Patents by Inventor Sean Robert Keith

Sean Robert Keith has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 10569309
    Abstract: A cleaning system and method uses a tank holding a fluid detergent and an equipment assembly formed from a plurality of discrete components joined together. One or more ultrasound transducers remove one or more deposits on the equipment assembly by generating and propagating high frequency ultrasound waves into the fluid detergent while the equipment assembly is in contact with the fluid detergent.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: February 25, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Nicole Tibbetts, Bernard Patrick Bewlay, Sean Robert Keith, Byron Andrew Pritchard, Jr., Brian Kalb, Evan Jarrett Dolley, Andrew James Jenkins, Alistair Searing, Stephen Francis Rutkowski
  • Publication number: 20200009620
    Abstract: A cleaning system and method uses a tank holding a fluid detergent and an equipment assembly formed from a plurality of discrete components joined together. One or more ultrasound transducers remove one or more deposits on the equipment assembly by generating and propagating high frequency ultrasound waves into the fluid detergent while the equipment assembly is in contact with the fluid detergent.
    Type: Application
    Filed: September 19, 2019
    Publication date: January 9, 2020
    Inventors: Nicole Tibbetts, Bernard Patrick Bewlay, Sean Robert Keith, Byron Andrew Pritchard, JR., Brian Kalb, Evan Jarrett Dolley, Andrew James Jenkins, Alistair Searing, Stephen Francis Rutkowski
  • Publication number: 20170165721
    Abstract: A cleaning system and method uses a tank holding a fluid detergent and an equipment assembly formed from a plurality of discrete components joined together. One or more ultrasound transducers remove one or more deposits on the equipment assembly by generating and propagating high frequency ultrasound waves into the fluid detergent while the equipment assembly is in contact with the fluid detergent.
    Type: Application
    Filed: December 15, 2015
    Publication date: June 15, 2017
    Inventors: Nicole Tibbetts, Bernard Patrick Bewlay, Sean Robert Keith, Byron Andrew Pritchard, JR., Brian Kalb, Evan Jarrett Dolley, Andrew James Jenkins, Alistair Searing, Stephen Francis Rutkowski
  • Patent number: 7976281
    Abstract: A rotor blade assembly includes a shank, an airfoil that is formed integrally with the shank, and a removable platform coupled between said shank and said airfoil via a friction fit. A method of assembling a gas turbine engine rotor blade assembly that includes a removable platform, and a gas turbine engine rotor assembly including the removable platform are also described herein.
    Type: Grant
    Filed: May 15, 2007
    Date of Patent: July 12, 2011
    Assignee: General Electric Company
    Inventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
  • Patent number: 7878763
    Abstract: A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and the second platform leg is configured to be retained by a second retainer coupled to a second adjacent rotor blade. A method of assembling a blade assembly that includes a removable platform, a rotor assembly including the removable platform, and a gas turbine engine assembly including the removable platform, are also described herein.
    Type: Grant
    Filed: May 15, 2007
    Date of Patent: February 1, 2011
    Assignee: General Electric Company
    Inventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
  • Patent number: 7607885
    Abstract: A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger.
    Type: Grant
    Filed: July 31, 2006
    Date of Patent: October 27, 2009
    Assignee: General Electric Company
    Inventors: Blaine Charles Bosley, Sean Robert Keith, Jeffrey Allen Kress, Richard W. Albrecht, Jr.
  • Publication number: 20090202337
    Abstract: A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger.
    Type: Application
    Filed: July 31, 2006
    Publication date: August 13, 2009
    Inventors: Blaine Charles Bosley, Sean Robert Keith, Jeffrey Allen Kress, Richard W. Albrecht, JR.
  • Publication number: 20080286106
    Abstract: A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and the second platform leg is configured to be retained by a second retainer coupled to a second adjacent rotor blade. A method of assembling a blade assembly that includes a removable platform, a rotor assembly including the removable platform, and a gas turbine engine assembly including the removable platform, are also described herein.
    Type: Application
    Filed: May 15, 2007
    Publication date: November 20, 2008
    Inventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, JR.
  • Publication number: 20080286109
    Abstract: A rotor blade assembly includes a shank, an airfoil that is formed integrally with the shank, and a removable platform coupled between said shank and said airfoil via a friction fit. A method of assembling a gas turbine engine rotor blade assembly that includes a removable platform, and a gas turbine engine rotor assembly including the removable platform are also described herein.
    Type: Application
    Filed: May 15, 2007
    Publication date: November 20, 2008
    Inventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, JR.
  • Patent number: 7306859
    Abstract: A coating process and TBC system suitable for protecting the surface of a component subjected to a hostile thermal environment. The TBC system has a first layer with a columnar microstructure, and a second layer on the first layer and with a microstructure characterized by irregular flattened grains. According to one aspect, the first layer is present and the second layer is not present on a first surface portion of the component, and the first and second layers are both present on a second surface portion of the component. According to another aspect, the first and second layers contain the same base ceramic compound.
    Type: Grant
    Filed: January 28, 2005
    Date of Patent: December 11, 2007
    Assignee: General Electric Company
    Inventors: David John Wortman, Jonathan Paul Blank, Sean Robert Keith
  • Patent number: 7198467
    Abstract: A method for fabricating a turbine rotor blade includes casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, and an airfoil, and forming a plurality of openings between the platform inner surface and the platform outer surface to facilitate cooling an exterior surface of the platform.
    Type: Grant
    Filed: July 30, 2004
    Date of Patent: April 3, 2007
    Assignee: General Electric Company
    Inventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
  • Patent number: 7144215
    Abstract: A method for fabricating a turbine rotor blade includes casting a turbine rotor blade including a dovetail, a platform having an outer surface, an inner surface, and a cast-in plenum defined between the outer surface and the inner surface, and an airfoil, and forming a plurality of openings between the platform inner surface and the platform outer surface to facilitate cooling an exterior surface of the platform.
    Type: Grant
    Filed: July 30, 2004
    Date of Patent: December 5, 2006
    Assignee: General Electric Company
    Inventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
  • Patent number: 7131817
    Abstract: A method for fabricating a rotor blade includes casting the turbine rotor blade to include a shank, and a platform having an upper surface and a lower surface, and coupling a first component to the rotor blade such that a first substantially hollow plenum is defined between the first component, the shank, and the platform lower surface.
    Type: Grant
    Filed: July 30, 2004
    Date of Patent: November 7, 2006
    Assignee: General Electric Company
    Inventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
  • Patent number: 6923616
    Abstract: A method facilitates fabricating a rotor assembly for a gas turbine engine. The method comprises providing a plurality of rotor blades that each include an airfoil, a dovetail, a shank, and a platform, wherein the platform extends between the shank and the airfoil, and wherein the dovetail extends outwardly from the shank, and forming a cooling circuit within a portion of the shank to supply cooling air to the rotor blade for supplying cooling air to the rotor blade for impingement cooling a portion of the rotor blade and for supplying cooling air to the rotor blade for purging a cavity defined downstream from the rotor blade.
    Type: Grant
    Filed: September 2, 2003
    Date of Patent: August 2, 2005
    Assignee: General Electric Company
    Inventors: Ronald Eugene McRae, Jr., Sean Robert Keith, Gulcharan Singh Brainch
  • Patent number: 6715988
    Abstract: A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The suction side wall has a selectively reduced thickness, which allows shortened trailing edge slots, improving trailing edge cooling.
    Type: Grant
    Filed: October 18, 2002
    Date of Patent: April 6, 2004
    Assignee: General Electric Company
    Inventors: Leslie Eugene Leeke, Sean Robert Keith, Ronald Eugene Mc Rae, Jr., Richard William Albrecht, Jr., David Alan Frey
  • Patent number: 6672832
    Abstract: A turbine includes a row of blades each having an integral airfoil, platform, and dovetail. Each platform has opposite first and second side edges corresponding with the opposite pressure and suction sides of the airfoil. The platform first side edge is radially higher than the platform second side edge continuously between opposite forward and aft edges of the platform. In this way, adjacent platforms define a down step therebetween for preventing obstruction of combustion gases flowable downstream thereover.
    Type: Grant
    Filed: January 7, 2002
    Date of Patent: January 6, 2004
    Assignee: General Electric Company
    Inventors: Leslie Eugene Leeke, Sean Robert Keith, Lawrence Paul Timko
  • Publication number: 20030223870
    Abstract: A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.
    Type: Application
    Filed: May 31, 2002
    Publication date: December 4, 2003
    Inventors: Sean Robert Keith, Thomas Edward DeMarche, John Robert Staker, Judd Dodge Tressler
  • Patent number: 6652235
    Abstract: A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.
    Type: Grant
    Filed: May 31, 2002
    Date of Patent: November 25, 2003
    Assignee: General Electric Company
    Inventors: Sean Robert Keith, Thomas Edward DeMarche, John Robert Staker, Judd Dodge Tressler
  • Patent number: 6609891
    Abstract: A hollow cooled turbine airfoil is provided having pressure and suction side walls and a plurality of trailing edge cooling passages that feed cooling air bleed slots at the trailing edge. The airfoil trailing edge is selectively thickened in the root portion so as to allow shortened trailing edge slots, thereby improving trailing edge cooling and reducing mechanical and thermal stresses.
    Type: Grant
    Filed: August 30, 2001
    Date of Patent: August 26, 2003
    Assignee: General Electric Company
    Inventors: Leslie Eugene Leeke, Sean Robert Keith, Ronald Eugene Mc Rae, Jr., Lawrence Paul Timko, David Alan Frey
  • Patent number: 6592330
    Abstract: A dovetail assembly including non-parallel relief faces that facilitates reduced pressure face brinelling in turbine engines. The assembly includes a plurality of rotor blades, each including a dovetail. Each dovetail includes at least a pair of blade tangs including blade relief faces. The dovetail assembly also includes a rotor disk including a plurality of dovetail slots, each sized to receive a dovetail. Each dovetail slot is defined by at least one pair of opposing disk tangs including disk relief faces. The disk relief faces are non-parallel to the blade relief faces when the dovetail is mounted in the dovetail slot.
    Type: Grant
    Filed: August 30, 2001
    Date of Patent: July 15, 2003
    Assignee: General Electric Company
    Inventors: Leslie Eugene Leeke, Sean Robert Keith, Ronald Eugene Mc Rae, Jr., Robert Ingram Ackerman, Richard William Albrecht, Jr.