Patents by Inventor Jalindar Appa Walunj
Jalindar Appa Walunj 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: 11384640Abstract: A turbine rotor blade including an airfoil that extends from a platform. The platform may include a first portion of a nominal platform contour substantially in accordance with Cartesian coordinate values of X?, Y?, and Z? as set forth in Table II. 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 a Z? axis. The X? and Y? values of the first portion are coordinate values that, when connected by smooth continuing arcs, define contour lines of the first portion of the nominal airfoil profile at each Z? coordinate value. The contour lines may be joined smoothly with one another to form the first portion.Type: GrantFiled: November 26, 2018Date of Patent: July 12, 2022Assignee: General Electric CompanyInventors: Jalindar Appa Walunj, Sylvain Pierre, Prem Venugopal
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Patent number: 11236628Abstract: A turbine nozzle for a gas turbine includes: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs that define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the airfoil profile sections at the Z distances are joined smoothly with one another to form the nominal profile.Type: GrantFiled: January 22, 2021Date of Patent: February 1, 2022Assignee: General Electric CompanyInventors: Neil Devin Ristau, Russell Pierson DeForest, Jalindar Appa Walunj
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Patent number: 10704406Abstract: A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.Type: GrantFiled: June 13, 2017Date of Patent: July 7, 2020Assignee: General Electric CompanyInventors: Jalindar Appa Walunj, Shashwat Swami Jaiswal, Stephen Paul Wassynger, Xiuzhang James Zhang
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Publication number: 20200165918Abstract: A turbine rotor blade including an airfoil that extends from a platform. The platform may include a first portion of a nominal platform contour substantially in accordance with Cartesian coordinate values of X?, Y?, and Z? as set forth in Table II. 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 a Z? axis. The X? and Y? values of the first portion are coordinate values that, when connected by smooth continuing arcs, define contour lines of the first portion of the nominal airfoil profile at each Z? coordinate value. The contour lines may be joined smoothly with one another to form the first portion.Type: ApplicationFiled: November 26, 2018Publication date: May 28, 2020Applicant: General Electric CompanyInventors: Jalindar Appa Walunj, Sylvain Pierre, Prem Venugopal
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Patent number: 10156146Abstract: The present disclosure is directed to an airfoil for a gas turbine rotor blade. The airfoil includes a pressure side wall and a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion. The pressure side wall and the suction side wall collectively define an internal cavity within the airfoil. A plurality of pins is disposed within the internal cavity. The trailing edge portion defines a first cooling passage having a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length. The first length is greater than the second length.Type: GrantFiled: April 25, 2016Date of Patent: December 18, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Jalindar Appa Walunj, Mark Steven Honkomp
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Publication number: 20180355727Abstract: A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.Type: ApplicationFiled: June 13, 2017Publication date: December 13, 2018Inventors: Jalindar Appa Walunj, Shashwat Swami Jaiswal, Stephen Paul Wassynger, Xiuzhang James Zhang
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Patent number: 10001014Abstract: 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 contour proximate a junction between the base and the airfoil.Type: GrantFiled: February 9, 2016Date of Patent: June 19, 2018Assignee: General Electric CompanyInventors: Mark Steven Honkomp, Xiaoyong Fu, Paul Kendall Smith, Jalindar Appa Walunj
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Publication number: 20170306765Abstract: The present disclosure is directed to an airfoil for a gas turbine rotor blade. The airfoil includes a pressure side wall and a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion. The pressure side wall and the suction side wall collectively define an internal cavity within the airfoil. A plurality of pins is disposed within the internal cavity. The trailing edge portion defines a first cooling passage having a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length. The first length is greater than the second length.Type: ApplicationFiled: April 25, 2016Publication date: October 26, 2017Inventors: Jalindar Appa Walunj, Mark Steven Honkomp
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Publication number: 20170226864Abstract: 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 contour proximate a junction between the base and the airfoil.Type: ApplicationFiled: February 9, 2016Publication date: August 10, 2017Inventors: Mark Steven Honkomp, Xiaoyong Fu, Paul Kendall Smith, Jalindar Appa Walunj
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Patent number: 9376922Abstract: An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine is provided. The interior cooling configuration may include a first flow passage and a second flow passage that have a side-by-side configuration for a segment, and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage. The crossover passages may be staggered.Type: GrantFiled: January 9, 2013Date of Patent: June 28, 2016Assignee: General Electric CompanyInventors: Harish Bommanakatte, Jalindar Appa Walunj, Anthony Louis Giglio, Jason Douglas Herzlinger
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Patent number: 8870525Abstract: A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit. The bucket assembly further includes a platform surrounding the main body and at least partially defining a platform cooling circuit. The platform includes a forward portion and an aft portion each extending between a pressure side slash face and a suction side slash face and further includes a forward face, an aft face, and a top face. The bucket assembly further includes a plenum at least partially defined in the platform. The plenum is in fluid communication with the main cooling circuit and extends from the main cooling circuit towards the suction side slash face.Type: GrantFiled: November 4, 2011Date of Patent: October 28, 2014Assignee: General Electric CompanyInventors: Jalindar Appa Walunj, Mark Steven Honkomp, Sergio Daniel Marques Amaral
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Patent number: 8858160Abstract: A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit, and a platform surrounding the main body and at least partially defining a platform cooling circuit. The bucket assembly further includes a passage defined in the main body extending from the exterior surface, the passage connecting the main cooling circuit and the platform cooling circuit, and a plug at least partially disposed in the passage. The plug includes a head and a plunger. The head is configured for preventing a flow through at least a portion of the passage. The plunger has a continuous exterior surface and is configured for allowing a flow between the main cooling circuit and the platform cooling circuit.Type: GrantFiled: November 4, 2011Date of Patent: October 14, 2014Assignee: General Electric CompanyInventors: Jalindar Appa Walunj, Mark Steven Honkomp
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Patent number: 8845289Abstract: A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit, and a platform surrounding the main body and at least partially defining a platform cooling circuit. The platform includes a forward portion and an aft portion each extending between a pressure side slash face and a suction side slash face. The platform further includes a forward face, an aft face, and a top face. The bucket assembly further includes a passage defined in the aft portion of the platform. The passage is in fluid communication with one of the main cooling circuit or the platform cooling circuit.Type: GrantFiled: November 4, 2011Date of Patent: September 30, 2014Assignee: General Electric CompanyInventors: Jalindar Appa Walunj, Mark Steven Honkomp
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Patent number: 8840370Abstract: A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit, and a platform surrounding the main body and at least partially defining a platform cooling circuit. The platform includes a forward portion and an aft portion each extending between a pressure side slash face and a suction side slash face. The platform further includes a forward face, an aft face, and a top face. The bucket assembly further includes a passage defined in the platform generally between the platform cooling circuit and the pressure side slash face and in fluid communication with one of the main cooling circuit or the platform cooling circuit.Type: GrantFiled: November 4, 2011Date of Patent: September 23, 2014Assignee: General Electric CompanyInventors: Jalindar Appa Walunj, Mark Steven Honkomp
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Patent number: 8827642Abstract: A system including: a first turbine segment comprising a first blade coupled to a first shank. The system also includes a second turbine segment including a second blade coupled to a second shank, as well as an elongated flexible seal disposed in a gap between the first and second shanks. The elongated flexible seal includes an opening configured to channel a fluid flow into a hollow region of the elongated flexible seal to induce expansion of the elongated flexible seal in the gap.Type: GrantFiled: January 31, 2011Date of Patent: September 9, 2014Assignee: General Electric CompanyInventors: Jalindar Appa Walunj, Brian Peter Arness, Mark Steven Honkomp, Scott Edmond Ellis, Prashant Shukla, Narayayanaswamy Kuruboor Veerabhadrappa
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Publication number: 20140193273Abstract: An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine is provided. The interior cooling configuration may include a first flow passage and a second flow passage that have a side-by-side configuration for a segment, and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage. The crossover passages may be staggered.Type: ApplicationFiled: January 9, 2013Publication date: July 10, 2014Applicant: General Electric CompanyInventors: Harrish Bommanakatte, Jalindar Appa Walunj, Anthony Louis Giglio, Jason Douglas Herzlinger
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Patent number: 8684695Abstract: A bucket pair in a turbomachine includes a first bucket having an airfoil and a shank; a second adjacent bucket having a second airfoil and a second shank adjacent the first shank; a first axial slot in the first shank; and an elongated, straight damper pin adapted to seat in the first axial slot, the damper pin formed with slanted forward and aft end faces.Type: GrantFiled: January 4, 2011Date of Patent: April 1, 2014Assignee: General Electric CompanyInventors: Jalindar Appa Walunj, Mark Honkomp
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Publication number: 20130115101Abstract: A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit, and a platform surrounding the main body and at least partially defining a platform cooling circuit. The platform includes a forward portion and an aft portion each extending between a pressure side slash face and a suction side slash face. The platform further includes a forward face, an aft face, and a top face. The bucket assembly further includes a passage defined in the aft portion of the platform. The passage is in fluid communication with one of the main cooling circuit or the platform cooling circuit.Type: ApplicationFiled: November 4, 2011Publication date: May 9, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Jalindar Appa Walunj, Mark Steven Honkomp
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Publication number: 20130115102Abstract: A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit, and a platform surrounding the main body and at least partially defining a platform cooling circuit. The platform includes a forward portion and an aft portion each extending between a pressure side slash face and a suction side slash face. The platform further includes a forward face, an aft face, and a top face. The bucket assembly further includes a passage defined in the platform generally between the platform cooling circuit and the pressure side slash face and in fluid communication with one of the main cooling circuit or the platform cooling circuit.Type: ApplicationFiled: November 4, 2011Publication date: May 9, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Jalindar Appa Walunj, Mark Steven Honkomp
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Publication number: 20130115060Abstract: A bucket assembly for a turbine system is disclosed. The bucket assembly includes a main body having an exterior surface and defining a main cooling circuit, and a platform surrounding the main body and at least partially defining a platform cooling circuit. The platform includes a forward portion and an aft portion each extending between a pressure side slash face and a suction side slash face and further includes a forward face, an aft face, and a top face. The platform cooling circuit includes an upper surface and a lower surface. The bucket assembly further includes a passage extending between and providing fluid communication between the main cooling circuit and the platform cooling circuit. An end opening of the passage is defined in the lower surface of the platform cooling circuit.Type: ApplicationFiled: November 4, 2011Publication date: May 9, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Jalindar Appa Walunj, Mark Steven Honkomp, Sergio Daniel Marques Amaral