Patents by Inventor Matthew Stephen Casavant

Matthew Stephen Casavant 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).

  • 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: 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: 9447794
    Abstract: A system includes at least one inducer including a flow passage configured to guide a fluid flow into a cavity defined by a casing and rotor of a gas turbine engine, the flow passage includes an inlet configured to receive the fluid flow from a compressor diffuser of the gas turbine engine, and an outlet configured to discharge the fluid flow into the cavity. The at least one inducer is configured to be disposed within the gas turbine engine so that the second outlet is axially disposed forward of a diffuser outlet of the compressor diffuser.
    Type: Grant
    Filed: August 27, 2013
    Date of Patent: September 20, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Matthew Stephen Casavant
  • Patent number: 9441499
    Abstract: A system for passively varying an axial position of an inner casing of a gas turbine pursuant to changing pressure in a flowpath during transient engine operation. The system may include: a connection assembly slidably connecting the inner casing to the outer casing for axial movement of the inner casing between a first position and a second position; means for pressurizing the annulus relative to a flowpath pressure; biasing means for axially preloading the inner casing toward the first position; and an inner casing receiving surface configured to receive a pressure in the annulus for axially loading the inner casing in opposition to the axial preload of the biasing means.
    Type: Grant
    Filed: July 31, 2013
    Date of Patent: September 13, 2016
    Assignee: General Electric Company
    Inventors: Matthew Stephen Casavant, David Martin Johnson
  • 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: 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: 9243510
    Abstract: A floating seal assembly for sealing two static parts is disclosed. Each static part has an opposing groove, and the opposing grooves define a seal cavity. Floating seal assembly includes a floating circumferential seal having a middle portion and opposing end portions, each opposing end portion is positioned within a groove in one of the static parts, wherein each end portion has a curved side facing a low pressure side of the seal cavity. The floating seal assembly according to embodiments of the invention is pressure driven in that each curved side of the end portions is configured to engage a low pressure side of the seal cavity in response to a pressure differential across the sealing cavity reaching a threshold value.
    Type: Grant
    Filed: September 10, 2012
    Date of Patent: January 26, 2016
    Assignee: General Electric Company
    Inventors: Matthew Stephen Casavant, Kevin Thomas McGovern
  • 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
  • Patent number: 9163649
    Abstract: A first adjustable stop on a jack member selectively adjusts an incline stop gap while a second adjustable stop on a support element selectively adjusts a decline stop gap. Stop surfaces on the first adjustable stop and the support element may define the incline stop gap, while stop surfaces on the second adjustable stop and the first adjustable stop may define the decline stop gap. A number of turns of a stop needed to effect a desired of adjustment may be determined using a pitch, lead, and/or number of starts of threads used to mount the stops.
    Type: Grant
    Filed: October 16, 2012
    Date of Patent: October 20, 2015
    Assignee: General Electric Company
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black
  • Patent number: 9127568
    Abstract: A turbine casing includes a plurality of arc-shaped segments having a flange at each side end to connect to a flange of an adjacent arc-shaped segment. The flange extends outward from an outer surface of each arc-shaped segment and extends along the outer surface in a front-to-rear direction. Each arc-shaped segment has a portion of the outer surface that is co-linear with the flange in a front-to-rear direction that does not include the flange.
    Type: Grant
    Filed: January 4, 2012
    Date of Patent: September 8, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Bradley Edwin Wilson, Matthew Stephen Casavant
  • Patent number: 9097123
    Abstract: A method and system adapted for removing one or more shells from an assembly of multiple annular shells, for example, turbine shells of a gas turbine engine. The method includes removing an upper shell positioned in an upper position relative to a lower shell of the assembly of multiple annular shells, and then positioning and securing a counterweight in the upper position and securing the counterweight to the lower shell as a replacement for the upper shell in the upper position. The counterweight and the lower shell are then rotated in unison until the lower shell is in the upper position and the counterweight is in a lower position previously occupied by the lower shell. Thereafter, the lower shell can be removed from the assembly.
    Type: Grant
    Filed: July 26, 2012
    Date of Patent: August 4, 2015
    Assignee: General Electric Company
    Inventors: James Bradford Holmes, Kenneth Damon Black, Christopher Paul Cox, Matthew Stephen Casavant, Bradley Edwin Wilson, Brett Darrick Klingler
  • Patent number: 9046004
    Abstract: A seal for a turbine casing is provided. The turbine casing includes a plurality of sections joined at flanges provided on each section. Each flange includes a bore and a counterbore. The seal comprises a compression sleeve seal having a length that is greater than a counterbore-to-counterbore length of two flanges; a fastener configured to extend through the compression sleeve seal; and a nut threadable on each end of the fastener. The compression sleeve seal is compressible between each flange and each nut to create a first seal and is radially extensible to create a second seal against each bore.
    Type: Grant
    Filed: February 28, 2012
    Date of Patent: June 2, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Stephen Casavant, Brett Darrick Klingler
  • Patent number: 9017015
    Abstract: A turbomachine includes an inner casing component having a first end that extends to a second end and a seal member. An outer casing component is coupled to the inner casing component. The annular outer casing component includes a first end portion that extends to a second end portion and a seal element that aligns with the seal member of the annular inner casing component to form a seal passage. A seal is arranged in the seal passage. The seal includes a first end section that extends to a second end section through an intermediate zone. The first end section includes a recessed portion and the second end section includes a connecting portion. The connecting portion is configured and disposed to nest within the recessed portion to form a substantially continuous seal.
    Type: Grant
    Filed: October 27, 2011
    Date of Patent: April 28, 2015
    Assignee: General Electric Company
    Inventors: Matthew Stephen Casavant, David Martin Johnson
  • Patent number: 8992167
    Abstract: In certain embodiments of the present disclosure a turbine casing assembly is described. The turbine casing assembly includes an inner casing and an outer casing surrounding the inner casing. The outer casing includes a first outer casing section and a second outer casing section that join together along a flange. Two bolts extend through the flange and join together the first outer casing section and the second outer casing section. A pin having a first segment having a first diameter and a second segment having a second diameter extends through the inner casing and the outer casing and supports the inner casing relative to the outer casing. The pin has a first diameter that is greater than the second diameter and is located between the two bolts along the axis of the flange.
    Type: Grant
    Filed: September 7, 2011
    Date of Patent: March 31, 2015
    Assignee: General Electric Company
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black
  • Publication number: 20150063996
    Abstract: A system includes at least one inducer including a flow passage configured to guide a fluid flow into a cavity defined by a casing and rotor of a gas turbine engine, the flow passage includes an inlet configured to receive the fluid flow from a compressor diffuser of the gas turbine engine, and an outlet configured to discharge the fluid flow into the cavity. The at least one inducer is configured to be disposed within the gas turbine engine so that the second outlet is axially disposed forward of a diffuser outlet of the compressor diffuser.
    Type: Application
    Filed: August 27, 2013
    Publication date: March 5, 2015
    Applicant: General Electric Company
    Inventor: Matthew Stephen Casavant
  • Publication number: 20150047358
    Abstract: An inner barrel member for a gas turbomachine includes a body having an outer surface, an inner surface and one or more radial flow splitters provided on the outer surface. The one or more radial flow splitters are configured and disposed to be arranged along a combustor centerline at a combustion flow outlet radially inwardly of a transition piece.
    Type: Application
    Filed: August 14, 2013
    Publication date: February 19, 2015
    Applicant: General Electric Company
    Inventors: Carl Gerard Schott, Kenneth Damon Black, Matthew Stephen Casavant
  • Publication number: 20150037133
    Abstract: A system for passively varying an axial position of an inner casing of a gas turbine pursuant to changing pressure in a flowpath during transient engine operation. The system may include: a connection assembly slidably connecting the inner casing to the outer casing for axial movement of the inner casing between a first position and a second position; means for pressurizing the annulus relative to a flowpath pressure; biasing means for axially preloading the inner casing toward the first position; and an inner casing receiving surface configured to receive a pressure in the annulus for axially loading the inner casing in opposition to the axial preload of the biasing means.
    Type: Application
    Filed: July 31, 2013
    Publication date: February 5, 2015
    Applicant: General Electric Company
    Inventors: Matthew Stephen Casavant, David Martin Johnson
  • Publication number: 20150037145
    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: Application
    Filed: July 31, 2013
    Publication date: February 5, 2015
    Applicant: General Electric Company
    Inventors: Matthew Stephen Casavant, Kenneth Damon Black, Christopher Paul Cox