Having Turbine Patents (Class 60/805)
  • Patent number: 10934872
    Abstract: A support case for a turbomachine ring sector includes an annular body around a longitudinal axis of the case, and a downstream edge for attachment of the ring sector. The downstream edge extends from the body radially towards the inside of the case. The downstream edge extends circumferentially along a junction region between the body and a fixed vanes stage. The junction region includes a central portion and two lateral portions located on each side of the central portion, along a circumferential direction of the case with respect to its longitudinal axis. The central portion projects radially outwards from the case with respect to the lateral portions.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: March 2, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Paul Tableau, Sebastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Maurice Guy Judet, Lucien Henri Jacques Quennehen
  • Patent number: 10844723
    Abstract: Disclosed is a vane assembly fixed to a turbine casing of a turbine and configured to guide the flow of combustion gas having passed by a turbine blade airfoil. The vane assembly comprises a vane airfoil configured to guide the flow of the combustion gas, a platform portion combined with an end of the vane airfoil, carrier hook portions formed at respective periphery portions of the platform portion and provided with a thermal stress prevention slot on a surface facing the turbine casing, and a seal plate installed in the thermal stress prevention slot, thereby preventing a portion of compressed air produced by a compressor and supplied to the platform portion between the carrier hook portions from leaking out of the platform portion through the thermal stress prevention slot.
    Type: Grant
    Filed: August 28, 2018
    Date of Patent: November 24, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Jin Woo Song
  • Patent number: 10794239
    Abstract: A rotary manifold for a rotor assembly of a cohesion-type drive includes a manifold body extending along a drive axis for rotation thereabout, a first ductwork internal the body for fluid communication with a plurality of first chambers of the drive, and a second ductwork internal the body for fluid communication with a plurality of second chambers of the drive. The second ductwork is in fluid isolation of the first ductwork.
    Type: Grant
    Filed: November 23, 2017
    Date of Patent: October 6, 2020
    Assignee: MCGUIRE AERO PROPULSION SOLUTIONS INC.
    Inventor: Daniel Matthew McGuire
  • Patent number: 10690054
    Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.
    Type: Grant
    Filed: April 22, 2019
    Date of Patent: June 23, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Michael E. McCune, Marc J. Muldoon
  • Patent number: 10519973
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 29, 2016
    Date of Patent: December 31, 2019
    Assignee: General Electric Company
    Inventors: Sunil Rajagopal, Michael James Dutka
  • Patent number: 10519972
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 29, 2016
    Date of Patent: December 31, 2019
    Assignee: General Electric Company
    Inventors: Paul G. Deivernois, Sunil Rajagopal
  • Patent number: 10487748
    Abstract: A gas turbine engine has a fan driven by a fan drive turbine through a gear reduction, a low pressure compressor and a high pressure compressor. The high pressure compressor is driven by a high pressure turbine and the low pressure compressor is driven by a low pressure compressor drive turbine through a mechanical transmission that increases the speed of the low pressure compressor relative to the low pressure compressor drive turbine. A tap taps air from the low pressure compressor and delivers the tapped air as cooling air to the high pressure turbine.
    Type: Grant
    Filed: December 5, 2016
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventor: Steven W. Trinks
  • Patent number: 10465710
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 28, 2016
    Date of Patent: November 5, 2019
    Assignee: General Electric Company
    Inventors: Moorthi Subramaniyan, Sagar Kamble
  • Patent number: 10465709
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 28, 2016
    Date of Patent: November 5, 2019
    Assignee: General Electric Company
    Inventors: Moorthi Subramaniyan, Sagar Kamble
  • Patent number: 10443610
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: October 15, 2019
    Assignee: General Electric Company
    Inventors: Matthew John McKeever, Alexander Regan Fannin
  • Patent number: 10443618
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: October 15, 2019
    Assignee: General Electric Company
    Inventors: Marc Edward Blohm, Sunil Rajagopal
  • Patent number: 10443611
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 27, 2016
    Date of Patent: October 15, 2019
    Assignee: General Electric Company
    Inventors: John David Stampfli, Nandakumar Aladahalli Rangaswamy
  • Patent number: 10443492
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 27, 2016
    Date of Patent: October 15, 2019
    Assignee: General Electric Company
    Inventors: Francesco Soranna, Nandakumar Aladahalli Rangaswamy
  • Patent number: 10436215
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: October 8, 2019
    Assignee: General Electric Company
    Inventors: Marc Edward Blohm, John Nathan Ihme
  • Patent number: 10436214
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: October 8, 2019
    Assignee: General Electric Company
    Inventors: Lakshmanan Valliappan, Ramesh Kempanna Babu, Sagar Kamble
  • Patent number: 10422343
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: September 24, 2019
    Assignee: General Electric Company
    Inventors: Marc Edward Blohm, John David Dyer
  • Patent number: 10422342
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: September 24, 2019
    Assignee: General Electric Company
    Inventors: Michael Healy, Michael James Dutka
  • Patent number: 10415585
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: John David Stampfli, John David Dyer
  • Patent number: 10415594
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: Paul G. Deivernois, John N. Ihme
  • Patent number: 10415463
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: Marc Edward Blohm, Brendon James Leary
  • Patent number: 10415595
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: Lakshmanan Valliappan, Ramesh Kempanna Babu
  • Patent number: 10415464
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: John David Stampfli, John David Dyer
  • Patent number: 10415593
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: Paul G. Deivernois, Dwight E. Davidson
  • Patent number: 10408059
    Abstract: The invention concerns an assembly for the stator of a compressor of an axial-flow turbine engine, such as a low-pressure compressor of the turbojet engine also known as a booster. The assembly comprises: a first annular array of first vanes of the stator extending radially in the axial flow; and a second annular row of second vanes of the stator, with controlled orientation, also known as variable-pitch vanes or VSV. In addition, the assembly comprises an external monobloc shroud on which the first vanes and the second vanes are mounted in a pivoting manner.
    Type: Grant
    Filed: August 21, 2017
    Date of Patent: September 10, 2019
    Assignee: Safran Aero Boosters SA
    Inventor: Morgan Vyvey
  • Patent number: 10393144
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: August 27, 2019
    Assignee: General Electric Company
    Inventors: Paul G. Deivernois, Alexander Regan Fannin
  • Patent number: 10371244
    Abstract: A gear includes a multiple of gear teeth that extend from an outer portion of a rim about an axis and an inner portion of the rim about the axis, the inner portion of the rim additive manufactured.
    Type: Grant
    Filed: April 9, 2015
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventor: Michael E McCune
  • Patent number: 10267228
    Abstract: A gas turbine engine includes a fan section and a compressor section. The compressor section includes both a first compressor section and a second compressor section. A turbine section includes at least one turbine and driving the second compressor section and a fan drive turbine driving at least a gear arrangement to drive the fan section. A power ratio is provided by the combination of the first compressor section and the second compressor section, with the power ratio being provided by a first power input to the first compressor section and a second power input to the second compressor section, the power ratio being equal to, or greater than, about 1.0 and less than, or equal to, about 1.4.
    Type: Grant
    Filed: February 11, 2014
    Date of Patent: April 23, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz
  • Patent number: 10054008
    Abstract: A gearbox assembly includes a housing structure, a shear bracket that connects the housing structure to a hanger to hold the housing structure relative to a turbomachine, and a thermal spray layer between the shear bracket and the housing structure.
    Type: Grant
    Filed: February 9, 2015
    Date of Patent: August 21, 2018
    Assignee: United Technologies Corporation
    Inventors: Lakshminarayan S. Bettagere, Keven Van Duyn, Mark R. Sondeen, Jonathan F. Zimmitti
  • Patent number: 10036257
    Abstract: An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.
    Type: Grant
    Filed: February 18, 2015
    Date of Patent: July 31, 2018
    Assignee: United Technologies Corporation
    Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
  • Patent number: 9932834
    Abstract: A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: April 3, 2018
    Assignee: United Technologies Corporation
    Inventors: Matthew A. Hough, Jeffrey S. Beattie
  • Patent number: 9915159
    Abstract: A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: March 13, 2018
    Assignee: General Electric Company
    Inventors: Benjamin Scott Huizenga, Christopher Charles Glynn, Darrell Glenn Senile, Robert Alan Frederick, Michael Todd Radwanski, Michael Ray Tuertscher, Greg Scott Phelps
  • Patent number: 9885482
    Abstract: A method of making an aero-derivative gas turbine engine (100) is provided. A combustor outer casing (68) is removed from an existing aero gas turbine engine (60). An annular combustor (84) is removed from the existing aero gas turbine engine. A first row of turbine vanes (38) is removed from the existing aero gas turbine engine. A can annular combustor assembly (122) is installed within the existing aero gas turbine engine. The can annular combustor assembly is configured to accelerate and orient combustion gasses directly onto a first row of turbine blades of the existing aero gas turbine engine. A can annular combustor assembly outer casing (108) is installed to produce the aero-derivative gas turbine engine (100). The can annular combustor assembly is installed within an axial span (85) of the existing aero gas turbine engine vacated by the annular combustor and the first row of turbine vanes.
    Type: Grant
    Filed: November 18, 2016
    Date of Patent: February 6, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventor: David J. Wiebe
  • Patent number: 9766019
    Abstract: A gas turbine engine recuperator recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust passages having an arcuate profile in a plane perpendicular to a central axis of the recuperator to reduce a swirl of the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and providing fluid flow communication between an air inlet and an air outlet, design to sealingly respective plenum of the gas turbine engine.
    Type: Grant
    Filed: February 28, 2011
    Date of Patent: September 19, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, David Menheere, Daniel Alecu, Darius Jehangir Karanjia, Daniel Van Den Ende
  • Patent number: 9399917
    Abstract: An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil is a fan blade for a gas turbine engine. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.
    Type: Grant
    Filed: October 7, 2015
    Date of Patent: July 26, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Byron R. Monzon, Ling Liu, Linda S. Li, Darryl Whitlow, Barry M. Ford
  • Patent number: 9394828
    Abstract: A gas turbine engine recuperator including a plurality of independent arcuate segments, each segment having an inlet connection member designed to sealingly engage a plenum in fluid flow communication with the compressor discharge, and an outlet connection member designed to sealingly engage a plenum containing the combustor. One of the inlet and outlet connection members is a rigid member forming a rigid connection to the respective plenum, and the other of the inlet and outlet connection members includes a flexible member and forms a floating connection to the respective plenum, the floating connection allowing relative movement between the segment and a remainder of the gas turbine engine.
    Type: Grant
    Filed: February 28, 2011
    Date of Patent: July 19, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, David Menheere, Daniel Alecu
  • Patent number: 9395122
    Abstract: A gas turbine engine recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust inlet having a smaller cross-sectional area than that of the exhaust outlet, and a cross sectional area of each exhaust passage progressively increasing from the exhaust inlet to the exhaust outlet such as to diffuse the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and provide fluid flow communication between an air inlet and an air outlet designed to sealingly engage respective plenums of the gas turbine engine.
    Type: Grant
    Filed: February 28, 2011
    Date of Patent: July 19, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, David Menheere, Daniel Alecu, Darius Jehangir Karanjia
  • Patent number: 9309774
    Abstract: An arrangement is provided for delivering gases from a plurality of combustors of a can-annular gas turbine combustion engine to a first row of turbine blades including a first row of turbine blades. The arrangement includes a gas path cylinder, a cone and an integrated exit piece (IEP) for each combustor. Each IEP comprises an inlet chamber for receiving a gas flow from a respective combustor, and includes a connection segment. The IEPs are connected together to define an annular chamber extending circumferentially and concentric to an engine longitudinal axis, for delivering the gas flow to the first row of blades. A radiused joint extends radially inward from a radially outer side of the inlet chamber to an outer boundary of the annular chamber, and a flared fillet extends radially inward from a radially inner side of the inlet chamber to an inner boundary of the annular chamber.
    Type: Grant
    Filed: January 15, 2014
    Date of Patent: April 12, 2016
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Richard C. Charron, David A. Little, Gary D. Snyder
  • Patent number: 9279340
    Abstract: The present application provides a cooling system for a gas turbine. The cooling system may include a source of CO2, a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a number of stator blades, and a rotor blade cooling system positioned about a rotor shaft of the gas turbine and in communication with the source of CO2 and a number of rotor blades. A first portion of a flow of CO2 may flow through the stator blade cooling system and returns to the source of CO2 in a first closed loop and a second portion of the flow of CO2 may flow through the rotor blade cooling system and returns to the source of CO2 in a second closed loop.
    Type: Grant
    Filed: May 9, 2013
    Date of Patent: March 8, 2016
    Assignee: General Electric Company
    Inventors: Mahendhra Muthuramalingam, Ashok Kumar Anand, Veerappan Muthaiah
  • Patent number: 9127555
    Abstract: A method for balancing a rotating assembly of a gas turbine engine includes removing a stator vane from a section of the gas turbine engine. Removing the stator vane provides access to a rotating assembly of the gas turbine engine. The method further includes at least one of adding, removing, and repositioning a weight with respect to the rotating assembly via access to the rotating assembly provided by removing the stator vane.
    Type: Grant
    Filed: December 21, 2010
    Date of Patent: September 8, 2015
    Assignee: Solar Turbines Incorporated
    Inventors: Cory P. Muscat, James A. Barber
  • Patent number: 9085053
    Abstract: The tip portion of a blade of a gas turbine is repaired in-situ in the gas turbine without removing the blade from the turbine rotor disk. To facilitate the in-situ repair of the tip portion of the turbine blades, one or more access holes may be provided in the turbine shroud or blade outer air seal circumscribing the plurality of turbine blades extending radially outward from the turbine rotor dick.
    Type: Grant
    Filed: December 22, 2009
    Date of Patent: July 21, 2015
    Assignee: United Technologies Corporation
    Inventors: Susan M. Tholen, Paul M. Lutjen
  • Patent number: 9080464
    Abstract: A gas turbine includes a combustor chamber that houses a combustor unit configured to include a combustor that burns fuel to generate combustion gas for rotating a rotor, a turbine unit chamber that houses a turbine-unit rotor blade and a disk that rotate upon reception of the combustion gas, a combustor casing that forms the combustor chamber, and a casing that is configured to include the combustor casing in which a divided portion on a surface orthogonal to a rotation axis of the rotor is not formed in the combustor casing, but is formed in a portion on a downstream side of flow of the combustion gas lower than the combustor casing.
    Type: Grant
    Filed: December 24, 2008
    Date of Patent: July 14, 2015
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Kenichi Arase, Eigo Katou, Masato Takeuchi
  • Patent number: 9038394
    Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface feature for interfacing with an adjacent transition duct. The turbine system further includes a convolution seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct.
    Type: Grant
    Filed: April 30, 2012
    Date of Patent: May 26, 2015
    Assignee: General Electric Company
    Inventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
  • Publication number: 20150128612
    Abstract: A gas or steam turbine is disclosed herein. The turbine may include a throat area formed between adjacent buckets. The turbine also may include a variable throat device associated with at least one of the adjacent buckets. The variable throat device may be configured to vary the throat area between the adjacent buckets for improved part load performance.
    Type: Application
    Filed: November 14, 2013
    Publication date: May 14, 2015
    Applicant: General Electric Company
    Inventors: Moorthi Subramaniyan, Jeyamani Doss, Subodh Diwakar Deodhar
  • Publication number: 20150128605
    Abstract: A gas turbine engine is disclosed with a bypass flow path having a bypass nozzle positioned downstream of a fan; a core flow path having a compressor, a combustor, a turbine and an exhaust nozzle; an auxiliary duct fluidly connecting the core flow path and the bypass flow path downstream of the turbine; and a control valve operably connected to the auxiliary duct to control fluid flow from the core flow path into the bypass flow path.
    Type: Application
    Filed: March 6, 2014
    Publication date: May 14, 2015
    Inventor: Dmitriy B. Sidelkovskly
  • Publication number: 20150128613
    Abstract: The object of the present invention is to reduce galling that occurs at a tapered thread according to generation of excessive pressure on a tip end side of the tapered thread. In order to attain the above-mentioned object, a tapered thread according to the present invention is characterized in that it is a tapered thread comprising a taper-shaped external thread threadedly engaged with a taper-shaped internal thread formed in a member that is to be fastened, a tapered thread center hole is formed in a bottom surface of the external thread, and a depth of the tapered thread center hole is not more than a half of an axial length of the external thread.
    Type: Application
    Filed: November 6, 2014
    Publication date: May 14, 2015
    Inventors: Tatsuya FUKUDA, Yasuyuki WATANABE
  • Publication number: 20150128611
    Abstract: A stacked wheel assembly for a rotor of a rotary machine includes a plurality of stacked wheels for rotation about a common axis and forming a portion of the rotor. Also included is a tie bolt passing through aligned bolt holes of the plurality of stacked wheels for retaining the plurality of stacked wheels in axially stacked relation, the tie bolt extending out of a forward end of a forward wheel of the plurality of stacked wheels and out of an aft end of an aft wheel of the plurality of stacked wheels. Further included is a rotor component disposed adjacent the aft end of the aft wheel. Yet further included is a nut mounted within a forward face of the rotor component, the nut configured to be in threaded engagement with the tie bolt to exert a clamping force on the plurality of stacked wheels.
    Type: Application
    Filed: November 11, 2013
    Publication date: May 14, 2015
    Applicant: General Electric Company
    Inventor: Rajesh Kumar
  • Publication number: 20150107266
    Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.
    Type: Application
    Filed: October 23, 2013
    Publication date: April 23, 2015
    Applicant: General Electric Company
    Inventors: Ross James Gustafson, Srinivasa Govardhan Jayana, Spencer Aaron Kareff, Dipesh Dinesh Nanda
  • Publication number: 20150107265
    Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using an airfoil profile and/or an endwall contour including at least one of a pressure side bump, a pressure side leading edge bump, or a suction side trough. In particular, by including two endwall bumps on the pressure side and a trough on the suction side combined with a particular airfoil profile, performance can be further improved.
    Type: Application
    Filed: October 23, 2013
    Publication date: April 23, 2015
    Applicant: General Electric Company
    Inventors: Paul Kendall Smith, Harish Bommanakatte, Anthony Louis Giglio, Jason Douglas Herzlinger, Jacob Charles Perry, Alexander Stein
  • Publication number: 20150101346
    Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define a first inner surface of the first end piece. The root portion defines a first projection and an opposing second projection of the first end piece. The first projection has an outer profile adapted to project into a first lateral recess of the attachment slot. The second projection has an outer profile adapted to project into a second lateral recess of the attachment slot. A second end piece fits between the first inner surface of the first end piece and a sidewall portion of the attachment slot and includes a platform portion and a root portion. A borehole extends continuously through the first end piece and the second end piece. A fastener configured to engage with a sidewall portion of the attachment slot extends through the borehole.
    Type: Application
    Filed: October 16, 2013
    Publication date: April 16, 2015
    Applicant: General Electric Company
    Inventors: Gregory Thomas Foster, Michael James Healy
  • Publication number: 20150101350
    Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece configured to fit into a space between the platforms of adjacent rotor blades. The first end piece comprises an outer surface and an inner surface. The outer surface has a profile that is adapted to project into the attachment slot. A second end piece is configured to fit into a space between the platforms. The second end piece comprises an outer surface and an inner surface. The outer surface has a profile that is adapted to project into the attachment slot. The inner surfaces of the first and second end pieces generally face each other. The first end piece and the second end piece are bonded together either directly or via a spacer block that is inserted between the inner surfaces.
    Type: Application
    Filed: October 16, 2013
    Publication date: April 16, 2015
    Applicant: General Electric Company
    Inventors: Michael James Healy, Brian Denver Potter