Patents by Inventor Alexander MirzaMoghadam
Alexander MirzaMoghadam 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: 11143048Abstract: A labyrinth seal for a gas turbine engine is provided. The labyrinth seal includes a stator and a rotor spaced apart from the stator. The rotor includes a first tooth at a first side having a first radial height, and a second tooth between the first tooth and a second side. The second tooth has a second radial height that is less than the first radial height. The rotor includes a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height. A first clearance between a first tip of the first tooth and the stator is different than a second clearance between a second tip of the second tooth and the stator, and a third clearance between a third tip of the third tooth and the stator is substantially the same as the first clearance.Type: GrantFiled: January 23, 2020Date of Patent: October 12, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Alexander MirzaMoghadam, Hasham Hamzamiyan Chougule, Abhay Naik
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Publication number: 20200157960Abstract: A labyrinth seal for a gas turbine engine is provided. The labyrinth seal includes a stator and a rotor spaced apart from the stator. The rotor includes a first tooth at a first side having a first radial height, and a second tooth between the first tooth and a second side. The second tooth has a second radial height that is less than the first radial height. The rotor includes a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height. A first clearance between a first tip of the first tooth and the stator is different than a second clearance between a second tip of the second tooth and the stator, and a third clearance between a third tip of the third tooth and the stator is substantially the same as the first clearance.Type: ApplicationFiled: January 23, 2020Publication date: May 21, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Alexander MirzaMoghadam, Hasham Hamzamiyan Chougule, Abhay Naik
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Patent number: 10598038Abstract: A labyrinth seal for a gas turbine engine is provided. The labyrinth seal includes a stator and a rotor spaced apart from the stator. The rotor includes a first tooth at a first side having a first radial height, and a second tooth between the first tooth and a second side. The second tooth has a second radial height that is different than the first radial height. The rotor includes a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height. A first clearance between a first tip of the first tooth and the stator is different than a second clearance between a second tip of the second tooth and the stator, and a third clearance between a third tip of the third tooth and the stator is substantially the same as the first clearance.Type: GrantFiled: November 21, 2017Date of Patent: March 24, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Alexander MirzaMoghadam, Hasham Hamzamiyan Chougule, Abhay Naik
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Publication number: 20190153884Abstract: A labyrinth seal for a gas turbine engine is provided. The labyrinth seal includes a stator and a rotor spaced apart from the stator. The rotor includes a first tooth at a first side having a first radial height, and a second tooth between the first tooth and a second side. The second tooth has a second radial height that is different than the first radial height. The rotor includes a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height. A first clearance between a first tip of the first tooth and the stator is different than a second clearance between a second tip of the second tooth and the stator, and a third clearance between a third tip of the third tooth and the stator is substantially the same as the first clearance.Type: ApplicationFiled: November 21, 2017Publication date: May 23, 2019Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Alexander MirzaMoghadam, Hasham Hamzamiyan Chougule, Abhay Naik
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Patent number: 9506365Abstract: Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.Type: GrantFiled: April 21, 2014Date of Patent: November 29, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bradley Reed Tucker, Ardeshir Riahi, Ed Zurmehly, Alexander MirzaMoghadam
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Publication number: 20150300192Abstract: Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.Type: ApplicationFiled: April 21, 2014Publication date: October 22, 2015Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bradley Reed Tucker, Ardeshir Riahi, Ed Zurmehly, Alexander MirzaMoghadam
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Patent number: 8801364Abstract: An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.Type: GrantFiled: June 4, 2010Date of Patent: August 12, 2014Assignee: Honeywell International Inc.Inventors: Mark C. Morris, Alexander MirzaMoghadam, Khosro Molla Hosseini, Kin Poon, Jeff Howe, Alan G. Tiltman
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Publication number: 20140058178Abstract: Apparatus and methods are provided for converting methane in a feed stream to acetylene. A hydrocarbon stream is introduced into a supersonic reactor and pyrolyzed to convert at least a portion of the methane to acetylene. The reactor effluent stream may be treated to convert acetylene to another hydrocarbon process.Type: ApplicationFiled: August 15, 2013Publication date: February 27, 2014Applicant: UOP LLCInventors: Robert L. Bedard, Christopher Naunheimer, Gavin P. Towler, Rodolphe Dudebout, Gregory O. Woodcock, Donald L. Mittendorf, Mark C. Morris, Alexander Mirzamoghadam, Richard V. Hausen
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Publication number: 20140058174Abstract: Apparatus and methods are provided for converting methane in a feed stream to acetylene. A hydrocarbon stream is introduced into a supersonic reactor and pyrolyzed to convert at least a portion of the methane to acetylene. The reactor effluent stream may be treated to convert acetylene to another hydrocarbon process.Type: ApplicationFiled: August 15, 2013Publication date: February 27, 2014Applicant: UOP LLCInventors: Robert L. Bedard, Christopher Naunheimer, Gavin P. Towler, Laura E. Leonard, Rodolphe Dudebout, Gregory O. Woodcock, Donald L. Mittendorf, Mark C. Morris, Richard V. Hausen, Alexander Mirzamoghadam
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Publication number: 20140056766Abstract: Apparatus and methods are provided for converting methane in a feed stream to acetylene. A hydrocarbon stream is introduced into a supersonic reactor and pyrolyzed to convert at least a portion of the methane to acetylene. The reactor effluent stream may be treated to convert acetylene to another hydrocarbon process.Type: ApplicationFiled: August 12, 2013Publication date: February 27, 2014Applicant: UOP LLCInventors: Robert L. Bedard, Christopher Naunheimer, Gavin P. Towler, Laura E. Leonard, Mark C. Morris, Alexander Mirzamoghadam
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Patent number: 8616832Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.Type: GrantFiled: November 30, 2009Date of Patent: December 31, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, Bradley Reed Tucker, Bob Mitlin, Dan Crites, Rajiv Rana, Alexander MirzaMoghadam
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Patent number: 8381533Abstract: An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air. The self-supporting seal plate comprises a plurality of shaped cooling holes in fluid communication with the flow of cooling air emanating from the TOBI. The rotating disk includes a plurality of turbine blade slots formed therein. The plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to the plurality of turbine blades. The plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment and optimized to minimize radial and hoop stresses.Type: GrantFiled: April 30, 2009Date of Patent: February 26, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, Bob Mitlin, Alexander MirzaMoghadam
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Publication number: 20110299972Abstract: An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.Type: ApplicationFiled: June 4, 2010Publication date: December 8, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Mark C. Morris, Alexander MirzaMoghadam, Khosro Molla Hosseini, Kin Poon, Jeff Howe, Alan G. Tiltman
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Publication number: 20110129342Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.Type: ApplicationFiled: November 30, 2009Publication date: June 2, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bradley Reed Tucker, Bob Mitlin, Dan Crites, Rajiv Rana, Alexander MirzaMoghadam
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Publication number: 20100275612Abstract: An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air. The self-supporting seal plate comprises a plurality of shaped cooling holes in fluid communication with the flow of cooling air emanating from the TOBI. The rotating disk includes a plurality of turbine blade slots formed therein. The plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to the plurality of turbine blades. The plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment and optimized to minimize radial and hoop stresses.Type: ApplicationFiled: April 30, 2009Publication date: November 4, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bob Mitlin, Alexander MirzaMoghadam