Patents by Inventor Sylvain Pierre
Sylvain Pierre 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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Publication number: 20200131912Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.Type: ApplicationFiled: October 31, 2018Publication date: April 30, 2020Applicant: General Electric CompanyInventors: Melbourne James Myers, Sylvain Pierre, Michael Gordon Sherman, Luke C. Sponseller, Zhirui Dong, Le Trong Tran
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Publication number: 20200131911Abstract: A turbine nozzle having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.Type: ApplicationFiled: October 31, 2018Publication date: April 30, 2020Applicant: General Electric CompanyInventors: Sylvain Pierre, Jinmei Zhang, Dustin James Hall, Marvin Luther Neeley
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Publication number: 20190258388Abstract: In embodiments of objects alignment and distribution layout, an object layout interface includes objects displayed for selection and manipulation. A layout algorithm receives a reposition input for a selected object in the object layout interface, and determines a distribution layout and/or an alignment layout of the objects. The layout algorithm positions the selected object equidistant between at least two of the objects or at a distance from a closest one of the objects, the distance being an equivalent distance of a space between the at least two objects. The space between the objects is displayed as positive space that visually indicates the equidistance between the objects. Alternatively or in addition, the layout algorithm positions the selected object in alignment with multiple objects, and an alignment indication, such as an edge line and/or a distance measurement, is displayed for each instance of the selected object being aligned with the multiple objects.Type: ApplicationFiled: May 6, 2019Publication date: August 22, 2019Applicant: Adobe Inc.Inventors: Robert Christopher Travis, Tomas Krcha, Narciso Batacan Jaramillo, Talin Chris Wadsworth, Sylvain Pierre Galineau, Lawrence Hsu, Anirudh Sasikumar
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Patent number: 10331319Abstract: In embodiments of objects alignment and distribution layout, an object layout interface includes objects displayed for selection and manipulation. A layout algorithm receives a reposition input for a selected object in the object layout interface, and determines a distribution layout and/or an alignment layout of the objects. The layout algorithm positions the selected object equidistant between at least two of the objects or at a distance from a closest one of the objects, the distance being an equivalent distance of a space between the at least two objects. The space between the objects is displayed as positive space that visually indicates the equidistance between the objects. Alternatively or in addition, the layout algorithm positions the selected object in alignment with multiple objects, and an alignment indication, such as an edge line and/or a distance measurement, is displayed for each instance of the selected object being aligned with the multiple objects.Type: GrantFiled: June 29, 2016Date of Patent: June 25, 2019Assignee: Adobe Inc.Inventors: Robert Christopher Travis, Tomas Krcha, Narciso Batacan Jaramillo, Talin Chris Wadsworth, Sylvain Pierre Galineau, Lawrence Hsu, Anirudh Sasikumar
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Patent number: 10253638Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: GrantFiled: August 12, 2015Date of Patent: April 9, 2019Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Santhosh Kumar Vijayan, Spencer Aaron Kareff
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Patent number: 10138736Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: GrantFiled: November 23, 2015Date of Patent: November 27, 2018Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Spencer Aaron Kareff
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Publication number: 20180004401Abstract: In embodiments of objects alignment and distribution layout, an object layout interface includes objects displayed for selection and manipulation. A layout algorithm receives a reposition input for a selected object in the object layout interface, and determines a distribution layout and/or an alignment layout of the objects. The layout algorithm positions the selected object equidistant between at least two of the objects or at a distance from a closest one of the objects, the distance being an equivalent distance of a space between the at least two objects. The space between the objects is displayed as positive space that visually indicates the equidistance between the objects. Alternatively or in addition, the layout algorithm positions the selected object in alignment with multiple objects, and an alignment indication, such as an edge line and/or a distance measurement, is displayed for each instance of the selected object being aligned with the multiple objects.Type: ApplicationFiled: June 29, 2016Publication date: January 4, 2018Applicant: Adobe Systems IncorporatedInventors: Robert Christopher Travis, Tomas Krcha, Narciso Batacan Jaramillo, Talin Chris Wadsworth, Sylvain Pierre Galineau, Lawrence Hsu, Anirudh Sasikumar
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Patent number: 9631500Abstract: An assembly for use in a turbine engine is provided. The assembly includes a first bucket, a second bucket circumferentially adjacent to the first bucket, a shroud extending between the first and second buckets, and an aerodynamic shell substantially encircling the shroud such that a cavity is formed between the aerodynamic shell and the shroud.Type: GrantFiled: October 30, 2013Date of Patent: April 25, 2017Assignee: General Electric CompanyInventors: Sylvain Pierre, Holly Davis Brown
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Patent number: 9500085Abstract: A method for enhancing one or more performance parameters of a gas turbine having at least one row of clocked airfoils may generally include choosing a first, a second and a third row of airfoils where the third row is clocked relative to the first row. An unsteady computational fluid dynamics model may be used to determine at least one wake parameter of a working fluid flowing from the second row of the airfoils to the third row of the airfoils. At least one design parameter of the airfoils of the second row may be modified, and the unsteady computational fluid dynamics model may then be used to determine the effect of the airfoil design parameter modification on the at least one wake parameter. The effect on the wake parameter may be compared to a predetermined target range.Type: GrantFiled: July 23, 2012Date of Patent: November 22, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Paul Kendall Smith, Sylvain Pierre, Dennis Scott Holloway
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Publication number: 20160289805Abstract: A martensitic stainless steel is provided, wherein its composition is: trace amounts?C?0.030%; trace amounts?Si?0.25%; trace amounts?Mn?0.25%; trace amounts?S?0.020%; trace amounts?P?0.040%; 8%?Ni?14%; 8%?Cr?14%; 1.5%?Mo+W/2?3.0%; 1.0%?Al?2.0%; 0.5%?Ti?2.0%; 2%?Co?9%; trace amounts?N?0.030%; trace amounts?O?0.020%; the remainder being iron and impurities resulting from the steelmaking; and its martensitic transformation beginning temperature Ms is calculated by the formula Ms (° C.)=1302?28Si?50Mn?63Ni?42Cr?30Mo+20Al?12Co?25Cu+10[Ti?4(C+N)]??(1) wherein the contents of the various elements are expressed in weight percentages, is greater than or equal to 50° C., preferably greater than or equal to 75° C. A part made in this steel and its manufacturing method are also provided.Type: ApplicationFiled: November 25, 2014Publication date: October 6, 2016Applicant: AUBERT & DUVALInventor: Sylvain Pierre PUECH
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Patent number: 9458732Abstract: Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct assembly further includes an aerodynamic structure defined by the passages of the first transition duct and the second transition duct. The aerodynamic structure includes a pressure side, a suction side, and a trailing edge, the trailing edge having a modified aerodynamic contour.Type: GrantFiled: October 25, 2013Date of Patent: October 4, 2016Assignee: General Electric CompanyInventors: Kevin Weston McMahan, Carl Gerard Schott, Clint Luigie Ingram, Gunnar Leif Siden, Sylvain Pierre
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Patent number: 9291061Abstract: Embodiments of the present disclosure include a turbomachine having a turbomachine blade and a stationary structural component. The turbomachine blade includes a tip shroud having a leading edge portion where the leading edge portion has a first surface. The stationary structural component is disposed about the turbomachine blade and includes a corresponding portion corresponding to the leading edge portion of the tip shroud, where the corresponding portion has a second surface, where the first surface and the second surface have generally parallel contours.Type: GrantFiled: April 13, 2012Date of Patent: March 22, 2016Assignee: General Electric CompanyInventors: Rohit Chouhan, Sylvain Pierre, Gunnar Leif Siden, Santhosh Kumar Vijayan, Joseph Anthony Cotroneo
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Publication number: 20160076385Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: ApplicationFiled: November 23, 2015Publication date: March 17, 2016Inventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Spencer Aaron Kareff
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Publication number: 20150345306Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: ApplicationFiled: August 12, 2015Publication date: December 3, 2015Applicant: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Santhosh Kumar Vijayan, Spencer Aaron Kareff
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Patent number: 9109455Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.Type: GrantFiled: January 20, 2012Date of Patent: August 18, 2015Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Santhosh Kumar Vijayan, Spencer Aaron Kareff
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Publication number: 20150167979Abstract: The present application and the resultant patent provide a disruptive surface on a trailing edge of a stage one nozzle or transition nozzle to promote mixing of respective combustion streams downstream thereof before entry into a first stage bucket of a turbine. For example, in one embodiment, a gas turbine engine may include a combustor having a combustion flow. The gas turbine engine also may include one or more airfoils forming a first stage nozzle or s transition nozzle disposed downstream of the combustor. Moreover, the gas turbine engine may include a flow disruption surface positioned about a trailing edge of the one or more airfoils to promote mixing of the combustion flow.Type: ApplicationFiled: December 17, 2013Publication date: June 18, 2015Applicant: General Electric CompanyInventors: Gunnar Leif Siden, Scott Matthew Sparks, Clint L. Ingram, Sylvain Pierre, Neil Ristau
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Patent number: 9051843Abstract: A turbine blade includes an airfoil portion including a suction side having a suction side contour, a pressure side having a pressure side contour, a leading edge, a trailing edge and a tip portion, and a squeeler pocket formed in the tip portion. The squeeler pocket includes a first side wall and a second side wall. The first side wall includes a first internal surface having a first substantially continuous curvilinear profile and the second side wall includes a second internal surface having a second substantially continuous curvilinear profile. A bleed passage extends from the squeeler pocket towards the trailing edge. The first and second side walls are configured to deliver a substantially unobstructed fluid flow from the squeeler pocket to the bleed passage and limit the fluid flow spillage onto one of the pressure side and the suction side.Type: GrantFiled: October 28, 2011Date of Patent: June 9, 2015Assignee: GENERAL ELECTRIC COMPANYInventors: Alexander Stein, Bradley Taylor Boyer, Sylvain Pierre
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Patent number: 9039375Abstract: Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.Type: GrantFiled: September 1, 2009Date of Patent: May 26, 2015Assignee: GENERAL ELECTRIC COMPANYInventors: Andrew Ray Kneeland, Andres Jose Garcia-Crespo, Bradley T. Boyer, Thomas William Vandeputte, Sylvain Pierre
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Publication number: 20150118062Abstract: An assembly for use in a turbine engine is provided. The assembly includes a first bucket, a second bucket circumferentially adjacent to the first bucket, a shroud extending between the first and second buckets, and an aerodynamic shell substantially encircling the shroud such that a cavity is formed between the aerodynamic shell and the shroud.Type: ApplicationFiled: October 30, 2013Publication date: April 30, 2015Applicant: General Electric CompanyInventors: Sylvain Pierre, Holly Davis Brown
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Publication number: 20150114003Abstract: Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct assembly further includes an aerodynamic structure defined by the passages of the first transition duct and the second transition duct. The aerodynamic structure includes a pressure side, a suction side, and a trailing edge, the trailing edge having a modified aerodynamic contour.Type: ApplicationFiled: October 25, 2013Publication date: April 30, 2015Applicant: General Electric CompanyInventors: Kevin Weston McMahan, Carl Gerard Schott, Clint Luigie Ingram, Gunnar Leif Siden, Sylvain Pierre