Patents by Inventor Mehmet Suleyman Ciray
Mehmet Suleyman Ciray 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: 11066934Abstract: The present application provides a turbine rotor blade including an airfoil shape and a trailing edge shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, while the trailing edge profile is defined by Table II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance (e.g., inches). The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: March 20, 2020Date of Patent: July 20, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Alexander Stein, Mark Steven Honkomp, Mehmet Suleyman Ciray
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Patent number: 11066935Abstract: Rotor blades and turbomachines are provided. A rotor blade includes a platform and an airfoil extending radially from a root proximate the platform to a tip. The airfoil includes a leading edge and a trailing edge. The airfoil further includes a pressure side surface extending between the leading edge and the trailing edge. The airfoil also includes a suction side surface disposed opposite the pressure side surface and extending between the leading edge and the trailing edge. The leading edge, the trailing edge, the pressure side surface, and the suction side surface collectively define a first profile at the tip and a second profile radially inward from the tip. The first profile includes a suction side overhang, a pressure side overhang, and a pressure side underhang relative to the second profile.Type: GrantFiled: March 20, 2020Date of Patent: July 20, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Alexander Stein, Mark Steven Honkomp, Mehmet Suleyman Ciray
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Patent number: 10934852Abstract: A turbine blade tip cooling system includes a turbine blade having a tip cavity, a tip rail surrounding at least a portion of the tip cavity and at least one internal cooling cavity. The tip rail has an inner rail surface, an outer rail surface, an end surface and at least one tip rail pocket open at the end surface and fluidly connected to the at least one internal cooling cavity that carries a coolant. A tip rail cooling insert attaches to the at least one tip rail pocket, and has insert cooling channel(s) and a coolant collection plenum for directing coolant from the at least one internal cooling cavity to the insert cooling channel(s).Type: GrantFiled: December 3, 2018Date of Patent: March 2, 2021Assignee: General Electric CompanyInventors: Mark Steven Honkomp, Mehmet Suleyman Ciray, Mark Lawrence Hunt
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Publication number: 20200173288Abstract: A turbine blade tip cooling system includes a turbine blade having a tip cavity, a tip rail surrounding at least a portion of the tip cavity and at least one internal cooling cavity. The tip rail has an inner rail surface, an outer rail surface, an end surface and at least one tip rail pocket open at the end surface and fluidly connected to the at least one internal cooling cavity that carries a coolant. A tip rail cooling insert attaches to the at least one tip rail pocket, and has insert cooling channel(s) and a coolant collection plenum for directing coolant from the at least one internal cooling cavity to the insert cooling channel(s).Type: ApplicationFiled: December 3, 2018Publication date: June 4, 2020Inventors: Mark Steven Honkomp, Mehmet Suleyman Ciray, Mark Lawrence Hunt
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Patent number: 10247007Abstract: 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 2, 2017Date of Patent: April 2, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Neil Ristau, Mehmet Suleyman Ciray, Jason Douglas Herzlinger
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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: 20180320527Abstract: 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 2, 2017Publication date: November 8, 2018Inventors: Neil Ristau, Mehmet Suleyman Ciray, Jason Douglas Herzlinger
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Patent number: 9976425Abstract: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; wherein the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.Type: GrantFiled: December 21, 2015Date of Patent: May 22, 2018Assignee: General Electric CompanyInventors: David Wayne Weber, Mehmet Suleyman Ciray, Jacob Charles Perry, II
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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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Publication number: 20170175542Abstract: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; wherein the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.Type: ApplicationFiled: December 21, 2015Publication date: June 22, 2017Inventors: David Wayne Weber, Mehmet Suleyman Ciray, Jacob Charles Perry, II