Patents by Inventor Amid Ansari
Amid Ansari 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: 11927103Abstract: A method of mitigating thermal rotor bow in a rotor assembly of a turbine engine may include performing a plurality of motoring cycles. The plurality of motoring cycles may include receiving feedback on a temperature within a turbine engine in a post-shutdown state, actuating a starter motor when the temperature is greater than a predetermined threshold, operating the starter motor for a motoring time to exhaust some residual heat from the turbine engine, and shutting down the starter motor after the motoring time.Type: GrantFiled: July 12, 2021Date of Patent: March 12, 2024Assignee: General Electric CompanyInventors: Robert Charles Hon, Amid Ansari, Michael Scott McCambridge, Thomas Earl Gillingham
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Patent number: 11686212Abstract: A method of operating a turbine engine that includes shutting down the turbine engine such that a rotational speed of the turbine engine decreases, and actuating a starter motor of the turbine engine at one of as the rotational speed of the turbine engine decreases or at a preset time after the turbine engine receives a full stop command such that residual heat is exhausted from the turbine engine.Type: GrantFiled: May 24, 2016Date of Patent: June 27, 2023Assignee: General Electric CompanyInventors: Robert Charles Hon, Amid Ansari, Michael Scott McCambridge, Thomas Earl Gillingham
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Patent number: 11268446Abstract: A gas turbine engine and method of starting, the gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor. The method comprises an acceleration phase, a bowed-rotor cooling phase, during the acceleration, and a combustion phase. The bowed-rotor cooling phase comprises a time where the rotational speed of the rotor is maintained below a bowed-rotor threshold speed until a non-bowed condition is satisfied, wherein the air forced through the gas turbine engine cools the rotor. The combustion phase occurs after the bowed-rotor cooling phase and upon reaching the combustion speed, wherein fuel is supplied to the gas turbine engine is turned on.Type: GrantFiled: November 14, 2019Date of Patent: March 8, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Joseph Daniel Garrett, III, Mark Edward Linz, Tod Robert Steen, Thomas Charles Swager, Andrew Todd Lehmann, Michael Scott McCambridge, Robert Charles Hon, Thomas Earl Gillingham, Daniel Roy Kiracofe, Kenneth Kirchmayer, Joseph Roger Broda, Kevin Richard Graziano, Steven Alan Ross, Amid Ansari
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Publication number: 20220049619Abstract: A method of mitigating thermal rotor bow in a rotor assembly of a turbine engine may include performing a plurality of motoring cycles. The plurality of motoring cycles may include receiving feedback on a temperature within a turbine engine in a post-shutdown state, actuating a starter motor when the temperature is greater than a predetermined threshold, operating the starter motor for a motoring time to exhaust some residual heat from the turbine engine, and shutting down the starter motor after the motoring time.Type: ApplicationFiled: July 12, 2021Publication date: February 17, 2022Inventors: Robert Charles Hon, Amid Ansari, Michael Scott McCambridge, Thomas Earl Gillingham
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Publication number: 20200240329Abstract: A gas turbine engine and method of starting, the gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor. The method comprises an acceleration phase, a bowed-rotor cooling phase, during the acceleration, and a combustion phase. The bowed-rotor cooling phase comprises a time where the rotational speed of the rotor is maintained below a bowed-rotor threshold speed until a non-bowed condition is satisfied, wherein the air forced through the gas turbine engine cools the rotor. The combustion phase occurs after the bowed-rotor cooling phase and upon reaching the combustion speed, wherein fuel is supplied to the gas turbine engine is turned on.Type: ApplicationFiled: November 14, 2019Publication date: July 30, 2020Inventors: Amid Ansari, Joseph Roger Broda, Thomas Earl Gillingham, Kevin Richard Graziano, Robert Charles Hon, Kenneth Kirchmayer, Daniel Roy Kiracofe, Andrew Todd Lehmann, Michael Scott McCambridge, Tod Robert Steen, Thomas Charles Swager
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Patent number: 10724443Abstract: A method of operating a turbine engine that includes actuating a starter motor of the turbine engine such that a motoring speed of the turbine engine increases, and actuating a plurality of variable stator vanes of the turbine engine such that the plurality of variable stator vanes are at least partially open to control the motoring speed of the turbine engine.Type: GrantFiled: May 24, 2016Date of Patent: July 28, 2020Assignee: General Electric CompanyInventors: Robert Charles Hon, Thomas Charles Swager, Andrew Todd Lehmann, Michael Scott McCambridge, Thomas Earl Gillingham, Joseph Roger Broda, Kevin Richard Graziano, Amid Ansari, Kenneth Lee Kirchmayer, Tod Robert Steen, Daniel Roy Kiracofe
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Patent number: 10502139Abstract: A method of starting a gas turbine engine having a rotor comprising at least a shaft-mounted compressor and turbine, with a casing surrounding the rotor includes an acceleration phase, a bowed-rotor cooling phase, during the acceleration, and a combustion phase. The bowed-rotor cooling phase comprises a time where the rotational speed of the rotor is maintained below a bowed-rotor threshold speed until a non-bowed condition is satisfied, wherein the air forced through the gas turbine engine cools the rotor. The combustion phase occurs after the bowed-rotor cooling phase and upon reaching the combustion speed, wherein fuel is supplied to the gas turbine engine.Type: GrantFiled: January 28, 2015Date of Patent: December 10, 2019Assignee: General Electric CompanyInventors: Steven Alan Ross, Mark Edward Linz, Joseph Daniel Garrett, III, Amid Ansari, Joseph Roger Broda, Thomas Earl Gillingham, Kevin Richard Graziano, Robert Charles Hon, Kenneth Kirchmayer, Daniel Roy Kiracofe, Andrew Todd Lehmann, Michael Scott McCambridge, Tod Robert Steen, Thomas Charles Swager
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Patent number: 10337405Abstract: An apparatus and method of cooling a rotatable member enclosed within a casing are provided. The gas compressor includes a rotor, a plurality of stages of compression extending along said rotor from an inlet stage configured to receive a flow of relatively low pressure gas to an outlet stage configured to discharge a flow of relatively high pressure gas, a casing at least partially surrounding said plurality of stages, and a conduit extending radially inwardly from said casing to an area proximate said rotor.Type: GrantFiled: May 17, 2016Date of Patent: July 2, 2019Assignee: General Electric CompanyInventors: Tod Robert Steen, Amid Ansari, Anthony Paul Greenwood
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Patent number: 10125690Abstract: A start-up system including a control system controlling a partial opening of an air intake valve of a start-up turbine during a first phase of the start-up. The start-up turbine is capable of turning a rotor of the turbomachine for the purpose of the start-up, so as to prevent the rotor from encountering critical frequencies of the turbomachine.Type: GrantFiled: June 25, 2014Date of Patent: November 13, 2018Assignees: AIRBUS OPERATIONS SAS, AIRBUS OPERATIONS S.L., GENERAL ELECTRIC COMPANYInventors: Patrick Zaccaria, Philippe Chareyre, Pio Fernandez-Lopez, Carlos Casado-Montero, Amid Ansari, Thomas Earl Gillingham, Robert Charles Hon, Daniel Roy Kiracofe, Kenneth Kirchmayer, Michael Scott McCambridge, Tod Robert Steen
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Publication number: 20170342908Abstract: A method of operating a turbine engine that includes actuating a starter motor of the turbine engine such that a motoring speed of the turbine engine increases, and actuating a plurality of variable stator vanes of the turbine engine such that the plurality of variable stator vanes are at least partially open to control the motoring speed of the turbine engine.Type: ApplicationFiled: May 24, 2016Publication date: November 30, 2017Inventors: Robert Charles Hon, Thomas Charles Swager, Andrew Todd Lehmann, Michael Scott McCambridge, Thomas Earl Gillingham, Joseph Roger Broda, Kevin Richard Graziano, Amid Ansari, Kenneth Kirchmayer, Tod Robert Steen, Daniel Roy Kiracofe
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Publication number: 20170342855Abstract: A method of operating a turbine engine that includes shutting down the turbine engine such that a rotational speed of the turbine engine decreases, and actuating a starter motor of the turbine engine at one of as the rotational speed of the turbine engine decreases or at a preset time after the turbine engine receives a full stop command such that residual heat is exhausted from the turbine engine.Type: ApplicationFiled: May 24, 2016Publication date: November 30, 2017Inventors: Robert Charles Hon, Amid Ansari, Michael Scott McCambridge, Thomas Earl Gillingham
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Publication number: 20170335768Abstract: An apparatus and method of cooling a rotatable member enclosed within a casing are provided. The gas compressor includes a rotor, a plurality of stages of compression extending along said rotor from an inlet stage configured to receive a flow of relatively low pressure gas to an outlet stage configured to discharge a flow of relatively high pressure gas, a casing at least partially surrounding said plurality of stages, and a conduit extending radially inwardly from said casing to an area proximate said rotor.Type: ApplicationFiled: May 17, 2016Publication date: November 23, 2017Inventors: Tod Robert Steen, Amid Ansari, Anthony Paul Greenwood
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Publication number: 20160348588Abstract: A method of starting a gas turbine engine having a rotor comprising at least a shaft mounted compressor and turbine, with a casing surrounding the rotor.Type: ApplicationFiled: January 28, 2015Publication date: December 1, 2016Inventors: Steven Alan Ross, Mark Edward Linz, Joseph Daniel Garrett, III, Amid Ansari, Joseph Roger Broda, Thomas Earl Gillingham, Kevin Richard Graziano, Robert Charles Hon, Kenneth Kirchmayer, Daniel Roy Kiracofe, Andrew Todd Lehmann, Michael Scott McCambrige, Tod Robert Steen, Thomas Charles Swager
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Publication number: 20090171631Abstract: A method for performing analytical engineering analyses on a plurality of components comprises the steps of: a) performing a first integrated computational process, the first process being comprised of a plurality of computational solvers adapted to compute characteristics of a first component; b) performing a second integrated computational process, the second process being comprised of a plurality of computational solvers adapted to compute characteristics of a second component; and c) communicating results back and forth between corresponding computational solvers of the first and second computational processes; and d) repeating the first and second computational processes.Type: ApplicationFiled: December 27, 2007Publication date: July 2, 2009Inventors: Zaineddin S. Dweik, James Carlton Dudley, Robert N. Pittman, Amid Ansari
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Publication number: 20090171626Abstract: An integrated engineering analysis system comprises: a) a first integrated computational process, the first process being comprised of a plurality of computational solvers adapted to compute characteristics of a first component; b) a second integrated computational process, the second process being comprised of a plurality of computational solvers adapted to compute characteristics of a second component; and c) communication paths between corresponding computational solvers of the first and second computational processes.Type: ApplicationFiled: December 27, 2007Publication date: July 2, 2009Inventors: Zaineddin S. Dweik, James Carlton Dudley, Robert N. Pittman, Amid Ansari
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Publication number: 20070122265Abstract: Apparatus and method of balancing thrust bearing load on a rotor thrust bearing employ a first thrust balance piston cavity for exerting an aft directed thrust balancing force and a second balance piston cavity for exerting an independently controlled forward directed thrust balancing force to allow flexible and wide range balancing of thrust load on the rotor thrust bearing.Type: ApplicationFiled: November 30, 2005Publication date: May 31, 2007Inventors: Amid Ansari, Emil Chouinard, Edward Stiftar