Patents by Inventor Lakshmanan Valliappan
Lakshmanan Valliappan 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: 10774652Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable table identified as TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape. The resulting article may be used as a stator vane in a compressor.Type: GrantFiled: August 21, 2018Date of Patent: September 15, 2020Assignee: General Electric CompanyInventors: Vasantharuban S, Prem Navin Dhayanandam, Lakshmanan Valliappan
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Patent number: 10436214Abstract: 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 22, 2016Date of Patent: October 8, 2019Assignee: General Electric CompanyInventors: Lakshmanan Valliappan, Ramesh Kempanna Babu, Sagar Kamble
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Patent number: 10415595Abstract: 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 22, 2016Date of Patent: September 17, 2019Assignee: General Electric CompanyInventors: Lakshmanan Valliappan, Ramesh Kempanna Babu
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Publication number: 20190063228Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable table identified as TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape. The resulting article may be used as a stator vane in a compressor.Type: ApplicationFiled: August 21, 2018Publication date: February 28, 2019Inventors: Vasantharuban S, Prem Navin DHAYANANDAM, Lakshmanan VALLIAPPAN
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Patent number: 9951790Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: GrantFiled: September 4, 2015Date of Patent: April 24, 2018Assignee: General Electric CompanyInventors: Lakshmanan Valliappan, Sharan Shanti, Penchala Kumar Mittadodla
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Publication number: 20180080464Abstract: 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 22, 2016Publication date: March 22, 2018Inventors: Lakshmanan Valliappan, Ramesh Kempanna Babu, Sagar Kamble
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Publication number: 20180080474Abstract: 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 22, 2016Publication date: March 22, 2018Inventors: Lakshmanan Valliappan, Ramesh Kempanna Babu
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Publication number: 20170067482Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.Type: ApplicationFiled: September 4, 2015Publication date: March 9, 2017Inventors: Lakshmanan Valliappan, Sharan Shanti, Penchala Kumar Mittadodla
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Patent number: 9546555Abstract: A rotatable blade for use in a turbomachine includes an airfoil portion having a leading edge, a trailing edge a radially-inner end and a radially-outer end; a root section at to the radially-inner end of the airfoil portion, and a part-span shroud located on the airfoil portion between the root section and the radially-outer end. The part-span shroud decreases in width and thickness from decreasing in width and thickness from the airfoil portion to a contact surface adapted to engage a mating contact surface on a part-span shroud of an adjacent blade.Type: GrantFiled: December 17, 2012Date of Patent: January 17, 2017Assignee: General Electric CompanyInventors: Rohit Chouhan, Holly Renae Davis, Lakshmanan Valliappan
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Patent number: 9169782Abstract: A turbine includes a compressor to intake a fluid and to compress the fluid, a combustion chamber to heat the fluid from the compressor, a turbine section to rotate a shaft with the heated fluid from the combustion chamber, and a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section.Type: GrantFiled: January 4, 2012Date of Patent: October 27, 2015Assignee: General Electric CompanyInventors: Moorthi Subramaniyan, Umesh Garg, Joshy John, Lakshmanan Valliappan
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Publication number: 20150063997Abstract: An airfoil includes a radially inner edge extending in a radial direction of the airfoil to a radially outer edge. Also included is a leading edge extending in an axial direction of the airfoil to a trailing edge. Further included is a trailing edge geometry comprising at least one wave segment having simultaneous curvature in at least two directions.Type: ApplicationFiled: August 29, 2013Publication date: March 5, 2015Applicant: General Electric CompanyInventors: Sunil Rajagopal, Moorthi Subramaniyan, Lakshmanan Valliappan
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Patent number: 8834107Abstract: The present application provides a tip clearance control system for reducing an airflow through a turbo machine. The tip clearance control system may include a casing shroud and a tip shroud positioned within the casing shroud. The tip shroud may include a first step at a leading edge and a second step adjacent to the first step. The casing shroud and the tip shroud may define a first cavity therebetween downstream of the second step.Type: GrantFiled: September 27, 2010Date of Patent: September 16, 2014Assignee: General Electric CompanyInventors: Lakshmanan Valliappan, Moorthi Subramanivan
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Publication number: 20140169974Abstract: A rotatable blade for use in a turbomachine includes an airfoil portion having a leading edge, a trailing edge a radially-inner end and a radially-outer end; a root section at to the radially-inner end of the airfoil portion, and a part-span shroud located on the airfoil portion between the root section and the radially-outer end. The part-span shroud decreases in width and thickness from decreasing in width and thickness from the airfoil portion to a contact surface adapted to engage a mating contact surface on a part-span shroud of an adjacent blade.Type: ApplicationFiled: December 17, 2012Publication date: June 19, 2014Applicant: General Electric CompanyInventors: Rohit CHOUHAN, Holly Renae DAVIS, Lakshmanan VALLIAPPAN
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Publication number: 20130280050Abstract: A turbine vibration reduction system includes a nozzle, a bucket in operable communication with the nozzle, and a structure having at least one opening configured to inject fluid into flow traveling past the nozzle and the bucket to disrupt formation of a vortex.Type: ApplicationFiled: April 18, 2012Publication date: October 24, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Asif Iqbal Ansari, Joshy John, Moorthi Subramaniyan, Lakshmanan Valliappan
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Publication number: 20130205795Abstract: A turbomachine includes a housing that defines a flow path, and a stage arranged within the housing. The stage includes a plurality of rotating airfoil members and a first plurality of stationary airfoil members. A second plurality of stationary airfoil members is arranged directly adjacent to the first plurality of stationary airfoil members. A flow improvement system is associated with each of the first and second pluralities of stationary airfoil members. The flow improvement system establishes a predetermined clocking of each of the first plurality of stationary airfoil members relative to each of the second plurality of stationary airfoil members to improve flow characteristics along the flow path.Type: ApplicationFiled: February 9, 2012Publication date: August 15, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Umesh Garg, Akil Abbas Rangwalla, Francesco Soranna, Lakshmanan Valliappan
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Publication number: 20130167551Abstract: A turbine includes a compressor to intake a fluid and to compress the fluid, a combustion chamber to heat the fluid from the compressor, a turbine section to rotate a shaft with the heated fluid from the combustion chamber, and a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section.Type: ApplicationFiled: January 4, 2012Publication date: July 4, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Moorthi Subramaniyan, Umesh Garg, Joshy John, Lakshmanan Valliappan
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Publication number: 20130064665Abstract: A low pressure steam turbine is disclosed including a rotor having: a rotor body; and a plurality of bucket stages disposed axially along the rotor body, the plurality of bucket stages including a last bucket stage; and a nozzle assembly at least partially surrounding the rotor, the nozzle assembly including a plurality of nozzle stages corresponding to the plurality of bucket stages, wherein a nozzle in a nozzle stage axially upstream of the last bucket stage is adjustable to modify a fluid flow within the last bucket stage during operation of the low pressure steam turbine.Type: ApplicationFiled: September 13, 2011Publication date: March 14, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Roy Paul Swintek, Asif Iqbal Ansari, Joshy John, Moorthi Subramaniyan, Lakshmanan Valliappan
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Publication number: 20120076634Abstract: The present application provides a tip clearance control system for reducing an airflow through a turbo machine. The tip clearance control system may include a casing shroud and a tip shroud positioned within the casing shroud. The tip shroud may include a first step at a leading edge and a second step adjacent to the first step. The casing shroud and the tip shroud may define a first cavity therebetween downstream of the second step.Type: ApplicationFiled: September 27, 2010Publication date: March 29, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Lakshmanan Valliappan, Moorthi Subramanivan