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).
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Patent number: 10100647Abstract: 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: GrantFiled: June 17, 2013Date of Patent: October 16, 2018Assignee: General Electric CompanyInventors: Stephen Mark Molter, Mark Edward Stegemiller, Shawn Michael Pearson, Steven Robert Brassfield
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Patent number: 9995148Abstract: 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: GrantFiled: March 13, 2013Date of Patent: June 12, 2018Assignee: General Electric CompanyInventors: Stephen Mark Molter, Steven Robert Brassfield, Shawn Michael Pearson, Mark Edward Stegemiller
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Patent number: 9869185Abstract: 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: GrantFiled: July 30, 2013Date of Patent: January 16, 2018Assignee: General Electric CompanyInventors: Shawn Michael Pearson, Steven Robert Brassfield, Stephen Mark Molter, Mark Edward Stegemiller, Nicholas Ertel, Vanessa Camarillo
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Patent number: 9863254Abstract: 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: GrantFiled: April 23, 2013Date of Patent: January 9, 2018Assignee: General Electric CompanyInventors: Christopher Michael Ceglio, Randall Charles Bauer, Stephen Mark Molter, Mark Edward Stegemiller
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Patent number: 9840920Abstract: 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: GrantFiled: June 14, 2013Date of Patent: December 12, 2017Assignee: General Electric CompanyInventors: Shawn Michael Pearson, Steven Robert Brassfield, Mark Edward Stegemiller, Jonathan Filipa, Daniel Lee Durstock
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Publication number: 20150226069Abstract: 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: ApplicationFiled: July 30, 2013Publication date: August 13, 2015Inventors: Shawn Michael Pearson, Steven Robert Brassfield, Stephen Mark Molter, Mark Edward Stegemiller, Nicholas Ertel, Vanessa Camarillo
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Publication number: 20150167480Abstract: 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: ApplicationFiled: June 14, 2013Publication date: June 18, 2015Inventors: Shawn Michael Pearson, Steven Robert Brassfield, Mark Edward Stegemiller, Jonathan Filipa, Daniel Lee Durstock
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Publication number: 20150152735Abstract: 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: ApplicationFiled: June 17, 2013Publication date: June 4, 2015Inventors: Stephen Mark Molter, Mark Edward Stegemiller, Shawn Michael Pearson, Steven Robert Brassfield
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Publication number: 20150152734Abstract: 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: ApplicationFiled: April 23, 2013Publication date: June 4, 2015Inventors: Christopher Michael Ceglio, Randall Charles Bauer, Stephen Mark Molter, Mark Edward Stegemiller
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Patent number: 9033652Abstract: 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: GrantFiled: September 30, 2011Date of Patent: May 19, 2015Assignee: General Electric CompanyInventors: Steve Mark Molter, Steven Robert Brassfield, Richard William Jendrix, Cory Michael Williams, Renee Solomon Wenstrup, Mark Willard Marusko, Mark Edward Stegemiller
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Publication number: 20130081408Abstract: 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: ApplicationFiled: September 30, 2011Publication date: April 4, 2013Inventors: Steve Mark Molter, Steven Robert Brassfield, Richard William Jendrix, Cory Michael Williams, Renee Solomon Wenstrup, Mark Willard Marusko, Mark Edward Stegemiller
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Patent number: 7290986Abstract: 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: GrantFiled: September 9, 2005Date of Patent: November 6, 2007Assignee: General Electric CompanyInventors: Mark Edward Stegemiller, Chander Prakash, Leslie Eugene Leeke, Kevin Samuel Klasing, Ching-Pang Lee
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Patent number: 7008179Abstract: 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: GrantFiled: December 16, 2003Date of Patent: March 7, 2006Assignee: General Electric Co.Inventors: Gerard Anthony Rinck, Jonathan Philip Clarke, Mark Edward Stegemiller, Hardev Singh, Steven Robert Brassfield
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Patent number: 6554572Abstract: 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: GrantFiled: May 17, 2001Date of Patent: April 29, 2003Assignee: General Electric CompanyInventors: Gerard Anthony Rinck, Mark Edward Stegemiller, Hardev Singh, Brian Alan Norton
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Publication number: 20030017052Abstract: 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: ApplicationFiled: July 6, 2001Publication date: January 23, 2003Inventors: Wilson Frost, Mark Edward Stegemiller, Andrew Charles Powis, Peter P. Pirolla, David John Humanchuk, Gunnar Leif Siden
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Patent number: 6503059Abstract: 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: GrantFiled: July 6, 2001Date of Patent: January 7, 2003Assignee: General Electric CompanyInventors: Wilson Frost, Mark Edward Stegemiller, Andrew Charles Powis, Peter P. Pirolla, David John Humanchuk, Gunnar Leif Siden
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Publication number: 20020187039Abstract: 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: ApplicationFiled: May 17, 2001Publication date: December 12, 2002Inventors: Gerard Anthony Rinck, Mark Edward Stegemiller, Hardev Singh, Brian Alan Norton
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Patent number: 6428273Abstract: 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: GrantFiled: January 5, 2001Date of Patent: August 6, 2002Assignee: General Electric CompanyInventors: Sean Robert Keith, Mark Edward Stegemiller, Steven Robert Brassfield
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Publication number: 20020090294Abstract: 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: ApplicationFiled: January 5, 2001Publication date: July 11, 2002Applicant: GENERAL ELECTRIC COMPANYInventors: Sean Robert Keith, Mark Edward Stegemiller, Steven Robert Brassfield