Patents by Inventor David Stampfli
David Stampfli 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: 10823194Abstract: A compressor is provided including a casing, a hub, a flow path, a plurality of blades, and an end-wall treatment formed in at least one of the casing and the hub, and facing a tip of each blade. The flow path is formed between the casing and the hub, and the plurality of blades is positioned in the flow path. The tip of each blade and the end-wall treatment are configured to move relative to each other. Such end-wall treatment includes a first recess portion extending along a first axis to maintain a fluid flow substantially straight through the first recess portion. The end-wall treatment further includes a plurality of second recess portions spaced apart from each other and extending from the first recess portion along a second axis different than the first axis to maintain the fluid flow substantially straight through the plurality of second recess portions.Type: GrantFiled: December 1, 2014Date of Patent: November 3, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Giridhar Jothiprasad, Ramakrishna Venkata Mallina, John David Stampfli, Rudolf Konrad Selmeier, Davide Giacché
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Patent number: 10443611Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.Type: GrantFiled: September 27, 2016Date of Patent: October 15, 2019Assignee: General Electric CompanyInventors: John David Stampfli, Nandakumar Aladahalli Rangaswamy
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Patent number: 10415464Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.Type: GrantFiled: September 21, 2016Date of Patent: September 17, 2019Assignee: General Electric CompanyInventors: John David Stampfli, John David Dyer
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Patent number: 10415585Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.Type: GrantFiled: September 21, 2016Date of Patent: September 17, 2019Assignee: General Electric CompanyInventors: John David Stampfli, John David Dyer
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Patent number: 10047620Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.Type: GrantFiled: December 16, 2014Date of Patent: August 14, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Davide Giacché, John David Stampfli, Ramakrishna Venkata Mallina, Vittorio Michelassi, Giridhar Jothiprasad, Ajay Keshava Rao, Rudolf Konrad Selmeier, Sungho Yoon, Ivan Malcevic
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Publication number: 20180087524Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.Type: ApplicationFiled: September 27, 2016Publication date: March 29, 2018Inventors: JOHN DAVID STAMPFLI, NANDAKUMAR ALADAHALLI RANGASWAMY
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Publication number: 20180080460Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.Type: ApplicationFiled: September 21, 2016Publication date: March 22, 2018Inventors: John David Stampfli, John David Dyer
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Publication number: 20180080459Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.Type: ApplicationFiled: September 21, 2016Publication date: March 22, 2018Inventors: John David Stampfli, John David Dyer
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Patent number: 9790796Abstract: An airfoil is disclosed herein. The airfoil may include a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side. The pressure side may include a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side.Type: GrantFiled: September 19, 2013Date of Patent: October 17, 2017Assignee: General Electric CompanyInventors: John David Stampfli, Ajay Keshava Rao, Rudolf Konrad Selmeier
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Publication number: 20160169017Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.Type: ApplicationFiled: December 16, 2014Publication date: June 16, 2016Inventors: Davide Giacché, John David Stampfli, Ramakrishna Venkata Mallina, Vittorio Michelassi, Giridhar Jothiprasad, Ajay Keshava Rao, Rudolf Konrad Selmeier, Sungho Yoon, Ivan Malcevic
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Publication number: 20160153465Abstract: An axial compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow in the compressor. The one or more endwall treatments having a height formed in an interior surface of a compressor casing or a compressor hub and configured to return a flow adjacent a plurality of rotor blade tips or a plurality of stator blade tips to a cylindrical flow passage upstream of a point of removal of the flow. Each of the endwall treatments defining a front wall, a rear wall, an outer wall extending between the front wall and the rear wall, an axial overhang, an axial overlap, an axial lean angle and a tangential lean angle. The axial overhang extending upstream to overhang at least one of the at least one set of rotor blades or the at least one set of stator blades. The axial overlap extending downstream to overlap at least one of the at least one set of rotor blades or the at least one set of stator blades.Type: ApplicationFiled: December 1, 2014Publication date: June 2, 2016Inventors: Sungho Yoon, John David Stampfli, Ramakrishna Venkata Mallina, Vittorio Michelassi, Giridhar Jothiprasad, Ajay Keshava Rao, Rudolf Konrad Selmeier, Davide Giacché, Ivan Malcevic
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Publication number: 20160153360Abstract: A compressor is provided including a casing, a hub, a flow path, a plurality of blades, and an end-wall treatment formed in at least one of the casing and the hub, and facing a tip of each blade. The flow path is formed between the casing and the hub, and the plurality of blades is positioned in the flow path. The tip of each blade and the end-wall treatment are configured to move relative to each other. Such end-wall treatment includes a first recess portion extending along a first axis to maintain a fluid flow substantially straight through the first recess portion. The end-wall treatment further includes a plurality of second recess portions spaced apart from each other and extending from the first recess portion along a second axis different than the first axis to maintain the fluid flow substantially straight through the plurality of second recess portions.Type: ApplicationFiled: December 1, 2014Publication date: June 2, 2016Inventors: Giridhar Jothiprasad, Ramakrishna Venkata Mallina, John David Stampfli, Rudolf Konrad Selmeier, Davide Giacché
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Publication number: 20150075179Abstract: An airfoil is disclosed herein. The airfoil may include a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side. The pressure side may include a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side.Type: ApplicationFiled: September 19, 2013Publication date: March 19, 2015Applicant: General Electric CompanyInventors: John David Stampfli, Ajay Keshava Rao, Rudolf Konrad Selmeier
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Publication number: 20140130513Abstract: A compressor section of a gas turbine generally includes a stage of inlet guide vanes positioned adjacent to an inlet of the compressor section and a stage of rotor blades disposed downstream from the inlet guide vanes. A stage of stator vanes is positioned downstream from the stage of rotor blades. The stage of stator blades includes a row of leading guide vanes having a trailing edge. A row of trailing guide vanes coupled to an actuator is disposed between two corresponding adjacent leading guide vanes. Each of the trailing guide vanes includes a trailing edge. The leading edge of each trailing guide vane is disposed upstream of the trailing edge of a corresponding leading guide vane when the trailing guide vane is in an open position and downstream from the trailing edge of the corresponding leading guide vane when the trailing guide vane is in a closed position.Type: ApplicationFiled: November 9, 2012Publication date: May 15, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Ya-tien Chiu, John David Stampfli, Rudolf Selmeier
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Patent number: 8322145Abstract: Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.Type: GrantFiled: April 23, 2009Date of Patent: December 4, 2012Assignee: General Electric CompanyInventors: David August Snider, Harold Lamar Jordan, Jr., Timothy Andrew Healy, John David Stampfli
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Publication number: 20100269481Abstract: Systems and methods for providing surge protection to turbine components are provided. A surge protection limit may be determined for the turbine component. One or more measurements associated with operation of the turbine component may be received and provided to a cycle model executed to predict an operating condition of the turbine component. The predicted operating condition of the turbine component may be adjusted based at least in part on the received one or more measurements. The surge protection limit may be adjusted based on the adjusted predicted operating condition of the turbine component.Type: ApplicationFiled: April 23, 2009Publication date: October 28, 2010Applicant: General Electric CompanyInventors: David August Snider, Harold Lamar Jordan, JR., Timothy Andrew Healy, John David Stampfli
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Patent number: 7467926Abstract: Tenth stage stator vanes for a compressor comprise airfoil profiles substantially in accordance with Cartesian coordinate values of x, Y and Z set forth in inches in Table I, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil. X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled to provide a scaled-up or scaled-down airfoil section for each stator vane.Type: GrantFiled: June 9, 2006Date of Patent: December 23, 2008Assignee: General Electric CompanyInventors: John David Stampfli, Josef Scott Cummins
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Publication number: 20070286718Abstract: Tenth stage stator vanes for a compressor comprise airfoil profiles substantially in accordance with Cartesian coordinate values of x, Y and Z set forth in inches in Table I, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil. X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled to provide a scaled-up or scaled-down airfoil section for each stator vane.Type: ApplicationFiled: June 9, 2006Publication date: December 13, 2007Applicant: General Electric CompanyInventors: John David Stampfli, Josef Scott Cummins
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Publication number: 20070177980Abstract: Twelfth stage stator vanes for a compressor comprise airfoil profiles substantially in accordance with Cartesian coordinate values of Z, Y and Z set forth in inches in Table I, wherein the Z coordinate values are perpendicular distances from planes normal to a radius from the compressor centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at a radial aerodynamic section of the airfoil. X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled to provide a scaled-up or scaled-down airfoil section for each stator vane.Type: ApplicationFiled: January 27, 2006Publication date: August 2, 2007Applicant: General Electric CompanyInventors: Christopher Keener, David Stampfli
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Patent number: 7186090Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S–16S, 1R–17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: November 12, 2004Date of Patent: March 6, 2007Assignee: General Electric CompanyInventors: Steven Eric Tomberg, Roger Beharrysingh, Timothy E. DeJoris, William J. Miller, Paul Deivernois, Venkata Siva P. Chaluvadi, Adrian Mircea Mistreanu, Michael James Dutka, Nathan S. Race, Jeffrey Boyd, Christopher David McGowan, Peter Gaines Cleveland, Jason Thomas Harrell, Carl G. Schott, John David Stampfli, Ronald Stuart Denmark, Steven Mark Schirle, Jennifer B. Michenfelder, John F. Ryman