Patents by Inventor Kapila Jain
Kapila Jain 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: 11118475Abstract: A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.Type: GrantFiled: January 23, 2020Date of Patent: September 14, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Remy Synnott, Mohammed Ennacer, Chris Pater, Denis Blouin, Kapila Jain, Farough Mohammadi
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Patent number: 10815829Abstract: The turbine housing assembly includes a housing surrounding a plurality of turbine shroud segments mounted to support members of the housing. Impingement holes extend through the housing and have outlet openings communicating with a cavity between the shroud segments and the support. A deflector rail protrudes axially away from the support members into the cavity. The deflector rail defines a flow-redirecting surface to redirect the cooling air flow from the impingement holes radially outwardly, away from the turbine shroud segments.Type: GrantFiled: March 9, 2017Date of Patent: October 27, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Kapila Jain, Patricia Phutthavong, Marc Tardif, Ho-Wing Leung
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Publication number: 20200277876Abstract: A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.Type: ApplicationFiled: January 23, 2020Publication date: September 3, 2020Inventors: Remy SYNNOTT, Mohammed ENNACER, Chris PATER, Denis BLOUIN, Kapila JAIN, Farough MOHAMMADI
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Patent number: 10570773Abstract: A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.Type: GrantFiled: December 13, 2017Date of Patent: February 25, 2020Assignee: Pratt & Whitney Canada Corp.Inventors: Remy Synnott, Mohammed Ennacer, Chris Pater, Denis Blouin, Kapila Jain, Farough Mohammadi
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Patent number: 10533454Abstract: A turbine shroud segment comprises a body having an upstream end portion and a downstream end portion relative to a flow of gases through the gas path. A core cavity is defined in the body and extends axially from the upstream end portion to the downstream end portion. A plurality of cooling inlets is defined in the upstream end portion of the body for feeding coolant in the core cavity. A plurality of cooling outlets is defined in the downstream end portion of the body for discharging coolant from the core cavity. Pedestals are provided in the core cavity.Type: GrantFiled: December 13, 2017Date of Patent: January 14, 2020Assignee: Pratt & Whitney Canada Corp.Inventors: Remy Synnott, Mohammed Ennacer, Chris Pater, Denis Blouin, Kapila Jain, Farough Mohammadi
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Patent number: 10502093Abstract: A turbine shroud segment has a body extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A core cavity is defined in the body and extends axially from a front end adjacent the leading edge to a rear end adjacent to the trailing edge. A plurality of cooling inlets and outlets are respectively provided along the front end and the rear end of the core cavity. A crossover wall extends across the core cavity and defines a row of crossover holes configured to accelerate the flow of coolant directed into the core cavity via the cooling inlets. The crossover wall is positioned to accelerate the coolant flow at the beginning of the cooling scheme where the shroud segment is the most thermally solicited.Type: GrantFiled: December 13, 2017Date of Patent: December 10, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Remy Synnott, Mohammed Ennacer, Chris Pater, Denis Blouin, Kapila Jain, Farough Mohammadi
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Publication number: 20190178103Abstract: A turbine shroud segment comprises a body having an upstream end portion and a downstream end portion relative to a flow of gases through the gas path. A core cavity is defined in the body and extends axially from the upstream end portion to the downstream end portion. A plurality of cooling inlets is defined in the upstream end portion of the body for feeding coolant in the core cavity. A plurality of cooling outlets is defined in the downstream end portion of the body for discharging coolant from the core cavity. Pedestals are provided in the core cavity.Type: ApplicationFiled: December 13, 2017Publication date: June 13, 2019Inventors: Remy SYNNOTT, Mohammed ENNACER, Chris PATER, Denis BLOUIN, Kapila JAIN, Farough MOHAMMADI
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Publication number: 20190178101Abstract: A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.Type: ApplicationFiled: December 13, 2017Publication date: June 13, 2019Inventors: Remy SYNNOTT, Mohammed ENNACER, Chris PATER, Denis BLOUIN, Kapila JAIN, Farough MOHAMMADI
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Publication number: 20190178102Abstract: A turbine shroud segment has a body extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A core cavity is defined in the body and extends axially from a front end adjacent the leading edge to a rear end adjacent to the trailing edge. A plurality of cooling inlets and outlets are respectively provided along the front end and the rear end of the core cavity. A crossover wall extends across the core cavity and defines a row of crossover holes configured to accelerate the flow of coolant directed into the core cavity via the cooling inlets. The crossover wall is positioned to accelerate the coolant flow at the beginning of the cooling scheme where the shroud segment is the most thermally solicited.Type: ApplicationFiled: December 13, 2017Publication date: June 13, 2019Inventors: Remy SYNNOTT, Mohammed ENNACER, Chris PATER, Denis BLOUIN, Kapila JAIN, Farough MOHAMMADI
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Publication number: 20180258790Abstract: The turbine housing assembly includes a housing surrounding a plurality of turbine shroud segments mounted to support members of the housing. Impingement holes extend through the housing and have outlet openings communicating with a cavity between the shroud segments and the support. A deflector rail protrudes axially away from the support members into the cavity. The deflector rail defines a flow-redirecting surface to redirect the cooling air flow from the impingement holes radially outwardly, away from the turbine shroud segments.Type: ApplicationFiled: March 9, 2017Publication date: September 13, 2018Inventors: Kapila JAIN, Patricia PHUTTHAVONG, Marc TARDIF, Ho-Wing LEUNG
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Patent number: 8740551Abstract: A blade outer air seal (BOAS) segment has a plurality of cooling passages axially extending through a platform of the BOAS segment. The passages each have an inlet defined in a radially outer surface and an exit defined on a leading edge of the platform. At least one of the passages positioned close to respective circumferential sides of the platform extends linearly from one of the inlets and is skewed away from the axial direction to cool a corner area of the platform.Type: GrantFiled: July 20, 2010Date of Patent: June 3, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Franco Di Paola, Kapila Jain
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Patent number: 8246297Abstract: An cooling arrangement for a turbine shroud provides an air stream directed from a passage extending through a radial wall to impinge on a surface in an area of a back side of the turbine shroud, the surface defining a plane which improves the attack angle of the air stream to the surface.Type: GrantFiled: July 21, 2008Date of Patent: August 21, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Kapila Jain, Marc Tardif
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Publication number: 20110044801Abstract: A blade outer air seal (BOAS) segment has a plurality of cooling passages axially extending through a platform of the BOAS segment. The passages each have an inlet defined in a radially outer surface and an exit defined on a leading edge of the platform. At least one of the passages positioned close to respective circumferential sides of the platform extends linearly from one of the inlets and is skewed away from the axial direction to cool a corner area of the platform.Type: ApplicationFiled: July 20, 2010Publication date: February 24, 2011Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Franco Di Paola, Kapila Jain
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Publication number: 20100014985Abstract: An cooling arrangement for a turbine shroud provides an air stream directed from a passage extending through a radial wall to impinge on a surface in an area of a back side of the turbine shroud, the surface defining a plane which improves the attack angle of the air stream to the surface.Type: ApplicationFiled: July 21, 2008Publication date: January 21, 2010Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Kapila JAIN, Marc TARDIF