Patents by Inventor Mark Willard Marusko

Mark Willard Marusko 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: 10648352
    Abstract: A turbine blade sealing structure for a ceramic matrix composite component is provided. The turbine sealing structure includes at least one top ply abutting a top portion of a shank. The at least one top ply extends out over the top portion of the shank. The turbine sealing structure includes at least one side ply abutting a side portion of the shank. The at least one side ply extends along a side portion of the shank. The at least one top ply and at least one side ply form an angel wing and a skirt with on the shank of the ceramic matrix composite component.
    Type: Grant
    Filed: June 13, 2013
    Date of Patent: May 12, 2020
    Assignee: General Electric Company
    Inventors: Anthony Reid Paige, Paul Izon, Michael Verrilli, Mark Willard Marusko, Mark Eugene Noe, Joshua Brian Jamison, Andrew John Breslin
  • Patent number: 10287897
    Abstract: A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation includes a shank portion formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus. The damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly.
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: May 14, 2019
    Assignee: General Electric Company
    Inventors: Anthony Reid Paige, II, Michael James Verrilli, Joshua Brian Jamison, Mark Eugene Noe, Paul Izon, Mark Willard Marusko
  • Patent number: 10018054
    Abstract: Methods for fabricating a component of a gas turbine engine are provided. In one embodiment, the method includes molding a CMC material to form a first portion of the gas turbine engine component, processing the first portion to form a first assembly, preparing the first assembly and a second portion of the gas turbine engine component for processing, and processing the first assembly and second portion to form a second assembly. In another embodiment, the method includes processing a first plurality of CMC plies to form a first assembly; positioning the first assembly and a second plurality of CMC plies on a tool for processing, the first assembly defining a first plane, the second plurality of plies defining a second plane, wherein the second plane is perpendicular to the first plane; and processing the first assembly and the second plurality of plies to form a second assembly.
    Type: Grant
    Filed: October 23, 2015
    Date of Patent: July 10, 2018
    Assignee: General Electric Company
    Inventors: Michael J. Verrilli, Mark Eugene Noe, Mark Willard Marusko, Paul Izon, Robert Tyler, Christopher Hasse
  • Patent number: 10018067
    Abstract: A clearance control apparatus for a gas turbine engine including an annular turbine case having opposed inner and outer surfaces; an annular manifold surrounding a portion of the turbine case, the manifold including: an inlet port in fluid communication with the manifold and the outer surface of the turbine case, and an exit port; and a bypass pipe having an upstream end coupled to the exit port, a downstream end coupled to a low-pressure sink, and a valve disposed between upstream and downstream ends, the valve selectively moveable between a first position which blocks flow between the upstream and downstream ends, and a second position which permits flow between the upstream and downstream ends.
    Type: Grant
    Filed: January 9, 2014
    Date of Patent: July 10, 2018
    Assignee: General Electric Company
    Inventors: Kevin Samuel Klasing, Richard William Albrecht, Jr., Brandon Flowers Powell, Mark Willard Marusko, Anthony Venzon, Thomas Ryan Wallace
  • Publication number: 20180161854
    Abstract: The present disclosure generally relates to integrated core-shell investment casting molds that provide a filament structure corresponding to a cooling hole pattern in the surface of the turbine blade or stator vane, which provide a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.
    Type: Application
    Filed: December 13, 2016
    Publication date: June 14, 2018
    Inventors: James Herbert DEINES, Brian David PRZESLAWSKI, Michael John MCCARREN, Douglas Gerard KONITZER, Mark Willard MARUSKO, Xi YANG
  • Publication number: 20180161853
    Abstract: The present disclosure generally relates to integrated core-shell investment casting molds including a main core portion, a core tip portion, and a shell portion with at least one cavity between the core portion and the shell portion. The cavity defines the shape of a cast component upon casting and removal of the ceramic mold. These molds also provide filament structures corresponding to cooling hole patterns in the surface of the turbine blade or the stator vane, which provide a leaching pathway for the core portion after metal casting. At least two ceramic tip filaments connect the core tip portion and the shell portion and eliminate the need for tip pins or a shell lock to hold the tip plenum core in place during casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.
    Type: Application
    Filed: December 13, 2016
    Publication date: June 14, 2018
    Inventors: James Herbert DEINES, Brian David PRZESLAWSKI, Michael John MCCARREN, Gregory Terrence GARAY, Douglas Gerard KONITZER, Mark Willard MARUSKO, Xi YANG, Brian Patrick PETERSON
  • Publication number: 20180010797
    Abstract: A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.
    Type: Application
    Filed: July 7, 2016
    Publication date: January 11, 2018
    Inventors: Mark Willard Marusko, Michael Alan Stieg, Brian Christopher Towle
  • Publication number: 20170370583
    Abstract: Ceramic matrix composite (CMC) components and methods for forming CMC components of gas turbine engines are provided. In one embodiment, a CMC component for a gas turbine engine includes an inner wall defining a first inner surface; an outer wall defining a second inner surface; and a nozzle extending from the inner wall to the outer wall. The inner wall, outer wall, and nozzle are integrally formed from a CMC material such that the inner wall, outer wall, and nozzle are a single unitary component. An exemplary method for forming a CMC component includes laying up a plurality of plies of a CMC material; processing the plurality of plies to form a green state component; firing the green state component; and densifying the fired component to produce a final unitary component. The unitary component comprises a combustor liner portion and a combustor discharge nozzle stage portion.
    Type: Application
    Filed: June 22, 2016
    Publication date: December 28, 2017
    Inventors: Mark Willard Marusko, Mark Eugene Noe, Darrell Glenn Senile
  • Publication number: 20170248030
    Abstract: A shroud for a gas turbine is provided. The shroud can include an outer box having a first wall and a second wall circumferentially spaced apart from the first wall. An inner box is positioned within the outer box. The inner box defines one or more passageways extending therethrough and a first chamber. The inner box and the outer box collectively define a second chamber. The one or more passageways defined by the inner box fluidly couple the first chamber and the second chamber. The first wall of the outer box defines a first boss and first notch, and the second wall of the outer box defines a second boss and notch. A gas turbine is also provided that can include a plurality of such turbine shrouds.
    Type: Application
    Filed: February 26, 2016
    Publication date: August 31, 2017
    Inventors: Mark Willard Marusko, Daniel Lee Durstock
  • Publication number: 20170114649
    Abstract: Methods for fabricating a component of a gas turbine engine are provided. In one embodiment, the method includes molding a CMC material to form a first portion of the gas turbine engine component, processing the first portion to form a first assembly, preparing the first assembly and a second portion of the gas turbine engine component for processing, and processing the first assembly and second portion to form a second assembly. In another embodiment, the method includes processing a first plurality of CMC plies to form a first assembly; positioning the first assembly and a second plurality of CMC plies on a tool for processing, the first assembly defining a first plane, the second plurality of plies defining a second plane, wherein the second plane is perpendicular to the first plane; and processing the first assembly and the second plurality of plies to form a second assembly.
    Type: Application
    Filed: October 23, 2015
    Publication date: April 27, 2017
    Inventors: Michael J. Verrilli, Mark Eugene Noe, Mark Willard Marusko, Paul Izon, Robert Tyler, Christopher Hasse
  • Patent number: 9410437
    Abstract: A process for producing airfoil components containing ceramic-based materials and having a tip cap. The process entails forming an airfoil portion of the component from an airfoil portion material that contains a precursor of a ceramic-based material. The airfoil portion material defines concave and convex walls of the airfoil portion, and the concave and convex walls define a tip region of the airfoil portion and at least one cavity within the airfoil portion. At least a first ply is formed that contains a precursor of a ceramic-based material, and the first ply at least partially closes the cavity at the tip region of the airfoil portion. The airfoil portion material and the first ply are then cured so that the first ply forms a tip cap that closes the cavity and the precursors of the airfoil portion material and first ply are converted to the ceramic-based materials thereof.
    Type: Grant
    Filed: December 20, 2012
    Date of Patent: August 9, 2016
    Assignee: General Electric Company
    Inventors: Anthony Reid Paige, Mark Eugene Noe, Michael James Verrilli, Mark Willard Marusko, Joshua Brian Jamison, Paul Izon
  • Patent number: 9228445
    Abstract: Hybrid turbine airfoil components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials. The components include a first component formed of a ceramic-based material and a second component formed of a metallic material. The first component comprises an airfoil portion and a nub, and the second component is separately formed and attached to the first component by casting the metallic material around the nub of the first component. The second component includes a platform portion between the airfoil portion and the nub of the first component and a dovetail portion on the nub of the first component. Each of the platform and dovetail portions has at least one off-axis geometric feature that results in the second component having a more complex geometry than the first component.
    Type: Grant
    Filed: December 23, 2010
    Date of Patent: January 5, 2016
    Assignee: General Electric Company
    Inventors: Toby George Darkins, Jr., John Peter Heyward, Eric Alan Estill, Joshua Brian Jamison, James Herbert Deines, Mark Willard Marusko, James Thomas Hawkins
  • Publication number: 20150369077
    Abstract: A clearance control apparatus for a gas turbine engine including an annular turbine case having opposed inner and outer surfaces; an annular manifold surrounding a portion of the turbine case, the manifold including: an inlet port in fluid communication with the manifold and the outer surface of the turbine case, and an exit port; and a bypass pipe having an upstream end coupled to the exit port, a downstream end coupled to a low-pressure sink, and a valve disposed between upstream and downstream ends, the valve selectively moveable between a first position which blocks flow between the upstream and downstream ends, and a second position which permits flow between the upstream and downstream ends.
    Type: Application
    Filed: January 9, 2014
    Publication date: December 24, 2015
    Inventors: Kevin Samuel KLASING, Richard William ALBRECHT, Jr., Brandon Flowers POWELL, Mark WIllard MARUSKO, Anthony VENZON, Thomas Ryan WALLACE
  • Publication number: 20150192027
    Abstract: A turbine blade sealing structure for a ceramic matrix composite component is provided. The turbine sealing structure includes at least one top ply abutting a top portion of a shank. The at least one top ply extends out over the top portion of the shank. The turbine sealing structure includes at least one side ply abutting a side portion of the shank. The at least one side ply extends along a side portion of the shank.
    Type: Application
    Filed: June 13, 2013
    Publication date: July 9, 2015
    Inventors: Anthony Reid Paige, Paul Izon, Michael Verrilli, Mark Willard Marusko, Mark Eugene Noe, Joshua Brian Jamison, Andrew John Breslin
  • Patent number: 9033652
    Abstract: An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and a trailing edge, such that a cavity is defined therebetween. A plurality of cooling circuits are defined within the cavity. Each cooling circuit channels cooling fluid through at least one cooling chamber to facilitate cooling the airfoil. More specifically, a cascade impingement circuit, a down pass circuit, a flag tip circuit, and a trailing edge circuit are provided. The cascade impingement circuit includes a central chamber and a plurality of impingement chambers.
    Type: Grant
    Filed: September 30, 2011
    Date of Patent: May 19, 2015
    Assignee: General Electric Company
    Inventors: Steve Mark Molter, Steven Robert Brassfield, Richard William Jendrix, Cory Michael Williams, Renee Solomon Wenstrup, Mark Willard Marusko, Mark Edward Stegemiller
  • Patent number: 8893382
    Abstract: A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.
    Type: Grant
    Filed: September 30, 2011
    Date of Patent: November 25, 2014
    Assignee: General Electric Company
    Inventors: David Bruce Patterson, Donald Michael Corsmeier, Craig Douglas Young, Donald Lee Gardner, James Edward Thompson, Daniel Dale Brown, Glenn Edward Wiehe, Donald Scott Yeager, Mark Willard Marusko, Michael Joseph Zerbe
  • Patent number: 8834105
    Abstract: A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; and an annular stationary structure surrounding the shroud segment, where the shroud segment is mechanically coupled to the stationary structure. The stationary structure includes at least one axially-facing bearing surface which is in direct contact with the shroud segment, and the shroud segment is disposed so as to absorb at least one axially-aligned force and transfer the axially-aligned force to the bearing surface.
    Type: Grant
    Filed: December 30, 2010
    Date of Patent: September 16, 2014
    Assignee: General Electric Company
    Inventors: Joseph Charles Albers, Mark Willard Marusko, Barry Allan Wilson, Aaron Michael Dziech, Christopher Ryan Johnson
  • Patent number: 8777582
    Abstract: Hybrid components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials, yet result in a robust mechanical attachment of the ceramic and non-ceramic portions of the components. The components includes a first subcomponent formed of a ceramic-based material and a second subcomponent formed of a metallic material. The first subcomponent has a nub and the second subcomponent is separately formed and attached to the first subcomponent by casting the metallic material around the nub of the first subcomponent. The second subcomponent is attached to the first subcomponent by a compression fit and encapsulation of the second subcomponent on the nub of the first subcomponent. The nub has a compliant coating system that provides thermal expansion compliance between the metallic material of the second subcomponent and the ceramic-based material of the first subcomponent.
    Type: Grant
    Filed: December 27, 2010
    Date of Patent: July 15, 2014
    Assignee: General Electric Company
    Inventors: Toby George Darkins, Jr., John Peter Heyward, Eric Alan Estill, Joshua Brian Jamison, James Herbert Deines, Mark Willard Marusko, James Thomas Hawkins
  • Patent number: 8753073
    Abstract: A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment comprising a low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces of the segment; and (b) a first seal assembly received in at least one slot formed in the first end face, the first seal assembly comprising one or more spline seals which protrude from the first end face and which are arranged to define a continuous sealing surface around the perimeter of the first end face.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: June 17, 2014
    Assignee: General Electric Company
    Inventors: Joseph Charles Albers, Mark Willard Marusko, Barry Allan Wilson, Aaron Michael Dziech
  • Patent number: 8740552
    Abstract: A turbine shroud apparatus for a gas turbine engine includes an arcuate turbine shroud segment of low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall. Radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof.
    Type: Grant
    Filed: May 28, 2010
    Date of Patent: June 3, 2014
    Assignee: General Electric Company
    Inventors: Mark Willard Marusko, Joseph Charles Albers, Aaron Michael Dziech, Christopher Ryan Johnson