Patents by Inventor Kenneth Damon Black

Kenneth Damon Black 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: 10215059
    Abstract: A system and method for active draft control through a combined cycle power plant (CCPP) can initiate a CCPP shutdown, activate the recirculated exhaust gas (REG) system for the turbomachine; measure a HRSG airflow through the HRSG; communicate the HRSG airflow to a controller configured to condition a control signal; and adjust a recirculated exhaust gas volume in accordance with the control signal.
    Type: Grant
    Filed: June 2, 2017
    Date of Patent: February 26, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Wolfgang Franz Dietrich Mohr, Kurt Rechsteiner, David Martin Johnson, Kenneth Damon Black
  • Publication number: 20180347407
    Abstract: A system and method for active draft control through a combined cycle power plant (CCPP) can initiate a CCPP shutdown, activate the recirculated exhaust gas (REG) system for the turbomachine; measure a HRSG airflow through the HRSG; communicate the HRSG airflow to a controller configured to condition a control signal; and adjust a recirculated exhaust gas volume in accordance with the control signal.
    Type: Application
    Filed: June 2, 2017
    Publication date: December 6, 2018
    Inventors: Wolfgang Franz Dietrich Mohr, Kurt Rechsteiner, David Martin Johnson, Kenneth Damon Black
  • Patent number: 10047633
    Abstract: Embodiments of the present disclosure include a bearing housing of a turbine, wherein the bearing housing is configured to support a shaft of the turbine, and the bearing housing comprises at least one bearing housing ear configured to transfer a load of the bearing housing to an inlet housing of the turbine through a horizontal center line of the bearing housing.
    Type: Grant
    Filed: May 14, 2015
    Date of Patent: August 14, 2018
    Assignees: General Electric Company, Exxon Mobil Upstream Research Company
    Inventors: Maruthi Prasad Manchikanti, Kenneth Damon Black, Donald Earl Floyd, II, Gregory Allan Crum
  • Patent number: 10024189
    Abstract: A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.
    Type: Grant
    Filed: August 15, 2016
    Date of Patent: July 17, 2018
    Assignee: General Electric Company
    Inventors: Radu Ioan Danescu, David Martin Johnson, Kenneth Damon Black, Christopher Paul Cox, Ozgur Bozkurt
  • Publication number: 20180195722
    Abstract: A diffuser assembly includes a casing at a compressor aft end; an inner barrel member radially inward of the casing; and an array of radial flow splitters extending between the inner barrel member and the casing. Each radial flow splitter includes a leading edge facing into a flow of air, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and an axis extending through the leading edge and the trailing end wall. A width of each radial flow splitter increases from the leading edge to the trailing end wall. The side walls diverge away from the axis in a downstream direction corresponding to the flow of air. Optionally, the side walls also diverge away from the axis in a radial direction between the inner barrel member and the casing.
    Type: Application
    Filed: March 5, 2018
    Publication date: July 12, 2018
    Applicant: General Electric Company
    Inventors: Carl Gerard Schott, Kenneth Damon Black, Matthew Stephen Casavant
  • Publication number: 20180010617
    Abstract: A gas turbine engine is disclosed having a turbine, one or more hydrocarbon gas combustors, and a compressor. The compressor has a rotor assembly with one or more rotor blade rows extending radially outward from an inner wheel disk. The compressor also has a stator assembly with one or more stator vane rows extending radially inward from an inner casing and positioned between adjacent rotor blade rows. The inner casing extends circumferentially around the rotor assembly and is constructed from at least one low-alpha metal alloy.
    Type: Application
    Filed: July 11, 2016
    Publication date: January 11, 2018
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black, Christian Michael Hansen, Donald Earl Floyd, James Adaickalasamy, Brett Darrick Klingler, Khoa Dang Cao, Kyle Eric Benson, Devin Patrick Perkins, Damian Anthony McClelland
  • Patent number: 9828880
    Abstract: A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: November 28, 2017
    Assignee: General Electric Company
    Inventors: Henry Grady Ballard, Jr., Ozgur Bozkurt, Kenneth Damon Black, Radu Ioan Danescu
  • Patent number: 9719372
    Abstract: A gas turbomachine includes a casing assembly surrounding a portion of the gas turbomachine and a counter-flow cooling system arranged within the casing. The counter-flow cooling system is configured and disposed to guide cooling fluid through the casing assembly in a first axial direction and return cooling fluid through the casing assembly in a second axial direction that is opposite the first axial direction.
    Type: Grant
    Filed: May 1, 2012
    Date of Patent: August 1, 2017
    Assignee: General Electric Company
    Inventors: Henry Grady Ballard, Jr., Kenneth Damon Black, John David Memmer
  • Patent number: 9611759
    Abstract: A support assembly for externally adjusting an inner casing with respect to an outer casing for a turbomachine includes a carrier plate, a carrier block that is fixedly connected to the carrier plate, a restrictor block fixedly connected to the carrier plate, a rod coupled to the carrier plate, and a plate threadably connected to the rod. The carrier block includes an inclined side and a carrier side. The restrictor block includes a restrictor side and an inclined side. The restrictor side is generally oriented towards the carrier side. A vertical gap for receiving a support arm of an inner turbine casing is defined between the restrictor side and the carrier side. The plate may be rotated about the rod to cause simultaneous movement of the rod, the carrier plate, the carrier block and the restrictor block, thus adjusting the inner casing with respect to the outer casing.
    Type: Grant
    Filed: May 30, 2014
    Date of Patent: April 4, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: James Adaickalasamy, Pramod Akulu, Kenneth Damon Black
  • Patent number: 9546572
    Abstract: A turbine system is provided having a first turbine casing and a second turbine casing, the first and second turbine casings together defining an inner wall. The turbine system further includes a first attachment flange extending from a surface of the first turbine casing within the inner wall and a second attachment flange extending from a surface of the second turbine casing within the inner wall. The first attachment flange defines a first aperture and the second attachment flange defines a second aperture. A pin extends through the first aperture and into the second aperture.
    Type: Grant
    Filed: September 24, 2013
    Date of Patent: January 17, 2017
    Assignee: General Electric Company
    Inventors: Khoa Dang Cao, Kenneth Damon Black
  • Patent number: 9528392
    Abstract: A system for supporting a turbine nozzle includes an inner barrel having a forward end, an aft end and an outer surface that extends between the forward end and the aft end. A first fitting that extends through the outer surface is defined within the inner barrel. The system further includes a nozzle support ring that defines a second fitting that is complementary to the first fitting defined within the inner barrel.
    Type: Grant
    Filed: May 10, 2013
    Date of Patent: December 27, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black
  • Patent number: 9528440
    Abstract: A diffuser strut fairing includes a top portion, a bottom portion, a pressure side portion, a suction side portion, an inner surface and an outer surface. The pressure side portion and the suction side portion extend between the top portion and the bottom portion. The exhaust diffuser strut faring further includes a flow manifold that is at least partially defined between the pressure side portion and the suction side portion. A plurality of openings is disposed along the suction side portion and are in fluid communication with the flow manifold.
    Type: Grant
    Filed: May 31, 2013
    Date of Patent: December 27, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Carl Gerard Schott, Douglas Frank Beadie, Kenneth Damon Black, Khoa Dang Cao
  • Publication number: 20160348534
    Abstract: A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.
    Type: Application
    Filed: August 15, 2016
    Publication date: December 1, 2016
    Inventors: Radu Ioan DANESCU, David Martin JOHNSON, Kenneth Damon BLACK, Christopher Paul COX, Ozgur BOZKURT
  • Publication number: 20160305281
    Abstract: A gas turbomachine includes a casing assembly surrounding a portion of the gas turbomachine. The casing assembly includes an inner casing portion defining a casing volume VC and a counter-flow cooling system arranged within the inner casing portion. The counter-flow cooling system includes a plurality of ducts that collectively define a channel volume Vch. The plurality of ducts is configured and disposed to guide cooling fluid through the casing assembly in a first axial direction and return cooling fluid through the casing assembly in a second axial direction that is opposite the first axial direction. The casing volume and the channel volume define a volume ratio of about 0.0002<VCh/VC<0.9.
    Type: Application
    Filed: June 7, 2016
    Publication date: October 20, 2016
    Inventors: Henry Grady Ballard, JR., Kenneth Damon Black, John David Memmer
  • Patent number: 9453429
    Abstract: A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.
    Type: Grant
    Filed: March 11, 2013
    Date of Patent: September 27, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Radu Ioan Danescu, David Martin Johnson, Kenneth Damon Black, Christopher Paul Cox, Ozgur Bozkurt
  • Patent number: 9435218
    Abstract: A gas turbine engine that includes: a flowpath defined through one of a compressor and a turbine; an inner casing defining an axially tilted outboard boundary of the flowpath, which, relative to the axial tilt, defines a converging direction in which the flowpath converges and a diverging direction in which the flowpath diverges; a row of rotor blades having outer tips that oppose the outboard boundary across a gap clearance defined therebetween; an outer casing concentrically arranged about the inner casing so to form an annulus therebetween; and a connection assembly that slidably connects the inner casing to the outer casing and includes a biasing means for axially preloading the inner casing in the converging direction.
    Type: Grant
    Filed: July 31, 2013
    Date of Patent: September 6, 2016
    Assignee: General Electric Company
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black, Christopher Paul Cox
  • Patent number: 9422824
    Abstract: Thermal control is provided for a gas turbine casing by supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine.
    Type: Grant
    Filed: October 18, 2012
    Date of Patent: August 23, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black, David Martin Johnson, Radu Ioan Danescu
  • Patent number: 9416679
    Abstract: A borescope assembly includes a first borescope plug comprising a first perimeter geometry portion. Also included is a second borescope plug comprising a second perimeter geometry portion distinct from the first perimeter geometry portion. Further included is a first borescope hole comprising a first hole geometry portion corresponding to the first perimeter geometry portion of the first borescope plug. Yet further included is a second borescope hole comprising a second hole geometry portion corresponding to the second perimeter geometry portion of the second borescope plug.
    Type: Grant
    Filed: August 7, 2013
    Date of Patent: August 16, 2016
    Assignee: General Electric Company
    Inventor: Kenneth Damon Black
  • Patent number: 9322334
    Abstract: A deformable fastener assembly for use with a gas turbine engine. The deformable fastener may be used to fasten a component of the gas turbine that is subjected to high temperatures and thermal deformation, such as an impingement sleeve assembly, to a rigid portion, such as the inner turbine shell of the gas turbine engine. The deformable fastener assemblies may permit components to be fastened to a rigid portion of the gas turbine with a consistent load input to permit frictional transient sliding of the component relative to the rigid portion of the gas turbine engine.
    Type: Grant
    Filed: October 23, 2012
    Date of Patent: April 26, 2016
    Assignee: General Electric Company
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black
  • Patent number: 9238971
    Abstract: A device for directing gas impingement to an inner casing of a gas turbine may include a plate configured for attachment to the outer surface of the inner casing. The plate has a first surface opposing the inner casing when the plate is attached to an area of the inner casing and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modifications are possible. Related gas turbine assemblies are also disclosed.
    Type: Grant
    Filed: October 18, 2012
    Date of Patent: January 19, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black, David Martin Johnson, Radu Ioan Danescu