Patents by Inventor Mark Edward Stegemiller

Mark Edward Stegemiller 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: 10100647
    Abstract: A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge; an endwall projecting laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch having a throat disposed at its upstream end; and at least one film cooling hole passing through the outer surface and communicating with the plenum.
    Type: Grant
    Filed: June 17, 2013
    Date of Patent: October 16, 2018
    Assignee: General Electric Company
    Inventors: Stephen Mark Molter, Mark Edward Stegemiller, Shawn Michael Pearson, Steven Robert Brassfield
  • Patent number: 9995148
    Abstract: Apparatuses and methods are taught for cooling a turbine blade wherein at least one circuit is isolated along a cool suction side of the blade and the circuit turns aft toward a trailing edge.
    Type: Grant
    Filed: March 13, 2013
    Date of Patent: June 12, 2018
    Assignee: General Electric Company
    Inventors: Stephen Mark Molter, Steven Robert Brassfield, Shawn Michael Pearson, Mark Edward Stegemiller
  • Patent number: 9869185
    Abstract: A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: January 16, 2018
    Assignee: General Electric Company
    Inventors: Shawn Michael Pearson, Steven Robert Brassfield, Stephen Mark Molter, Mark Edward Stegemiller, Nicholas Ertel, Vanessa Camarillo
  • Patent number: 9863254
    Abstract: A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.
    Type: Grant
    Filed: April 23, 2013
    Date of Patent: January 9, 2018
    Assignee: General Electric Company
    Inventors: Christopher Michael Ceglio, Randall Charles Bauer, Stephen Mark Molter, Mark Edward Stegemiller
  • Patent number: 9840920
    Abstract: A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.
    Type: Grant
    Filed: June 14, 2013
    Date of Patent: December 12, 2017
    Assignee: General Electric Company
    Inventors: Shawn Michael Pearson, Steven Robert Brassfield, Mark Edward Stegemiller, Jonathan Filipa, Daniel Lee Durstock
  • Publication number: 20150226069
    Abstract: A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.
    Type: Application
    Filed: July 30, 2013
    Publication date: August 13, 2015
    Inventors: Shawn Michael Pearson, Steven Robert Brassfield, Stephen Mark Molter, Mark Edward Stegemiller, Nicholas Ertel, Vanessa Camarillo
  • Publication number: 20150167480
    Abstract: A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.
    Type: Application
    Filed: June 14, 2013
    Publication date: June 18, 2015
    Inventors: Shawn Michael Pearson, Steven Robert Brassfield, Mark Edward Stegemiller, Jonathan Filipa, Daniel Lee Durstock
  • Publication number: 20150152735
    Abstract: A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge; an endwall projecting laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch having a throat disposed at its upstream end; and at least one film cooling hole passing through the outer surface and communicating with the plenum.
    Type: Application
    Filed: June 17, 2013
    Publication date: June 4, 2015
    Inventors: Stephen Mark Molter, Mark Edward Stegemiller, Shawn Michael Pearson, Steven Robert Brassfield
  • Publication number: 20150152734
    Abstract: A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.
    Type: Application
    Filed: April 23, 2013
    Publication date: June 4, 2015
    Inventors: Christopher Michael Ceglio, Randall Charles Bauer, Stephen Mark Molter, Mark Edward Stegemiller
  • 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
  • Publication number: 20130081408
    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: Application
    Filed: September 30, 2011
    Publication date: April 4, 2013
    Inventors: Steve Mark Molter, Steven Robert Brassfield, Richard William Jendrix, Cory Michael Williams, Renee Solomon Wenstrup, Mark Willard Marusko, Mark Edward Stegemiller
  • Patent number: 7290986
    Abstract: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.
    Type: Grant
    Filed: September 9, 2005
    Date of Patent: November 6, 2007
    Assignee: General Electric Company
    Inventors: Mark Edward Stegemiller, Chander Prakash, Leslie Eugene Leeke, Kevin Samuel Klasing, Ching-Pang Lee
  • Patent number: 7008179
    Abstract: A gas turbine engine turbine blade includes a hollow airfoil extending radially from a blade root to a radially outer airfoil tip. The airfoil includes an airfoil outer wall having transversely spaced apart pressure and suction side walls meeting along chordally spaced apart leading and trailing edges of the airfoil. A radially extending cooling air supply channel within the airfoil includes a bank of pins integral with and extending transversely between the pressure and suction side walls. The bank of the pins is tuned such that a natural frequency of the blade associated with an engine forced driving mode of the blade is sufficiently away from a steady state engine operating frequency to substantially avoid natural frequency resonance of the blade during steady state engine operation. The bank of the pins is tuned by locations of the pins within the cooling air supply channel.
    Type: Grant
    Filed: December 16, 2003
    Date of Patent: March 7, 2006
    Assignee: General Electric Co.
    Inventors: Gerard Anthony Rinck, Jonathan Philip Clarke, Mark Edward Stegemiller, Hardev Singh, Steven Robert Brassfield
  • Patent number: 6554572
    Abstract: A turbine blade for a gas turbine engine. An existing blade was found to exhibit bowing, or a concave configuration facing the pressure side, along its trailing edge. The invention reduces bowing by (1) changing tilt, (2) changing lean, (3) reducing the number of cooling holes, while (4) changing the diameters of the cooling holes, to maintaining the total cooling flow unchanged.
    Type: Grant
    Filed: May 17, 2001
    Date of Patent: April 29, 2003
    Assignee: General Electric Company
    Inventors: Gerard Anthony Rinck, Mark Edward Stegemiller, Hardev Singh, Brian Alan Norton
  • Publication number: 20030017052
    Abstract: The fourth-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.
    Type: Application
    Filed: July 6, 2001
    Publication date: January 23, 2003
    Inventors: Wilson Frost, Mark Edward Stegemiller, Andrew Charles Powis, Peter P. Pirolla, David John Humanchuk, Gunnar Leif Siden
  • Patent number: 6503059
    Abstract: The fourth-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.
    Type: Grant
    Filed: July 6, 2001
    Date of Patent: January 7, 2003
    Assignee: General Electric Company
    Inventors: Wilson Frost, Mark Edward Stegemiller, Andrew Charles Powis, Peter P. Pirolla, David John Humanchuk, Gunnar Leif Siden
  • Publication number: 20020187039
    Abstract: A turbine blade for a gas turbine engine. An existing blade was found to exhibit bowing, or a concave configuration facing the pressure side, along its trailing edge. The invention reduces bowing by (1) changing tilt, (2) changing lean, (3) reducing the number of cooling holes, while (4) changing the diameters of the cooling holes, to maintaining the total cooling flow unchanged.
    Type: Application
    Filed: May 17, 2001
    Publication date: December 12, 2002
    Inventors: Gerard Anthony Rinck, Mark Edward Stegemiller, Hardev Singh, Brian Alan Norton
  • Patent number: 6428273
    Abstract: A turbine nozzle includes vanes joined to outer and inner bands. Each vane includes opposite sidewalls extending between leading and trailing edges, with an internal bridge extending between the sidewalls to effect forward and aft cavities. Side ribs extend along the sidewalls and project inwardly into the cavities. Each of the side ribs is truncated adjacent the bridge to uncouple the ribs therefrom and increase nozzle life.
    Type: Grant
    Filed: January 5, 2001
    Date of Patent: August 6, 2002
    Assignee: General Electric Company
    Inventors: Sean Robert Keith, Mark Edward Stegemiller, Steven Robert Brassfield
  • Publication number: 20020090294
    Abstract: A turbine nozzle includes vanes joined to outer and inner bands. Each vane includes opposite sidewalls extending between leading and trailing edges, with an internal bridge extending between the sidewalls to effect forward and aft cavities. Side ribs extend along the sidewalls and project inwardly into the cavities. Each of the side ribs is truncated adjacent the bridge to uncouple the ribs therefrom and increase nozzle life.
    Type: Application
    Filed: January 5, 2001
    Publication date: July 11, 2002
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Sean Robert Keith, Mark Edward Stegemiller, Steven Robert Brassfield