Patents by Inventor Sumeet Soni
Sumeet Soni 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: 10539032Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine has opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution is defined by values set forth in Table 1, where the throat distribution values are within a +/?10% tolerance of the values set forth in Table 1. The throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.Type: GrantFiled: December 8, 2016Date of Patent: January 21, 2020Assignee: General Electric CompanyInventors: Sumeet Soni, Rohit Chouhan, Ross James Gustafson, Matthew Peter Scoffone
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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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Patent number: 9957804Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.Type: GrantFiled: December 18, 2015Date of Patent: May 1, 2018Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Ross James Gustafson, Nicholas Alvin Hogberg
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Patent number: 9957805Abstract: A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.Type: GrantFiled: December 18, 2015Date of Patent: May 1, 2018Assignee: General Electric CompanyInventors: Sumeet Soni, Ross James Gustafson, Rohit Chouhan, Jason Adam Neville
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Patent number: 9719355Abstract: A method of manufacturing a blade for use with a rotary machine includes coupling a suction-side section of a part-span shroud to a suction-side surface of an airfoil of the blade. A first point of the airfoil suction-side surface, defined where a trailing edge of the suction-side section intersects the airfoil suction-side surface, is upstream from a second point, defined where a throat intersects the airfoil suction-side surface. A third point, defined where a leading edge of the suction-side section intersects the airfoil suction-side surface, is downstream from a fourth point, defined at a leading edge of the blade. The method also includes coupling a pressure-side section of the part-span shroud to a pressure-side surface of the airfoil. A fifth point of the airfoil pressure-side surface, defined where a trailing edge of the pressure-side section intersects the airfoil pressure-side surface, is downstream from the first point.Type: GrantFiled: December 20, 2013Date of Patent: August 1, 2017Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni
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Publication number: 20170175556Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine has opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution is defined by values set forth in Table 1, where the throat distribution values are within a +/?10% tolerance of the values set forth in Table 1. The throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.Type: ApplicationFiled: December 8, 2016Publication date: June 22, 2017Inventors: Sumeet SONI, Rohit CHOUHAN, Ross James GUSTAFSON, Matthew Peter SCOFFONE
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Publication number: 20170175529Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.Type: ApplicationFiled: December 18, 2015Publication date: June 22, 2017Inventors: Rohit Chouhan, Sumeet Soni, Ross James Gustafson, Nicholas Alvin Hogberg
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Publication number: 20170175530Abstract: A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.Type: ApplicationFiled: December 18, 2015Publication date: June 22, 2017Inventors: Sumeet Soni, Ross James Gustafson, Rohit Chouhan, Jason Adam Neville
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Publication number: 20160245095Abstract: A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge, wherein the pressure tip wall and the suction tip wall define a trailing edge tip thickness. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall, the squealer cavity including a trench extending fully to the tip trailing edge to form an open flow path out of the tip trailing edge. Further included is a suction side wall and a pressure side wall extending from a root portion of the turbine rotor blade to the tip portion, wherein the suction side wall and the pressure side wall define a trailing edge blade thickness, the trailing edge tip thickness being greater than the trailing edge blade thickness.Type: ApplicationFiled: February 25, 2015Publication date: August 25, 2016Inventors: Rohit Chouhan, Sumeet Soni, Jason Adam Neville
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Patent number: 9322282Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.Type: GrantFiled: November 30, 2012Date of Patent: April 26, 2016Assignee: General Electric CompanyInventors: Rohit Chouhan, Harish Bommanakatte, Sumeet Soni, Srinivasa Govardhan Jayana, Spencer Aaron Kareff
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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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Patent number: 9097136Abstract: The present application provides a stage of a turbine engine. The stage may include a bucket, a shroud facing the bucket, and a contoured honeycomb seal on the shroud. The contoured honeycomb seal may include a first step with a first shape and a second step with a contoured shape.Type: GrantFiled: January 3, 2012Date of Patent: August 4, 2015Assignee: General Electric CompanyInventors: Rohit Chouhan, Georgia L. Fleming, Sumeet Soni
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Publication number: 20150176411Abstract: A method of manufacturing a blade for use with a rotary machine includes coupling a suction-side section of a part-span shroud to a suction-side surface of an airfoil of the blade. A first point of the airfoil suction-side surface, defined where a trailing edge of the suction-side section intersects the airfoil suction-side surface, is upstream from a second point, defined where a throat intersects the airfoil suction-side surface. A third point, defined where a leading edge of the suction-side section intersects the airfoil suction-side surface, is downstream from a fourth point, defined at a leading edge of the blade. The method also includes coupling a pressure-side section of the part-span shroud to a pressure-side surface of the airfoil. A fifth point of the airfoil pressure-side surface, defined where a trailing edge of the pressure-side section intersects the airfoil pressure-side surface, is downstream from the first point.Type: ApplicationFiled: December 20, 2013Publication date: June 25, 2015Applicant: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni
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Patent number: 8936431Abstract: A shroud for a turbine and a method of assembling is provided. The turbine includes a housing, a rotatable shaft and a bucket extending outward therefrom. The shroud includes an alignment member which is coupled to the housing, wherein the alignment member includes a first end, a second end and a body extending between the first and second ends. The second end includes an arcuate portion to facilitate fluid flow downstream from the bucket. The shroud further includes a seal coupled to the body to facilitate sealing a gap defined between the bucket and the body.Type: GrantFiled: June 8, 2012Date of Patent: January 20, 2015Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni
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Publication number: 20140154079Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.Type: ApplicationFiled: November 30, 2012Publication date: June 5, 2014Applicant: General Electric CompanyInventors: Rohit Chouhan, Harish Bommanakatte, Sumeet Soni, Srinivasa Govardhan Jayana, Spencer Aaron Kareff
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Publication number: 20130330179Abstract: A shroud for a turbine and a method of assembling is provided. The turbine includes a housing, a rotatable shaft and a bucket extending outward therefrom. The shroud includes an alignment member which is coupled to the housing, wherein the alignment member includes a first end, a second end and a body extending between the first and second ends. The second end includes an arcuate portion to facilitate fluid flow downstream from the bucket. The shroud further includes a seal coupled to the body to facilitate sealing a gap defined between the bucket and the body.Type: ApplicationFiled: June 8, 2012Publication date: December 12, 2013Inventors: Rohit Chouhan, Sumeet Soni
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Publication number: 20130189106Abstract: 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: January 20, 2012Publication date: July 25, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Santhosh Kumar Vijayan, Spencer Aaron Kareff