Patents by Inventor Mahmoud Mansour
Mahmoud Mansour 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: 11946474Abstract: A gas turbine engine includes a combustor having a combustor air inlet, an axial-centrifugal compressor, a shroud, a secondary flow duct, and a valve. The shroud surrounds at least a portion of the axial-centrifugal compressor and has a surge bleed plenum defined therein that is in fluid communication with, and receives compressed air from, the axial compressor outlet. The secondary airflow duct has a duct inlet that is in fluid communication with the surge bleed plenum, and a duct outlet that is in fluid communication with the combustor air inlet. The valve is mounted on the secondary airflow duct and is movable between a closed position, in which the secondary airflow duct does not provide fluid communication between the surge bleed plenum and the combustor air inlet, and an open position, in which the secondary airflow duct provides fluid communication between the surge bleed plenum and the combustor air inlet.Type: GrantFiled: October 14, 2021Date of Patent: April 2, 2024Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Bruce David Reynolds, Nick Nolcheff, Mahmoud Mansour, Timothy Darling, Ernest Kurschat
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Publication number: 20230122939Abstract: A gas turbine engine includes a combustor having a combustor air inlet, an axial-centrifugal compressor, a shroud, a secondary flow duct, and a valve. The shroud surrounds at least a portion of the axial-centrifugal compressor and has a surge bleed plenum defined therein that is in fluid communication with, and receives compressed air from, the axial compressor outlet. The secondary airflow duct has a duct inlet that is in fluid communication with the surge bleed plenum, and a duct outlet that is in fluid communication with the combustor air inlet. The valve is mounted on the secondary airflow duct and is movable between a closed position, in which the secondary airflow duct does not provide fluid communication between the surge bleed plenum and the combustor air inlet, and an open position, in which the secondary airflow duct provides fluid communication between the surge bleed plenum and the combustor air inlet.Type: ApplicationFiled: October 14, 2021Publication date: April 20, 2023Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Bruce David Reynolds, Nick Nolcheff, Mahmoud Mansour, Timothy Darling, Ernest Kurschat
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Publication number: 20230090162Abstract: A pharmaceutical composition comprises a metal nanoparticle having an average diameter of about 0.5 nm to about 5 nm. The composition may be used to treat cancer or an anosmia-related disease.Type: ApplicationFiled: November 16, 2022Publication date: March 23, 2023Inventors: Vitaly VODYANOY, Oleg PUSTOVYY, Ludmila GLOBA, Mahmoud MANSOUR, Iryna SOROKULOVA
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Patent number: 11506059Abstract: An impeller associated with a compressor of a gas turbine engine includes a plurality of impeller blades. Each impeller blade of the plurality of impeller blades has a leading edge and a trailing edge opposite the leading edge in a streamwise direction. Each impeller blade of the plurality of impeller blades extends in a spanwise direction from a hub at 0% span to a tip at 100% span, and each impeller blade of the plurality of impeller blades has a plurality of mean camber lines that each extend from the leading edge to the trailing edge at a respective spanwise location. The leading edge includes a partially swept leading edge surface defined between 70% span to 100% span that extends in the streamwise direction between 3% to 15% of a mean camber line at 100% span.Type: GrantFiled: September 23, 2020Date of Patent: November 22, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shailesh Kumar, Shakeel Nasir, Jyotichandra Jingade, Mahmoud Mansour
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Patent number: 11421595Abstract: A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flowpath, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not in operation, but does not occur continuously during engine operation.Type: GrantFiled: October 17, 2019Date of Patent: August 23, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shakeel Nasir, Yogendra Yogi Sheoran, John Schugardt, Daniel Aukland, Mahmoud Mansour, Cristopher Frost, Matt Greenman
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Publication number: 20220042415Abstract: An impeller associated with a compressor of a gas turbine engine includes a plurality of impeller blades. Each impeller blade of the plurality of impeller blades has a leading edge and a trailing edge opposite the leading edge in a streamwise direction. Each impeller blade of the plurality of impeller blades extends in a spanwise direction from a hub at 0% span to a tip at 100% span, and each impeller blade of the plurality of impeller blades has a plurality of mean camber lines that each extend from the leading edge to the trailing edge at a respective spanwise location. The leading edge includes a partially swept leading edge surface defined between 70% span to 100% span that extends in the streamwise direction between 3% to 15% of a mean camber line at 100% span.Type: ApplicationFiled: September 23, 2020Publication date: February 10, 2022Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shailesh Kumar, Shakeel Nasir, Jyotichandra Jingade, Mahmoud Mansour
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Publication number: 20210000868Abstract: A pharmaceutical composition comprises a metal nanoparticle having an average diameter of about 0.5 nm to about 5 nm. The composition may be used to treat cancer or an anosmia-related disease.Type: ApplicationFiled: September 21, 2020Publication date: January 7, 2021Inventors: Vitaly VODYANOY, Oleg PUSTOVYY, Ludmila GLOBA, Mahmoud MANSOUR, Iryna SOROKULOVA
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Patent number: 10816014Abstract: A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.Type: GrantFiled: July 25, 2018Date of Patent: October 27, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shakeel Nasir, John Schugardt, Mahmoud Mansour, Richard Bonvouloir
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Patent number: 10806754Abstract: A pharmaceutical composition comprises a metal nanoparticle having an average diameter of about 0.5 nm to about 5 nm. The composition may be used to treat cancer or an anosmia-related disease.Type: GrantFiled: March 21, 2018Date of Patent: October 20, 2020Assignee: Auburn UniversityInventors: Vitaly Vodyanoy, Oleg Pustovyy, Ludmila Globa, Mahmoud Mansour, Iryna Sorokulova
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Publication number: 20200049069Abstract: A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not operation, but does not occur continuously during engine operation.Type: ApplicationFiled: October 17, 2019Publication date: February 13, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shakeel Nasir, Yogendra Yogi Sheoran, John Schugardt, Daniel Aukland, Mahmoud Mansour, Cristopher Frost, Matt Greenman
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Publication number: 20200032818Abstract: A turbine engine incorporating a fine particle separation means. The turbine engine includes: a compressor, a diffuser, and a flow path positioned downstream from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc that redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the extraction slot also being positioned downstream axially along the flow path from the arc. The turbine engine further includes an aspiration slot, downstream from the extraction slot, that allows air from the plenum to recirculate back into the flow path.Type: ApplicationFiled: July 25, 2018Publication date: January 30, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shakeel Nasir, John Schugardt, Mahmoud Mansour, Richard Bonvouloir
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Patent number: 10359051Abstract: Embodiments of an impeller shroud support for disposition around an impeller are provided, as are embodiments of gas turbine engine including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body, a support arm joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages. Each MIB flow passage includes, in turn, an inlet formed in the shroud body and configured to receive bleed air extracted from the impeller, a throat portion, an outlet formed in the support arm and through which the bleed air is discharged, and a curved intermediate section between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate section turns the bleed air flowing through the MIB passage in a radially outward direction prior to discharge from the outlet of the MIB flow passage.Type: GrantFiled: January 26, 2016Date of Patent: July 23, 2019Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Raymond Gage, Bruce David Reynolds, Jeffrey D. Harrison, Michael Todd Barton, Mahmoud Mansour, Kent L. Kime
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Publication number: 20180271904Abstract: A pharmaceutical composition comprises a metal nanoparticle having an average diameter of about 0.5 nm to about 5 nm. The composition may be used to treat cancer or an anosmia-related disease.Type: ApplicationFiled: March 21, 2018Publication date: September 27, 2018Inventors: Vitaly VODYANOY, Oleg PUSTOVYY, Ludmila GLOBA, Mahmoud MANSOUR, Iryna SOROKULOVA
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Publication number: 20180135516Abstract: A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not operation, but does not occur continuously during engine operation.Type: ApplicationFiled: November 16, 2016Publication date: May 17, 2018Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shakeel Nasir, Yogendra Yogi Sheoran, John Schugardt, Daniel Aukland, Mahmoud Mansour, Cristopher Frost, Matt Greenman
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Publication number: 20170211586Abstract: Embodiments of an impeller shroud support for disposition around an impeller are provided, as are embodiments of gas turbine engine including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body, a support arm joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages. Each MIB flow passage includes, in turn, an inlet formed in the shroud body and configured to receive bleed air extracted from the impeller, a throat portion, an outlet formed in the support arm and through which the bleed air is discharged, and a curved intermediate section between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate section turns the bleed air flowing through the MIB passage in a radially outward direction prior to discharge from the outlet of the MIB flow passage.Type: ApplicationFiled: January 26, 2016Publication date: July 27, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Raymond Gage, Bruce David Reynolds, Jeffrey D. Harrison, Michael Todd Barton, Mahmoud Mansour, Kent L. Kime
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Patent number: 9377030Abstract: Embodiments of a turbomachine, such as a gas turbine engine, are provided. In one embodiment, the turbomachine includes an impeller, a main intake plenum in fluid communication with the inlet of the impeller, and an impeller shroud recirculation system. The impeller shroud recirculation system includes an impeller shroud extending around at least a portion of the impeller and having a shroud port therein. A shroud port cover circumscribes at least a portion of the shroud port and cooperates therewith to at least partially define an impeller recirculation flow path. The impeller recirculation flow path has an outlet positioned to discharge airflow into the main intake plenum at a location radially outboard of the shroud port when pressurized air flows from the impeller, through the shroud port, and into the impeller recirculation flow path during operation of the turbomachine.Type: GrantFiled: March 29, 2013Date of Patent: June 28, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Mark Matwey, Mahmoud Mansour, Yogendra Y. Sheoran
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Publication number: 20140294564Abstract: Embodiments of a turbomachine, such as a gas turbine engine, are provided. In one embodiment, the turbomachine includes an impeller, a main intake plenum in fluid communication with the inlet of the impeller, and an impeller shroud recirculation system. The impeller shroud recirculation system includes an impeller shroud extending around at least a portion of the impeller and having a shroud port therein. A shroud port cover circumscribes at least a portion of the shroud port and cooperates therewith to at least partially define an impeller recirculation flow path. The impeller recirculation flow path has an outlet positioned to discharge airflow into the main intake plenum at a location radially outboard of the shroud port when pressurized air flows from the impeller, through the shroud port, and into the impeller recirculation flow path during operation of the turbomachine.Type: ApplicationFiled: March 29, 2013Publication date: October 2, 2014Applicant: Honeywell International Inc.Inventors: Mark Matwey, Mahmoud Mansour, Yogendra Y. Sheoran
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Patent number: 8602720Abstract: A compressor section includes a rotor platform; a rotor blade extending radially outwardly from the rotor platform, the rotor blade including a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between a leading edge and a trailing edge; a casing having an inner surface surrounding the tip and spaced radially outwardly thereform to define a gap therebetween; a plurality of grooves disposed in the inner surface of the casing and extending in a generally circumferential direction, the plurality of grooves including a first groove and a second groove; and a channel system comprising at least a first channel positioned within the casing and configured to provide fluid communication between the first groove and the second groove.Type: GrantFiled: June 22, 2010Date of Patent: December 10, 2013Assignee: Honeywell International Inc.Inventors: Shraman Narayan Goswami, Mahmoud Mansour, Hasham Hamzamiyan Chougule
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Publication number: 20130051974Abstract: Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction.Type: ApplicationFiled: August 25, 2011Publication date: February 28, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Kin Poon, Jeff Howe, Michael T. Todd Barton, Frank Mignano, Mahmoud Mansour, Nick Nolcheff, Scott Taylor, Steve Trzcinski, Ardeshir Riahi, Jeff Guymon, Alan Hemmingson, Alex Mirzamoghadam
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Publication number: 20110311354Abstract: A compressor section includes a rotor platform; a rotor blade extending radially outwardly from the rotor platform, the rotor blade including a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between a leading edge and a trailing edge; a casing having an inner surface surrounding the tip and spaced radially outwardly thereform to define a gap therebetween; a plurality of grooves disposed in the inner surface of the casing and extending in a generally circumferential direction, the plurality of grooves including a first groove and a second groove; and a channel system comprising at least a first channel positioned within the casing and configured to provide fluid communication between the first groove and the second groove.Type: ApplicationFiled: June 22, 2010Publication date: December 22, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shraman Narayan Goswami, Mahmoud Mansour, Hasham Hamzamiyan Chougule