Patents by Inventor Brian Alan Norton
Brian Alan Norton 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: 10677032Abstract: An electric submersible pump (ESP) intake system, apparatus and method is described. An ESP intake system includes a filtered intake section coupled adjacently to a sliding sleeve intake section, wherein the sliding sleeve intake section has a closed initial state and is selectively actuatable to an open position when the filtered intake section becomes at least partially clogged. An ESP intake method includes operating an ESP pump downhole in a well including abrasive-laden fluid, the ESP pump including a filtered intake section and an actuatable intake section, employing the filtered intake section as a first fluid entrance into the ESP pump, monitoring information from ESP sensors during employment of the first fluid entrance to identify clogging of the filtered intake section, and opening the actuatable intake section upon the clogging so identified such that the actuatable intake section serves as a second fluid entrance into the ESP pump.Type: GrantFiled: October 24, 2017Date of Patent: June 9, 2020Assignee: HALLIBURTON ENERGY SERVICES, INC.Inventor: Brian Alan Norton
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Patent number: 7695243Abstract: A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil.Type: GrantFiled: July 27, 2006Date of Patent: April 13, 2010Assignee: General Electric CompanyInventors: Ching-Pang Lee, Tingfan Pang, Brian Alan Norton, Jan Christopher Schilling, Aspi Rustom Wadia
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Publication number: 20090155088Abstract: A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil.Type: ApplicationFiled: July 27, 2006Publication date: June 18, 2009Inventors: Ching-Pang Lee, Tingfan Pang, Brian Alan Norton, Jan Christopher Schilling, Aspi Rustom Wadia
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Patent number: 7244101Abstract: A gas turbine engine rotor blade includes an airfoil, platform, shank, and dovetail integrally joined together. A dust escape hole extends through the platform adjacent a fillet bridging the platform and shank to bleed dust therefrom during operation.Type: GrantFiled: October 4, 2005Date of Patent: July 17, 2007Assignee: General Electric CompanyInventors: Ching-Pang Lee, Darek Tomasz Zatorski, Brian Alan Norton, Jan Christopher Schilling
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Patent number: 7121802Abstract: A turbine blade includes an airfoil, platform, shank, and dovetail. The platform includes a first side disposed along the pressure side of the airfoil, and an opposite second side disposed along the airfoil suction side. The platform second side includes an integral damper keeper disposed below the midchord of the airfoil, and is locally thinner at the forward and aft ends of the platform second side for reducing blade weight.Type: GrantFiled: July 13, 2004Date of Patent: October 17, 2006Assignee: General Electric CompanyInventors: Robert Edward Athans, Brian Alan Norton
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Patent number: 7097429Abstract: A turbine blade includes an airfoil, platform, shank, and dovetail. The shank includes opposite forward and aft faces corresponding with leading and trailing edges of the airfoil, and opposite first and second sides corresponding with pressure and suction sides of the airfoil. The shank further includes lugs extending outwardly from the two sides, with a first lug having an inverted skirt extending outwardly toward the platform to join the shank aft face. The skirt cooperates with a seal body when mounted in the engine for reducing inter-blade leakage.Type: GrantFiled: July 13, 2004Date of Patent: August 29, 2006Assignee: General Electric CompanyInventors: Robert Edward Athans, William Charles Herman, Brian Alan Norton
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Patent number: 7008186Abstract: A turbine blade includes an airfoil having an internal cooling circuit with a first flow passage disposed directly behind the leading edge followed by a second flow passage separated therefrom by a corresponding bridge. The bridge includes a row of impingement apertures for cooling the leading edge. The suction sidewall of the airfoil includes a row of diffusion film cooling first holes extending in flow communication with the first passage. The first holes have a compound inclination angle, with a quadrilateral cross section forming a generally teardrop shaped outlet in the convex contour of the suction sidewall.Type: GrantFiled: September 17, 2003Date of Patent: March 7, 2006Assignee: General Electric CompanyInventors: Robert John Heeg, Brian Alan Norton, Scott Joseph Schmid, Ganesh Nagab Kumar
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Patent number: 6905308Abstract: A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and a vane. The replacement casting includes an airfoil stub. The airfoil stub is received in a recess formed in the inner band. Joining is completed by joining the airfoil stub to the inner band. The replacement casting may be modified from a newly manufactured singlet casting.Type: GrantFiled: November 20, 2002Date of Patent: June 14, 2005Assignee: General Electric CompanyInventors: Michael Philip Hagle, Brian Alan Norton, James Walter Caddell, Jr.
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Patent number: 6793457Abstract: A method for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and at least one vane. The replacement casting includes a mounting platform formed on one end of the vane and a boss formed on the mounting platform. A collar is joined to the inner band and has a slot formed therein. The boss is then inserted into the slot, and the mounting platform is received in a recess formed in the inner band. Joining is completed by joining the boss to the collar and the mounting platform to the inner band. The thickness of the collar is tapered in an axial direction, and a relief is formed in the collar to provide assembly clearance with adjacent components.Type: GrantFiled: November 15, 2002Date of Patent: September 21, 2004Assignee: General Electric CompanyInventors: James Walter Caddell, Matthew Nicklus Miller, Brian Alan Norton
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Patent number: 6786696Abstract: A turbine blade includes an airfoil and dovetail. The dovetail includes a pair of supporting tangs. A rectangular root block bridges the tangs over a majority of the root end thereof. The block terminates short of one endface of the dovetail to form a root notch thereat for preferentially reducing weight.Type: GrantFiled: May 6, 2002Date of Patent: September 7, 2004Assignee: General Electric CompanyInventors: William Charles Herman, Brian Alan Norton, Brian David Keith
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Publication number: 20040096322Abstract: A method for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and at least one vane. The replacement casting includes a mounting platform formed on one end of the vane and a boss formed on the mounting platform. A collar is joined to the inner band and has a slot formed therein. The boss is then inserted into the slot, and the mounting platform is received in a recess formed in the inner band. Joining is completed by joining the boss to the collar and the mounting platform to the inner band. The thickness of the collar is tapered in an axial direction, and a relief is formed in the collar to provide assembly clearance with adjacent components.Type: ApplicationFiled: November 15, 2002Publication date: May 20, 2004Applicant: General Electric CompanyInventors: James Walter Caddell, Matthew Nicklus Miller, Brian Alan Norton
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Publication number: 20040096323Abstract: A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and a vane. The replacement casting includes an airfoil stub. The airfoil stub is received in a recess formed in the inner band. Joining is completed by joining the airfoil stub to the inner band. The replacement casting may be modified from a newly manufactured singlet casting.Type: ApplicationFiled: November 20, 2002Publication date: May 20, 2004Applicant: General Electric CompanyInventors: Michael Philip Hagle, Brian Alan Norton, James Walter Caddell,
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Publication number: 20030206803Abstract: A turbine blade includes an airfoil and dovetail. The dovetail includes a pair of supporting tangs. A rectangular root block bridges the tangs over a majority of the root end thereof. The block terminates short of one endface of the dovetail to form a root notch thereat for preferentially reducing weight.Type: ApplicationFiled: May 6, 2002Publication date: November 6, 2003Inventors: William Charles Herman, Brian Alan Norton, Brian David Keith
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Patent number: 6561758Abstract: A gas turbine engine includes rotor blades including airfoils that facilitates reducing manufacturing losses due to airfoil trailing edge scarfing. Each airfoil includes a first and second sidewall connected at a leading edge and a trailing edge. The sidewalls define a cooling cavity that includes at least a leading edge chamber bounded by the sidewalls and the airfoil leading edge, and a trailing edge chamber bounded by sidewalls and the airfoil trailing edge. The cooling cavity trailing edge chamber includes a tip region, a throat, and a passageway region connected in flow communication such that the throat is between the tip region and the passageway region. Furthermore, the tip region is bounded by the airfoil tip and extends divergently from the throat, such that a width of the tip region is greater than a width of the throat.Type: GrantFiled: April 27, 2001Date of Patent: May 13, 2003Assignee: General Electric CompanyInventors: Gerard Anthony Rinck, Jonathan Philip Clarke, Brian Alan Norton
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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: 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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Publication number: 20020159888Abstract: A gas turbine engine includes rotor blades including airfoils that facilitates reducing manufacturing losses due to airfoil trailing edge scarfing. Each airfoil includes a first and second sidewall connected at a leading edge and a trailing edge. The sidewalls define a cooling cavity that includes at least a leading edge chamber bounded by the sidewalls and the airfoil leading edge, and a trailing edge chamber bounded by sidewalls and the airfoil trailing edge. The cooling cavity trailing edge chamber includes a tip region, a throat, and a passageway region connected in flow communication such that the throat is between the tip region and the passageway region. Furthermore, the tip region is bounded by the airfoil tip and extends divergently from the throat, such that a width of the tip region is greater than a width of the throat.Type: ApplicationFiled: April 27, 2001Publication date: October 31, 2002Inventors: Gerard Anthony Rinck, Jonathan Philip Clarke, Brian Alan Norton