Patents by Inventor Graham David Sherlock
Graham David Sherlock 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: 9303515Abstract: A turbomachine diaphragm includes a sealing section having a first end portion that extends to a second end portion through an intermediate portion. At least one rail member includes a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section. The second end section includes a machined surface having a repair coupon mounting element. A repair coupon is mounted at the repair coupon mounting element and operatively connected to the at least one rail member. A method of repairing a turbomachine diaphragm is also disclosed herein.Type: GrantFiled: August 30, 2012Date of Patent: April 5, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Anshuman Singh, Paul Lawrence Kalmar, Graham David Sherlock, Americo Zapata
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Patent number: 8671585Abstract: A method for fabricating a nozzle segment for use within a turbine nozzle assembly. The method comprises providing a nozzle segment including an outer band, an inner band, and at least one vane extending there between, wherein at least one of the inner band and the outer band is formed with a transition piece groove defined therein, positioning an inspection tool in contact with the nozzle assembly such that the inspection tool is aligned relative to the nozzle segment using at least one datum, and verifying an alignment of each transition piece groove using the inspection tool.Type: GrantFiled: October 11, 2011Date of Patent: March 18, 2014Assignee: General Electric CompanyInventors: Graham David Sherlock, Christopher Edward Thompson
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Publication number: 20140064954Abstract: A turbomachine diaphragm includes a sealing section having a first end portion that extends to a second end portion through an intermediate portion. At least one rail member includes a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section. The second end section includes a machined surface having a repair coupon mounting element. A repair coupon is mounted at the repair coupon mounting element and operatively connected to the at least one rail member. A method of repairing a turbomachine diaphragm is also disclosed herein.Type: ApplicationFiled: August 30, 2012Publication date: March 6, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Anshuman Singh, Paul Lawrence Kalmar, Graham David Sherlock, Americo Zapata
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Publication number: 20120023746Abstract: A method for fabricating a nozzle segment for use within a turbine nozzle assembly. The method comprises providing a nozzle segment including an outer band, an inner band, and at least one vane extending there between, wherein at least one of the inner band and the outer band is formed with a transition piece groove defined therein, positioning an inspection tool in contact with the nozzle assembly such that the inspection tool is aligned relative to the nozzle segment using at least one datum, and verifying an alignment of each transition piece groove using the inspection tool.Type: ApplicationFiled: October 11, 2011Publication date: February 2, 2012Inventors: Graham David Sherlock, Christopher Edward Thompson
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Patent number: 8051564Abstract: A method for fabricating a nozzle segment for use within a turbine nozzle assembly. The method comprises providing a nozzle segment including an outer band, an inner band, and at least one vane extending there between, wherein at least one of the inner band and the outer band is formed with a transition piece groove defined therein, positioning an inspection tool in contact with the nozzle assembly such that the inspection tool is aligned relative to the nozzle segment using at least one datum, and verifying an alignment of each transition piece groove using the inspection tool.Type: GrantFiled: January 9, 2007Date of Patent: November 8, 2011Assignee: General Electric CompanyInventors: Graham David Sherlock, Christopher Edward Thompson
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Patent number: 7862264Abstract: A method for forming an opening in two different turbine components is provided. The method includes coupling a clamp to a base and coupling the clamp to a clamp bar, wherein the clamp bar is moveable with respect to the base. A first bushing plate is selected based on a first turbine component being drilled and is removably coupled to the base. A bushing is removably coupled to at least one aperture extending through the first bushing plate. An opening is formed in the first turbine component. A second bushing plate is selected based on a second turbine component being drilled. The second turbine component is different from the first turbine component. The second bushing plate is removably coupled to the base. An opening is formed in the second turbine component.Type: GrantFiled: February 27, 2007Date of Patent: January 4, 2011Assignee: General Electric CompanyInventors: Graham David Sherlock, Lynn Charles Gagne, Larry Paul Wencil
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Patent number: 7806655Abstract: A method for assembling a stator assembly for a turbine engine is provided. The method includes providing a blade with a base including an end wall having at least one hole defined therein and providing a shim having at least one aperture extending therethrough. The shim aperture is aligned with the end wall hole, and the shim is secured to the blade base end wall using a fastener. The fastener is inserted through the shim aperture in an interference fit within the end wall hole. The blade and the shim are coupled to a turbine casing.Type: GrantFiled: February 27, 2007Date of Patent: October 5, 2010Assignee: General Electric CompanyInventors: Lynn Charles Gagne, Graham David Sherlock, Kelvin Aaron, Thomas Robbins Tipton
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Patent number: 7766726Abstract: An assembly is provided for cropping the trailing edge tip of a stator zero blade in-situ. The cropping assembly includes a base plate that is secured to the end of the compressor stator blade to be cropped; a removable, rotational guide block; and a drill that is mounted to the guide block and rotatable relative to the base plate to crop the trailing edge tip of a stator blade.Type: GrantFiled: July 10, 2007Date of Patent: August 3, 2010Assignee: General Electric CompanyInventors: Graham David Sherlock, Lynn Charles Gagne
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Patent number: 7735238Abstract: A measuring tool measures a trailing edge position of gas turbine nozzle. The tool includes a frame member attachable to at least one predefined reference point on the nozzle. At least one sliding member is slidable relative to the frame member and includes a measuring point engageable with the trailing edge. A position of the sliding member relative to the frame member is determinative of the trailing edge position.Type: GrantFiled: July 31, 2008Date of Patent: June 15, 2010Assignee: General Electric CompanyInventors: Graham David Sherlock, Paul Lawrence Kalmar
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Patent number: 7735222Abstract: A tool capable of removing material is applied to a turbine wheel cooling slot. Material is removed from a selected portion of the cooling slot with the tool. And, stress concentrations are reduced within the slot through the removal of material.Type: GrantFiled: November 30, 2005Date of Patent: June 15, 2010Assignee: General Electric CompanyInventors: Graham David Sherlock, Paul Lawrence Kalmar
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Publication number: 20100024238Abstract: A measuring tool measures a trailing edge position of gas turbine nozzle. The tool includes a frame member attachable to at least one predefined reference point on the nozzle. At least one sliding member is slidable relative to the frame member and includes a measuring point engageable with the trailing edge. A position of the sliding member relative to the frame member is determinative of the trailing edge position.Type: ApplicationFiled: July 31, 2008Publication date: February 4, 2010Inventors: Graham David Sherlock, Paul Lawrence Kalmar
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Patent number: 7578164Abstract: A method for inspecting a turbine nozzle segment includes positioning the turbine nozzle segment on a base of a tool, with the outer forward face and the inner forward face of the turbine nozzle segment contacting a surface of the base. The outer wall is positioned between a first pedestal outer stand and a second pedestal outer stand of the tool, and the inner wall is positioned between a first pedestal inner stand and a second pedestal inner stand of the tool. At least one of a position, a depth and a width of a seal slot formed in a side edge of the outer wall and/or the inner wall is measured. At least one axial dimension of the turbine nozzle segment and at least one radial dimension of the turbine nozzle segment are measured.Type: GrantFiled: September 22, 2005Date of Patent: August 25, 2009Assignee: General Electric CompanyInventors: Graham David Sherlock, Paul Lawrence Kalmar, Benjamin Erick Baker
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Patent number: 7484928Abstract: A trailing edge coupon for the trailing edge of a airfoil of a turbine nozzle segment is welded to an airfoil section of the nozzle segment having a damaged trailing edge portion removed. The coupon includes film cooling holes spaced one from the other along a pressure side wall portion of the coupon and a plurality of radially spaced openings along the trailing edge. By welding the pressure and suction side edges of the coupon to the pressure and side edges of the remaining portion of the airfoil, the operating life of the nozzle is extended.Type: GrantFiled: March 21, 2007Date of Patent: February 3, 2009Assignee: General Electric CompanyInventors: Brian Peter Arness, Graham David Sherlock, Joseph Leonard Moroso, Stewart William Beitz, Graydon Wayne Peters
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Publication number: 20080206005Abstract: A method for forming an opening in two different turbine components is provided. The method includes coupling a clamp to a base and coupling the clamp to a clamp bar, wherein the clamp bar is moveable with respect to the base. A first bushing plate is selected based on a first turbine component being drilled and is removably coupled to the base. A bushing is removably coupled to at least one aperture extending through the first bushing plate. An opening is formed in the first turbine component. A second bushing plate is selected based on a second turbine component being drilled. The second turbine component is different from the first turbine component. The second bushing plate is removably coupled to the base. An opening is formed in the second turbine component.Type: ApplicationFiled: February 27, 2007Publication date: August 28, 2008Inventors: Graham David Sherlock, Lynn Charles Gagne, Larry Paul Wencil
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Publication number: 20080206063Abstract: A method for assembling a stator assembly for a turbine engine is provided. The method includes providing a blade with a base including an end wall having at least one hole defined therein and providing a shim having at least one aperture extending therethrough. The shim aperture is aligned with the end wall hole, and the shim is secured to the blade base end wall using a fastener. The fastener is inserted through the shim aperture in an interference fit within the end wall hole. The blade and the shim are coupled to a turbine casing.Type: ApplicationFiled: February 27, 2007Publication date: August 28, 2008Inventors: Lynn Charles Gagne, Graham David Sherlock, Kelvin Aaron, Thomas Robbins Tipton
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Publication number: 20080166229Abstract: A method for fabricating a nozzle segment for use within a turbine nozzle assembly. The method comprises providing a nozzle segment including an outer band, an inner band, and at least one vane extending there between, wherein at least one of the inner band and the outer band is formed with a transition piece groove defined therein, positioning an inspection tool in contact with the nozzle assembly such that the inspection tool is aligned relative to the nozzle segment using at least one datum, and verifying an alignment of each transition piece groove using the inspection tool.Type: ApplicationFiled: January 9, 2007Publication date: July 10, 2008Inventors: Graham David Sherlock, Christopher Edward Thompson
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Publication number: 20080115648Abstract: An assembly is provided for cropping the trailing edge tip of a stator zero blade in-situ. The cropping assembly includes a base plate that is secured to the end of the compressor stator blade to be cropped; a removable, rotational guide block; and a drill that is mounted to the guide block and rotatable relative to the base plate to crop the trailing edge tip of a stator blade.Type: ApplicationFiled: July 10, 2007Publication date: May 22, 2008Applicant: General Electric CompanyInventors: Graham David Sherlock, Lynn Charles Gagne
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Patent number: 7231724Abstract: A tool for measuring seal slot position includes a tool shaft having a longitudinal axis, a pin eccentrically disposed at one end of the tool shaft relative to the longitudinal axis, and a disk member disposed at an opposite end of the tool shaft that facilitates rotation of the tool shaft and pin in the seal slot. The tool provides for increased accuracy in measuring seal slot position such as turbine nozzle seal slot position.Type: GrantFiled: October 28, 2005Date of Patent: June 19, 2007Assignee: General Electric CompanyInventors: Graham David Sherlock, Paul Lawrence Kalmar, Christopher Edward Thompson