Patents by Inventor Mark Andrew Jones
Mark Andrew Jones 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: 10577945Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a trailing edge surface and defining a cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud includes a radially inner surface. The tip shroud defines a cooling core fluidly coupled to the cooling passage. The cooling core includes at least one of a first outlet aperture having a first opening defined by the radially inner surface or a second outlet aperture having a second opening defined by the trailing edge surface of the airfoil. The first or second outlet apertures eject coolant from the cooling core in a direction of a local flow of combustion gases external to the tip shroud.Type: GrantFiled: June 30, 2017Date of Patent: March 3, 2020Assignee: General Electric CompanyInventors: Robert Alan Brittingham, Mark Andrew Jones
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Patent number: 10502069Abstract: A rotor blade includes an airfoil defining at least one cooling passage and a camber line extending from a leading edge to a trailing edge. The rotor blade further includes a tip shroud coupled to the airfoil, the tip shroud and the airfoil defining a core fluidly coupled to the at least one cooling passage, the core including a plurality of outlet apertures, each of the plurality of outlet apertures including an opening defined in an exterior surface of the tip shroud. A first outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is between 15 degrees from parallel to and parallel to the camber line at the trailing edge. A second outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is greater than 15 degrees from parallel to the camber line at the trailing edge.Type: GrantFiled: June 7, 2017Date of Patent: December 10, 2019Assignee: General Electric CompanyInventors: Mark Andrew Jones, Bradley Taylor Boyer
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Patent number: 10494932Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of the core and a second portion of the core. The airfoil, the rib, and the radially outer wall partially define a first cooling passage fluidly isolated from the core.Type: GrantFiled: February 7, 2017Date of Patent: December 3, 2019Assignee: General Electric CompanyInventor: Mark Andrew Jones
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Patent number: 10472974Abstract: In one aspect, the present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining at least one cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a core fluidly coupled to the cooling passage. A maximum radial depth of the core is at least six times greater than a minimum hydraulic diameter of a largest cooling passage of the at least one cooling passage.Type: GrantFiled: February 14, 2017Date of Patent: November 12, 2019Assignee: General Electric CompanyInventors: Mark Andrew Jones, James Tyson Balkcum, III
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Patent number: 10436034Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: May 15, 2017Date of Patent: October 8, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Lee Larned Brozyna, Mark Andrew Jones, Matthew Lutz, Srinivasa Govardhan Jayana
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Patent number: 10427213Abstract: A turbine blade includes pressure and suction surfaces connected to define an interior through which coolant is passable. First and second pedestal arrays, each include pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from and directly opposed to pedestals of the second pedestal array by gaps respectively defined therebetween.Type: GrantFiled: February 14, 2017Date of Patent: October 1, 2019Assignee: General Electric CompanyInventors: Tyler Walton Kasperski, Mark Andrew Jones, Jason Adam Neville
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Patent number: 10190417Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric endwall contour proximate a junction between the base and the airfoil.Type: GrantFiled: February 9, 2016Date of Patent: January 29, 2019Assignee: General Electric CompanyInventors: Lee Larned Brozyna, Mehmet Suleyman Ciray, Mark Andrew Jones
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Publication number: 20190003318Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a trailing edge surface and defining a cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud includes a radially inner surface. The tip shroud defines a cooling core fluidly coupled to the cooling passage. The cooling core includes at least one of a first outlet aperture having a first opening defined by the radially inner surface or a second outlet aperture having a second opening defined by the trailing edge surface of the airfoil. The first or second outlet apertures eject coolant from the cooling core in a direction of a local flow of combustion gases external to the tip shroud.Type: ApplicationFiled: June 30, 2017Publication date: January 3, 2019Inventors: Robert Alan Brittingham, Mark Andrew Jones
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Publication number: 20180355729Abstract: A rotor blade includes an airfoil defining at least one cooling passage and a camber line extending from a leading edge to a trailing edge. The rotor blade further includes a tip shroud coupled to the airfoil, the tip shroud and the airfoil defining a core fluidly coupled to the at least one cooling passage, the core including a plurality of outlet apertures, each of the plurality of outlet apertures including an opening defined in an exterior surface of the tip shroud. A first outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is between 15 degrees from parallel to and parallel to the camber line at the trailing edge. A second outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is greater than 15 degrees from parallel to the camber line at the trailing edge.Type: ApplicationFiled: June 7, 2017Publication date: December 13, 2018Inventors: Mark Andrew Jones, Bradley Taylor Boyer
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Publication number: 20180340428Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud defines a core. The tip shroud includes a rib positioned within the core and a radially outer wall. The rib separates a first portion of the core and a second portion of the core. The airfoil, the rib, and the radially outer wall partially define a first cooling passage fluidly isolated from the core.Type: ApplicationFiled: February 7, 2017Publication date: November 29, 2018Inventor: Mark Andrew Jones
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Publication number: 20180328178Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: ApplicationFiled: May 15, 2017Publication date: November 15, 2018Inventors: Lee Larned Brozyna, Mark Andrew Jones, Matthew Lutz, Srinivasa Govardhan Jayana
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Publication number: 20180230813Abstract: In one aspect, the present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining at least one cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a core fluidly coupled to the cooling passage. A maximum radial depth of the core is at least six times greater than a minimum hydraulic diameter of a largest cooling passage of the at least one cooling passage.Type: ApplicationFiled: February 14, 2017Publication date: August 16, 2018Inventors: Mark Andrew Jones, James Tyson Balkcum, III
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Publication number: 20180216474Abstract: The present disclosure is directed to a blade for a turbomachine. The blade includes an airfoil having a pressure side surface and a suction side surface extending from a leading edge to a trailing edge. The airfoil defines a camber line positioned between the pressure side surface and the suction side surface and extending from the leading edge to the trailing edge. A tip shroud couples to the airfoil and defines a cooling cavity therein. The cooling cavity includes one or more turbulators positioned in one or two regions of a forward region, a central region, and an aft region.Type: ApplicationFiled: February 1, 2017Publication date: August 2, 2018Inventor: Mark Andrew Jones
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Patent number: 9995144Abstract: A method for producing a rotating turbine blade and tuning the natural frequencies of the blade is disclosed that changes the second effective beam length of the blade thereby changing the separation between the first natural frequency and the second natural frequency of the blade.Type: GrantFiled: February 18, 2016Date of Patent: June 12, 2018Assignee: General Electric CompanyInventors: Mark Andrew Jones, Lee Larned Brozyna
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Publication number: 20170370088Abstract: A method of controlling the discharge of waste water from a toilet includes the installation of a valve in the discharge outlet of the toilet, the valve including a valve body and a spring-loaded valve closure member that is movable relative to the valve body into an open position during flushing of the toilet against the action of its spring-loading and which is returned to the closed position by the action of its spring-loading on completion of the flushing operation.Type: ApplicationFiled: June 26, 2017Publication date: December 28, 2017Inventors: Mark Andrew Jones, Julie Jones, Joseph Doyle, Maurice Doyle
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Patent number: 9810070Abstract: A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting portion. The airfoil portion further defines the cooling circuit. The turbine rotor blade further includes a platform portion that is disposed radially between the mounting portion and the airfoil. The platform portion includes a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls. A cooling plenum that at least partially defines the cooling circuit is defined within the platform portion. The cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls.Type: GrantFiled: May 15, 2013Date of Patent: November 7, 2017Assignee: General Electric CompanyInventors: David Richard Johns, Mark Andrew Jones
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Publication number: 20170241269Abstract: A method for producing a rotating turbine blade and tuning the natural frequencies of the blade is disclosed that changes the second effective beam length of the blade thereby changing the separation between the first natural frequency and the second natural frequency of the blade.Type: ApplicationFiled: February 18, 2016Publication date: August 24, 2017Inventors: Mark Andrew Jones, Lee Larned Brozyna
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Publication number: 20170226863Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric endwall contour proximate a junction between the base and the airfoil.Type: ApplicationFiled: February 9, 2016Publication date: August 10, 2017Inventors: Lee Larned Brozyna, Mehmet Suleyman Ciray, Mark Andrew Jones
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Patent number: 9695696Abstract: A turbine blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from pedestals of the second pedestal array by gaps respectively defined therebetween.Type: GrantFiled: July 31, 2013Date of Patent: July 4, 2017Assignee: General Electric CompanyInventors: Mark Andrew Jones, Bradley Taylor Boyer, Robert Alan Brittingham, Gregory Thomas Foster, Christopher William Kester
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Patent number: D794163Type: GrantFiled: September 23, 2015Date of Patent: August 8, 2017Assignee: BOXES DIRECT LIMITEDInventors: Mark Andrew Jones, Julie Jones, Joseph Doyle, Maurice Doyle