Patents by Inventor Hasham Hamzamiyan Chougule
Hasham Hamzamiyan Chougule 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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Patent number: 11131210Abstract: A compressor of a gas turbine engine includes an impeller having a plurality of impeller blades. The compressor includes a diffuser downstream from the impeller that has a plurality of diffuser blades. Each diffuser blade extends from a hub to a shroud in a spanwise direction, and a leading edge of each diffuser blade is spaced apart from an impeller trailing edge of each of the plurality of impeller blades by a vaneless gap. Each diffuser blade includes a cutback region that extends from proximate the leading edge toward a trailing edge. The cutback region reduces a thickness of each of the diffuser blades such that a throat area defined between adjacent diffuser blades increases in the spanwise direction from the hub to the shroud and the vaneless gap increases in the spanwise direction from the hub to the shroud.Type: GrantFiled: January 14, 2019Date of Patent: September 28, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shraman Narayan Goswami, Hasham Hamzamiyan Chougule, Jyotichandra Shivaji Roa Jingade, Mohd Abdullah Qizar
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Publication number: 20200224549Abstract: A compressor of a gas turbine engine includes an impeller having a plurality of impeller blades. The compressor includes a diffuser downstream from the impeller that has a plurality of diffuser blades. Each diffuser blade extends from a hub to a shroud in a spanwise direction, and a leading edge of each diffuser blade is spaced apart from an impeller trailing edge of each of the plurality of impeller blades by a vaneless gap. Each diffuser blade includes a cutback region that extends from proximate the leading edge toward a trailing edge. The cutback region reduces a thickness of each of the diffuser blades such that a throat area defined between adjacent diffuser blades increases in the spanwise direction from the hub to the shroud and the vaneless gap increases in the spanwise direction from the hub to the shroud.Type: ApplicationFiled: January 14, 2019Publication date: July 16, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shraman Narayan Goswami, Hasham Hamzamiyan Chougule, Jyotichandra Shivaji Roa Jingade, Mohd Abdullah Qizar
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Patent number: 10669927Abstract: A rotor rotatably mounted within a turbocharger housing includes a turbine wheel and a shaft. The shaft connects the turbine wheel. The hub defines a turbine-wheel back-disk surface facing the portion of the housing containing the bearings, and the hub defines a blade-side surface. The turbine hub and the housing define a turbine-wheel back-disk cavity. The turbine hub forms a ring-shaped primary axial protrusion extending circularly around the turbine-wheel back-disk surface into a circular channel in the housing. The circular channel leads into a bypass that bypasses the turbine blades. A relief flow valve is placed in the bypass. The relief control valve is controlled to open when the bypass pressure is above a cutoff pressure, and close when it is below the cutoff pressure.Type: GrantFiled: November 30, 2017Date of Patent: June 2, 2020Assignee: Garrett Transportation I Inc.Inventors: Kiran.S Rao, Kiran Pithamber, Hasham Hamzamiyan Chougule
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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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Patent number: 10458432Abstract: A compressor assembly of a turbocharger can include a compressor housing that includes a compressor wheel space and a diffuser section that extends from the compressor wheel space to at least one volute; a dual-faced compressor wheel disposed at least in part in the compressor wheel space where the dual-faced compressor wheel includes a first compressor wheel face and a second compressor wheel face oriented back-to-back; and a diffuser section divider disposed at least in part in the diffuser section where the diffuser section divider includes a first side that defines in part a first diffuser that includes a first set of vanes associated with the first compressor wheel face and a second side that defines in part a second diffuser that includes a second set of vanes associated with the second compressor wheel face.Type: GrantFiled: April 25, 2017Date of Patent: October 29, 2019Assignee: Garrett Transportation I Inc.Inventors: Shakeel Nasir, Hasham Hamzamiyan Chougule, Amarnath Balu Rajan
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Publication number: 20190162113Abstract: A rotor rotatably mounted within a turbocharger housing includes a turbine wheel and a shaft. The shaft connects the turbine wheel. The hub defines a turbine-wheel back-disk surface facing the portion of the housing containing the bearings, and the hub defines a blade-side surface. The turbine hub and the housing define a turbine-wheel back-disk cavity. The turbine hub forms a ring-shaped primary axial protrusion extending circularly around the turbine-wheel back-disk surface into a circular channel in the housing. The circular channel leads into a bypass that bypasses the turbine blades. A relief flow valve is placed in the bypass. The relief control valve is controlled to open when the bypass pressure is above a cutoff pressure, and close when it is below the cutoff pressure.Type: ApplicationFiled: November 30, 2017Publication date: May 30, 2019Applicant: Honeywell International Inc.Inventors: Kiran.S Rao, Kiran Pithamber, Hasham Hamzamiyan Chougule
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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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Publication number: 20180306203Abstract: A compressor assembly of a turbocharger can include a compressor housing that includes a compressor wheel space and a diffuser section that extends from the compressor wheel space to at least one volute; a dual-faced compressor wheel disposed at least in part in the compressor wheel space where the dual-faced compressor wheel includes a first compressor wheel face and a second compressor wheel face oriented back-to-back; and a diffuser section divider disposed at least in part in the diffuser section where the diffuser section divider includes a first side that defines in part a first diffuser that includes a first set of vanes associated with the first compressor wheel face and a second side that defines in part a second diffuser that includes a second set of vanes associated with the second compressor wheel face.Type: ApplicationFiled: April 25, 2017Publication date: October 25, 2018Inventors: Shakeel Nasir, Hasham Hamzamiyan Chougule, Amarnath Balu Rajan
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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: 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