Patents by Inventor Parham Zabeti
Parham Zabeti 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: 11533788Abstract: An induction heating system can be adapted for shrink fitting a plurality of different assemblies. A plurality of tooling units associated to respective ones of the assemblies, each one having an appropriately configured induction coil and holder, can be provided. A computer can be used to control the delivery of electrical power to the induction coil in accordance with a heating recipe, and can be provided with an input device for inputting an assembly identifier allowing the computer to operate the control based on the right heating recipe.Type: GrantFiled: May 17, 2021Date of Patent: December 20, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Joseph Swiderski, Guy Beaulieu, Parham Zabeti, Pierre-Luc Lachance
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Publication number: 20220369429Abstract: An induction heating system can be adapted for shrink fitting a plurality of different assemblies. A plurality of tooling units associated to respective ones of the assemblies, each one having an appropriately configured induction coil and holder, can be provided. A computer can be used to control the delivery of electrical power to the induction coil in accordance with a heating recipe, and can be provided with an input device for inputting an assembly identifier allowing the computer to operate the control based on the right heating recipe.Type: ApplicationFiled: May 17, 2021Publication date: November 17, 2022Inventors: Joseph SWIDERSKI, Guy BEAULIEU, Parham ZABETI, Pierre-Luc LACHANCE
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Patent number: 11156504Abstract: A method of measuring a temperature of a part during an assembly process comprises reading the temperature via a reference block that is independently exposed to a same heat source as the part to be monitored.Type: GrantFiled: August 7, 2019Date of Patent: October 26, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Pierre-Luc Lachance, Parham Zabeti, Joao Desouza
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Publication number: 20210041303Abstract: A method of measuring a temperature of a part during an assembly process comprises reading the temperature via a reference block that is independently exposed to a same heat source as the part to be monitored.Type: ApplicationFiled: August 7, 2019Publication date: February 11, 2021Inventors: Pierre-Luc LACHANCE, Parham ZABETI, Joao DESOUZA
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Patent number: 10788209Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.Type: GrantFiled: August 5, 2015Date of Patent: September 29, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Parham Zabeti, Tin Cheung John Hu
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Patent number: 10378774Abstract: In a gas turbine combustor having an inner and outer liner defining an annular combustion chamber, at least an annular scoop ring provided on each inner and outer combustor liner. The annular scoop ring includes a solid radial inner base provided with bores defined therein and communicating with the combustion chamber to form air dilution inlets. The scoop ring has a radial outer portion in the form of a C-shaped scoop open to receive high velocity annular air flow. The bores of the inlets communicating with the scoop portion to direct the air flow into the combustion chamber whereby the bores of the inlets form jet nozzles to generate air jet penetration and direction within the combustion chamber.Type: GrantFiled: October 25, 2013Date of Patent: August 13, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Tin Cheung John Hu, Oleg Morenko, Lev Alexander Prociw, Parham Zabeti
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Patent number: 10208956Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber.Type: GrantFiled: December 15, 2015Date of Patent: February 19, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Parham Zabeti
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Publication number: 20160097535Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber.Type: ApplicationFiled: December 15, 2015Publication date: April 7, 2016Inventors: Lev Alexander Prociw, Parham Zabeti
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Patent number: 9228747Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber.Type: GrantFiled: March 12, 2013Date of Patent: January 5, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Parham Zabeti
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Publication number: 20150338102Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.Type: ApplicationFiled: August 5, 2015Publication date: November 26, 2015Inventors: Lev Alexander Prociw, Parham Zabeti, Tin Cheung John Hu
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Patent number: 9127843Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.Type: GrantFiled: March 12, 2013Date of Patent: September 8, 2015Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Parham Zabeti, Tin Cheung John Hu
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Publication number: 20150113994Abstract: In a gas turbine combustor having an inner and outer liner defining an annular combustion chamber, at least an annular scoop ring provided on each inner and outer combustor liner. The annular scoop ring includes a solid radial inner base provided with bores defined therein and communicating with the combustion chamber to form air dilution inlets. The scoop ring has a radial outer portion in the form of a C-shaped scoop open to receive high velocity annular air flow. The bores of the inlets communicating with the scoop portion to direct the air flow into the combustion chamber whereby the bores of the inlets form jet nozzles to generate air jet penetration and direction within the combustion chamber.Type: ApplicationFiled: October 25, 2013Publication date: April 30, 2015Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Tin Cheung John Hu, Oleg Morenko, Lev Alexander Prociw, Parham Zabeti
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Publication number: 20140260297Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Parham Zabeti
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Publication number: 20140260298Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Parham Zabeti, Tin Cheung John Hu