Patents by Inventor CHRIS PATER
CHRIS PATER 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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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: 10662815Abstract: An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.Type: GrantFiled: December 14, 2016Date of Patent: May 26, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Vincent Paradis, Chris Pater
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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: 20170089221Abstract: An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.Type: ApplicationFiled: December 14, 2016Publication date: March 30, 2017Inventors: Vincent PARADIS, Chris PATER
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Patent number: 9556746Abstract: An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.Type: GrantFiled: October 8, 2013Date of Patent: January 31, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Vincent Paradis, Chris Pater
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Publication number: 20150098812Abstract: An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.Type: ApplicationFiled: October 8, 2013Publication date: April 9, 2015Applicant: Pratt & Whitney Canada Corp.Inventors: VINCENT PARADIS, CHRIS PATER