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).
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Patent number: 11027317Abstract: 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: GrantFiled: September 19, 2019Date of Patent: June 8, 2021Assignee: General Electric CompanyInventors: 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
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Patent number: 10569309Abstract: 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: GrantFiled: December 15, 2015Date of Patent: February 25, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: 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
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Publication number: 20200009620Abstract: 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: ApplicationFiled: September 19, 2019Publication date: January 9, 2020Inventors: 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
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Publication number: 20170165721Abstract: 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: ApplicationFiled: December 15, 2015Publication date: June 15, 2017Inventors: 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
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Patent number: 7976281Abstract: 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: GrantFiled: May 15, 2007Date of Patent: July 12, 2011Assignee: General Electric CompanyInventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
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Patent number: 7878763Abstract: 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: GrantFiled: May 15, 2007Date of Patent: February 1, 2011Assignee: General Electric CompanyInventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
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Patent number: 7607885Abstract: 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: GrantFiled: July 31, 2006Date of Patent: October 27, 2009Assignee: General Electric CompanyInventors: Blaine Charles Bosley, Sean Robert Keith, Jeffrey Allen Kress, Richard W. Albrecht, Jr.
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Publication number: 20090202337Abstract: 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: ApplicationFiled: July 31, 2006Publication date: August 13, 2009Inventors: Blaine Charles Bosley, Sean Robert Keith, Jeffrey Allen Kress, Richard W. Albrecht, JR.
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Publication number: 20080286109Abstract: 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: ApplicationFiled: May 15, 2007Publication date: November 20, 2008Inventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, JR.
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Publication number: 20080286106Abstract: 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: ApplicationFiled: May 15, 2007Publication date: November 20, 2008Inventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, JR.
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Patent number: 7306859Abstract: 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: GrantFiled: January 28, 2005Date of Patent: December 11, 2007Assignee: General Electric CompanyInventors: David John Wortman, Jonathan Paul Blank, Sean Robert Keith
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Patent number: 7198467Abstract: 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: GrantFiled: July 30, 2004Date of Patent: April 3, 2007Assignee: General Electric CompanyInventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
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Patent number: 7144215Abstract: 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: GrantFiled: July 30, 2004Date of Patent: December 5, 2006Assignee: General Electric CompanyInventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
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Patent number: 7131817Abstract: 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: GrantFiled: July 30, 2004Date of Patent: November 7, 2006Assignee: General Electric CompanyInventors: Sean Robert Keith, Michael Joseph Danowski, Leslie Eugene Leeke, Jr.
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Patent number: 6923616Abstract: 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: GrantFiled: September 2, 2003Date of Patent: August 2, 2005Assignee: General Electric CompanyInventors: Ronald Eugene McRae, Jr., Sean Robert Keith, Gulcharan Singh Brainch
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Patent number: 6715988Abstract: 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: GrantFiled: October 18, 2002Date of Patent: April 6, 2004Assignee: General Electric CompanyInventors: Leslie Eugene Leeke, Sean Robert Keith, Ronald Eugene Mc Rae, Jr., Richard William Albrecht, Jr., David Alan Frey
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Patent number: 6672832Abstract: 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: GrantFiled: January 7, 2002Date of Patent: January 6, 2004Assignee: General Electric CompanyInventors: Leslie Eugene Leeke, Sean Robert Keith, Lawrence Paul Timko
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Publication number: 20030223870Abstract: 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: ApplicationFiled: May 31, 2002Publication date: December 4, 2003Inventors: Sean Robert Keith, Thomas Edward DeMarche, John Robert Staker, Judd Dodge Tressler
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Patent number: 6652235Abstract: 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: GrantFiled: May 31, 2002Date of Patent: November 25, 2003Assignee: General Electric CompanyInventors: Sean Robert Keith, Thomas Edward DeMarche, John Robert Staker, Judd Dodge Tressler
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Patent number: 6609891Abstract: 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: GrantFiled: August 30, 2001Date of Patent: August 26, 2003Assignee: General Electric CompanyInventors: Leslie Eugene Leeke, Sean Robert Keith, Ronald Eugene Mc Rae, Jr., Lawrence Paul Timko, David Alan Frey