5 and an inner annular duct 6 by at least one annular flow divider 11, in each of which rotor blades 7 and stator vanes 8 are arranged Outer rotor blades 7a, which are arranged in the outer annular duct 5, are rotatable at a different speed than the inner rotor blades 7b, which are arranged in the inner annular duct 6.
    Type: Grant
    Filed: March 11, 2009
    Date of Patent: January 24, 2012
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • Publication number: 20110280710
    Abstract: Herein described is a system for injecting and extracting gas for a fluid rotating machine of the type comprising at least one stator case, one first stage which receives the gas flowing into the machine, one final stage, downstream of which the gas is discharged from the machine, and one or more intermediate stages arranged between the first stage and the final stage. Each stage is made up of a single centrifugal rotor and a fixed ducting, associated to such centrifugal rotor and made on the single stator case. The system comprises at least one first worm screw for extracting gas from the machine and at least one second worm screw for injecting gas into the machine. Both worm screws for extracting gas and for injecting gas are operatively connected to at least one stage of the machine.
    Type: Application
    Filed: January 22, 2010
    Publication date: November 17, 2011
    Inventor: Gabriele Mariotti
  • Patent number: 8037686
    Abstract: The invention is for a continuous-combustion, closed-cycle, gas turbine engine with a regenerator and a displacer. It has embodiments that remove heater and cooler interior volumes during gas compression, which enable it to scale well to very large sizes. Low combustion temperatures insure very low emissions. The displacer levitated by an integral gas bearing and small clearance seal and given oscillatory translational motion by electromagnetic forces operates without surface wear. The turbine blades, subjected only to warm gases, are durable and inexpensive. Thus, this engine has a very long, continuous, maintenance-free service life. This gas turbine engine also operates without back work allowing high efficiency for both low and rated output. Pressurized encapsulation permits use of low-cost ceramics for high temperature components. The invention includes a unique monolithic ceramic heater, a compact high-capacity regenerator and a constant-power gas turbine.
    Type: Grant
    Filed: July 3, 2007
    Date of Patent: October 18, 2011
    Inventor: George Lasker
  • Patent number: 8016544
    Abstract: The vertical windmill includes a rotatable wind wheel column mounted to a base. The column includes a plurality of hollow wheel hubs stacked vertically atop each other. Each wheel hub includes a plurality of radiating mounting arms equidistantly spaced around the axis of the wheel hub such that the arms of an adjacent hub are angularly offset with respect to the other. A plurality of mounting assemblies is disposed on each of the mounting arms for mounting an array of wing blades. Each alternate stacked wheel hub and mounting arms together forms a wind wheel with vertically oriented wing blades mounted between upper and lower spaced arms such that the top wheel is interconnected with the lower wheel at a height less than the height of the blades. Each array of blades may freely rotate or be positively rotated to orient the blades for optimum usage of wind power in rotating the column.
    Type: Grant
    Filed: March 8, 2010
    Date of Patent: September 13, 2011
    Inventor: Huy T. Nguyen
  • Patent number: 7950220
    Abstract: A counter-rotating blade stage in lieu of a stator stage may compensate for relatively low rotational speed of a gas turbine engine spool. A first spool may have at least two compressor blade stage and at least two turbine blade stage. A combustor is located between the at least two compressor blade stage and the at least two turbine blade stage along a core flowpath. The at least two counter-rotating compressor blade stage is interspersed with the first spool at least two compressor blade stage. A transmission couples the at least two additional compressor blade stage to the first spool for counter-rotation about the engine axis.
    Type: Grant
    Filed: June 19, 2006
    Date of Patent: May 31, 2011
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, John P. Nikkanen
  • Publication number: 20110116907
    Abstract: An axial turbine includes a plurality of stages each comprising a plurality of stationary blades arranged in a row along the turbine circumferential direction and a plurality of moving blades in a row parallel to the stationary blades, each of the moving blade being disposed downstream of a respective one of the corresponding stationary blade in a flow direction of a working fluid so as to be opposed to the corresponding stationary blade. Herein, each of the stationary blades is formed so that the intersection line between the outer peripheral portion of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer peripheral portion of the stationary blade and that is parallel to the turbine central axis.
    Type: Application
    Filed: January 27, 2011
    Publication date: May 19, 2011
    Applicant: HITACHI, LTD.
    Inventors: Shigeki SENOO, Tetsuaki KIMURA
  • Patent number: 7850417
    Abstract: In a contra rotating propeller engine propeller blade assemblies are provided which rotate in opposite directions as a result of association with an epicyclic gear assembly acting as a differential gearbox. A carrier is provided to drive one propeller blade assembly. Actuators are provided to cause pitch angle adjustment of the respective propeller blades of the assemblies. These actuators, are secured upon a stationary structure and act through actuator rods and appropriate mechanisms to cause such angular pitch adjustment. Rotational de-couplers are provided to rotationally isolate the actuators while an actuator rod part acts across the assemblies and a rotational de-coupler to de-couple contra rotation between the assemblies while still allowing axial displacement for adjustment of the other propeller blade assembly.
    Type: Grant
    Filed: June 22, 2007
    Date of Patent: December 14, 2010
    Assignee: Rolls-Royce PLC
    Inventor: David M. Beaven
  • Publication number: 20090226298
    Abstract: An apparatus comprising a tandem pump which includes first and second pump sections driven by a rotation shaft, and a housing defining a pump receiving portion including a first pump chamber receiving the first pump section and a second pump chamber receiving the second pump section. The first and second pump chambers are separated by a partition. The partition is positioned by the housing at least in the axial direction of the rotation shaft.
    Type: Application
    Filed: March 9, 2009
    Publication date: September 10, 2009
    Inventors: Keigo Kajiyama, Toshihiro Koizumi, Norihiro Saita
  • Publication number: 20080219832
    Abstract: A shroud for supporting a variable vane in a compressor section for a gas turbine engine includes a pair of components which are secured together by a threaded fastener extending into a blind hole in one of the two components. Additional material forms on the component which includes the blind hole extends beyond a pivot axis for the vane such that there is an increased length of engagement between the threaded fastener and the blind hole. The blind hole eliminates the need for multiple nuts and reduces the radial height of the shroud to save additional weight.
    Type: Application
    Filed: March 6, 2007
    Publication date: September 11, 2008
    Inventors: Daniel W. Major, Edward Torres, Joseph C. Burge
  • Publication number: 20080148707
    Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor disposed downstream from the high-pressure compressor, and a high-pressure turbine coupled to the high-pressure compressor using a shaft, counter-rotating booster compressor coupled to the core gas turbine engine, the counter-rotating booster compressor comprising a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction, a single stage fan assembly coupled to the first rotor section, a drive shaft coupled between the low-pressure turbine and the fan assembly, and a gearbox coupled between the drive shaft and the second rotor section such that the low-pressure turbine drives the gearbox and such that the gearbox drives the second rotor section. A method of assembling the above turbofan engine assembly is also described herein.
    Type: Application
    Filed: December 21, 2006
    Publication date: June 26, 2008
    Inventor: Jan Christopher Schilling
  • Patent number: 7334981
    Abstract: A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor that includes a first plurality of rows of turbine blades configured to rotate in a first rotational direction, providing a low-pressure turbine outer rotor that includes a second plurality of rows of turbine blades configured to rotate in a rotational direction that is opposite the first rotational direction, and coupling a support structure between the outer rotor and a turbine mid-frame such that the support structure supports a forward end of the outer rotor, and wherein the support structure includes a first portion that has a first coefficient of thermal expansion and a second portion that has a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion.
    Type: Grant
    Filed: October 29, 2004
    Date of Patent: February 26, 2008
    Assignee: General Electric Company
    Inventors: Thomas Ory Moniz, Robert Joseph Orlando
  • Patent number: 7290386
    Abstract: A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor that includes a first plurality of turbine blade rows configured to rotate in a first direction, and rotatably coupling a low-pressure turbine outer rotor to the inner rotor, wherein the outer rotor includes a second plurality of turbine blade rows that are configured to rotate in a second direction that is opposite the first rotational direction of the inner rotor and such that at least one of the second plurality of turbine blade rows is coupled axially forward of the first plurality of turbine blade rows.
    Type: Grant
    Filed: October 29, 2004
    Date of Patent: November 6, 2007
    Assignee: General Electric Company
    Inventors: Robert Joseph Orlando, Thomas Ory Moniz
  • Patent number: 7195446
    Abstract: A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor configured to rotate in a first direction, providing a low-pressure turbine outer rotor configured to rotate in a second direction that is opposite the first rotational direction, and coupling at least one foil bearing to at least one of the inner and outer rotors to facilitate improving clearance control between a first rotating component and at least one of a second rotating component and a non-rotating component.
    Type: Grant
    Filed: October 29, 2004
    Date of Patent: March 27, 2007
    Assignee: General Electric Company
    Inventors: Jorge Francisco Seda, Thomas Ory Moniz, Lawrence Butler
  • Patent number: 7186073
    Abstract: A method for assembling a gas turbine engine includes providing a low-pressure turbine inner rotor that includes at least a first pair of adjacent rows of turbine blades that are configured to rotate in a first direction providing a low-pressure turbine outer rotor that includes a forward end, an aft end, and at least one row of turbine blades that is rotatably coupled between the first pair of inner rotor turbine blades, wherein the at least one row of outer rotor turbine blades is configured to rotate in a second direction that is opposite the first direction, and coupling a support assembly between the first pair of inner rotor turbine blades such that the support assembly supports the outer rotor forward end.
    Type: Grant
    Filed: October 29, 2004
    Date of Patent: March 6, 2007
    Assignee: General Electric Company
    Inventors: Robert Joseph Orlando, Thomas Ory Moniz
  • Patent number: 7052230
    Abstract: A pump assembly including a pump, a pump frame and a motor, the pump including a pumping member which is mounted in a pump housing, relative rotation of the pumping member with respect to the pump housing causing pumping of fluid, and the motor including a rotor and a stator, operation of the motor causing rotation of the pumping member relative to the pump housing, wherein one or two of the stator, pumping member and pump housing is fixed relative to the pump frame, a resilient support part being provided between the pump frame and each of the other two or one of the stator, pumping member, and the pump housing, the resilient support part or parts permitting movement of the stator, pumping member or pump housing with respect to the pump frame.
    Type: Grant
    Filed: May 6, 2004
    Date of Patent: May 30, 2006
    Assignee: Automotive Motion Technology Limited
    Inventors: Robert William Beaven, Michael John Werson
  • Patent number: 6960059
    Abstract: A blower having a plurality of impellers is described. The blower has two driving devices and two impellers respectively mounted on the two driving devices. The blades of the two impellers, which are radially or axially disposed, are overlapped so as to enhance the heat-dissipating efficiency of the blower.
    Type: Grant
    Filed: January 23, 2003
    Date of Patent: November 1, 2005
    Assignee: Delta Electronics, Inc.
    Inventors: Shun-Chen Chang, Kuo-Cheng Lin, Wen-Shi Huang
  • Patent number: 6854954
    Abstract: A method for assembling a power system is provided. The method includes coupling a first turbine and second turbine together with a coupling that extends between a first rotor of a first turbine and a second rotor of the second turbine, and such that the first turbine has fluid flow along a first flow path, and the second turbine has fluid flow along a second flow path. The method further includes fixedly coupling an outer wall to the first turbine that directs fluid flow from the first flow path towards the second flow path.
    Type: Grant
    Filed: March 3, 2003
    Date of Patent: February 15, 2005
    Assignee: General Electric Company
    Inventors: Douglas Carl Hofer, Daniel Mark Brown, Scott William Blackwell, Norman Douglas Lathrop, Edward John Sharrow
  • Patent number: 6684626
    Abstract: An aircraft gas turbine engine includes a low pressure turbine having a low pressure turbine flowpath and counter rotatable low pressure inner and outer shaft rotors having inner and outer shafts, respectively. The low pressure inner and outer shaft rotors include low pressure first and second turbine blade rows disposed across the turbine flowpath and drivingly connected to first and second fan blade rows by low pressure inner and outer shafts, respectively. At least one of the low pressure first and second turbine blade rows is interdigitated with an adjacent pair of one of the turbine blade rows. At least one row of non-rotatable low pressure vanes is disposed across the low pressure turbine flowpath between a non interdigitated adjacent pair of one of the turbine blade rows.
    Type: Grant
    Filed: July 30, 2002
    Date of Patent: February 3, 2004
    Assignee: General Electric Company
    Inventors: Robert Joseph Orlando, Thomas Ory Moniz
  • Patent number: 5443590
    Abstract: A rotatable turbine frame includes annular outer and inner bands having a plurality of circumferentially spaced apart struts extending therebetween. An annular drive shaft is fixedly joined to the inner band for transmitting output torque therefrom, and the struts are backwardly radially inclined relative to the direction of rotation of the frame so that gas flow between the struts tends to straighten the inclined struts to effect a compressive load component therein.
    Type: Grant
    Filed: June 18, 1993
    Date of Patent: August 22, 1995
    Assignee: General Electric Company
    Inventors: John J. Ciokajlo, Ambrose A. Hauser, Samuel H. Davison
  • Patent number: 5307622
    Abstract: A counterrotating turbine support assembly includes outer and inner rotors having respective outer and inner blades disposed in an outer casing. A mid-frame is disposed forwardly of the rotors and fixedly joined to the outer casing. A rear frame is disposed axially aft of the rotors and is fixedly joined to the outer casing. A forward support shaft is joined at one end to a forward end of the outer rotor and is rotatably supported at an inner end to the mid-frame by a forward bearing. An aft support shaft is joined at one end to an aft end of the outer rotor and is rotatably supported at an inner end to the rear frame by an aft bearing. An intermediate support shaft is fixedly joined at one end to the inner rotor and is rotatably supported at an inner end to the mid-frame by an intermediate bearing.
    Type: Grant
    Filed: August 2, 1993
    Date of Patent: May 3, 1994
    Assignee: General Electric Company
    Inventors: John J. Ciokajlo, Ambrose A. Hauser
  • Patent number: 4951461
    Abstract: A coupling arrangement for supporting a power turbine in a gas turbine engine. The power turbine section comprises a stator structure, first and second rotors, and first and second bearings. The first and second rotors are coaxially disposed about a longitudinal axis of the stator. An annular gas flowpath is coaxially positioned between the first and second rotors. Annular arrays of turbine blades are coupled to the first and second rotors and extend into the flowpath so that a gas stream flowing through the flowpath reacts with the turbine blades causing the rotors to counterrotate. The first bearings are interposed between the first rotor and the stator structure to rotatably secure the first rotor to the stator structure. The second bearings are interposed between the second rotor and the first rotor to rotatably secure the second rotor to the first rotor.
    Type: Grant
    Filed: March 20, 1989
    Date of Patent: August 28, 1990
    Assignee: General Electric Company
    Inventor: Lawrence Butler
  • Patent number: 4907944
    Abstract: An improved blade mounting arrangement for a gas turbine engine with a turbine and an annular flowpath therethrough is disclosed. The improvement comprises a one-piece outer casing and a one-piece inner casing bounding the flowpath. The outer casing has a plurality of circumferential recesses disposed therein with each of the recesses having first and second axially opposite circumferential slots. A plurality of first turbine blades, each with axially facing tangs on a mounting platform, mate with the slots in the outer casing recess. The inner casing has a plurality of recesses disposed therein, each of the recesses including a forward circumferential slot and concentric aft radially outer and radially inner circumferential slots. A plurality of second turbine blades, each with forward and aft axially facing tangs on a mounting platform, mate with respective ones of forward slot and radially outer slot in the inner casing recess.
    Type: Grant
    Filed: October 1, 1984
    Date of Patent: March 13, 1990
    Assignee: General Electric Company
    Inventors: Gerard P. Kroger, Robert A. Peck, Ralph A. Kirkpatrick