Patents by Inventor Jaisukhlal V. Chokshi
Jaisukhlal V. Chokshi 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: 9890659Abstract: A mid-turbine frame for a gas turbine engine includes a vane assembly supported within a case. The vane assembly directs airflow between a first turbine and a second turbine. A support rod extends through the vane assembly and is secured to the case by a retaining nut. The retaining nut extends through a guide attached to the vane assembly for aligning the vane assembly relative to the case portion.Type: GrantFiled: February 3, 2014Date of Patent: February 13, 2018Assignee: United Technologies CorporationInventor: Jaisukhlal V. Chokshi
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Patent number: 9617870Abstract: A turbine engine assembly, with an axis, includes a vane arrangement segment, a mounting bracket and a strut. The vane arrangement segment includes a first platform segment, a second platform segment and a guide vane that extends radially between and is connected to the first and the second platform segments. The mounting bracket is connected to the vane arrangement segment. The strut extends radially through the first platform segment, the second platform segment and the guide vane, and is engaged with the mounting bracket. The mounting bracket attaches the vane arrangement segment to the strut.Type: GrantFiled: February 4, 2014Date of Patent: April 11, 2017Assignee: United Technologies CorporationInventor: Jaisukhlal V. Chokshi
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Publication number: 20150125291Abstract: A turbine engine assembly, with an axis, includes a vane arrangement segment, a mounting bracket and a strut. The vane arrangement segment includes a first platform segment, a second platform segment and a guide vane that extends radially between and is connected to the first and the second platform segments. The mounting bracket is connected to the vane arrangement segment. The strut extends radially through the first platform segment, the second platform segment and the guide vane, and is engaged with the mounting bracket. The mounting bracket attaches the vane arrangement segment to the strut.Type: ApplicationFiled: February 4, 2014Publication date: May 7, 2015Applicant: United Technologies CorporationInventor: Jaisukhlal V. Chokshi
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Publication number: 20140227078Abstract: A mid-turbine frame for a gas turbine engine includes a vane assembly supported within a case. The vane assembly directs airflow between a first turbine and a second turbine. A support rod extends through the vane assembly and is secured to the case by a retaining nut. The retaining nut extends through a guide attached to the vane assembly for aligning the vane assembly relative to the case portion.Type: ApplicationFiled: February 3, 2014Publication date: August 14, 2014Applicant: United Technologies CorporationInventor: Jaisukhlal V. Chokshi
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Patent number: 8794006Abstract: A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.Type: GrantFiled: July 19, 2012Date of Patent: August 5, 2014Assignee: United Technologies CorporationInventors: Jaisukhlal V. Chokshi, Craig F. Smith, Carlos G. Figueroa, Larry C. George
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Patent number: 8668448Abstract: An example airfoil retention arrangement includes a retention assembly having a first retention segment and a second retention segment. Each of the retention segments is separately moveable to an installed position relative to an airfoil assembly and a support structure. The retention segments each have a portion position between a lip of the airfoil assembly and a collar of the support structure when the retention segments are in the installed position. The retention assembly is configured to limit radial movement of an airfoil relative to the support structure when in the installed position.Type: GrantFiled: October 29, 2010Date of Patent: March 11, 2014Assignee: United Technologies CorporationInventors: Jorge I. Farah, Jaisukhlal V. Chokshi
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Publication number: 20130000310Abstract: A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.Type: ApplicationFiled: July 19, 2012Publication date: January 3, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jaisukhlal V. Chokshi, Craig F. Smith, Carlos G. Figueroa, Larry C. George
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Patent number: 8291711Abstract: A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.Type: GrantFiled: July 25, 2008Date of Patent: October 23, 2012Assignee: United Technologies CorporationInventors: Jaisukhlal V. Chokshi, Craig F. Smith, Carlos G. Figueroa, Larry C. George
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Patent number: 8245514Abstract: A combustion duct assembly has a transition duct and a combustion liner having a hula seal at a downstream end that is forced within an inner wall of the transition duct. The combustion liner is held within the transition duct by the hula seal, but allowed to move relative to the transition duct. The combustion liner is formed with heat transfer columns adjacent the downstream end, and radially inwardly of the hula seal.Type: GrantFiled: July 10, 2008Date of Patent: August 21, 2012Assignee: United Technologies CorporationInventors: John S. Tu, Craig F. Smith, Jaisukhlal V. Chokshi
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Publication number: 20120107124Abstract: An example airfoil retention arrangement includes a retention assembly having a first retention segment and a second retention segment. Each of the retention segments is separately moveable to an installed position relative to an airfoil assembly and a support structure. The retention segments each have a portion position between a lip of the airfoil assembly and a collar of the support structure when the retention segments are in the installed position. The retention assembly is configured to limit radial movement of an airfoil relative to the support structure when in the installed position.Type: ApplicationFiled: October 29, 2010Publication date: May 3, 2012Inventors: Jorge I. Farah, Jaisukhlal V. Chokshi
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Patent number: 8166764Abstract: A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes. The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes for directing axial air flow and radial flow chambers for directing radial air flow.Type: GrantFiled: July 21, 2008Date of Patent: May 1, 2012Assignee: United Technologies CorporationInventors: Jaisukhlal V. Chokshi, Craig F. Smith, Carlos G. Figueroa
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Patent number: 8109099Abstract: A combustion duct for a gas turbine engine has a combustion liner to receive products of combustion, and deliver the products of combustion downstream toward a turbine rotor. An outer housing is positioned radially outwardly of the combustion liner. A flow sleeve is positioned radially intermediate the outer housing and the combustion liner. A chamber radially outwardly of the flow sleeve receives cooling air. A plurality of holes through the flow sleeve deliver cooling air from the chamber against an outer periphery of the combustion liner. A plurality of tabs are associated with at least some of the holes in the flow sleeve. The tabs are positioned to extend radially inwardly on a downstream side of the holes.Type: GrantFiled: July 9, 2008Date of Patent: February 7, 2012Assignee: United Technologies CorporationInventors: John S. Tu, Jaisukhlal V. Chokshi, Christopher R. Brdar, Randal G. McKinney, Shakira A. Ramos
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Publication number: 20100031666Abstract: A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.Type: ApplicationFiled: July 25, 2008Publication date: February 11, 2010Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jaisukhlal V. Chokshi, Craig F. Smith, Carlos G. Figueroa, Larry C. George
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Publication number: 20100031665Abstract: A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes. The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes for directing axial air flow and radial flow chambers for directing radial air flow.Type: ApplicationFiled: July 21, 2008Publication date: February 11, 2010Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jaisukhlal V. Chokshi, Craig F. Smith, Carlos G. Figueroa
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Publication number: 20100005805Abstract: A combustion duct for a gas turbine engine has a combustion liner to receive products of combustion, and deliver the products of combustion downstream toward a turbine rotor. An outer housing is positioned radially outwardly of the combustion liner. A flow sleeve is positioned radially intermediate the outer housing and the combustion liner. A chamber radially outwardly of the flow sleeve receives cooling air. A plurality of holes through the flow sleeve deliver cooling air from the chamber against an outer periphery of the combustion liner. A plurality of tabs are associated with at least some of the holes in the flow sleeve. The tabs are positioned to extend radially inwardly on a downstream side of the holes.Type: ApplicationFiled: July 9, 2008Publication date: January 14, 2010Inventors: John S. Tu, Jaisukhlal V. Chokshi, Christopher R. Brdar, Randal G. McKinney, Shakira A. Ramos
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Publication number: 20100005803Abstract: A combustion duct assembly has a transition duct and a combustion liner having a hula seal at a downstream end that is forced within an inner wall of the transition duct. The combustion liner is held within the transition duct by the hula seal, but allowed to move relative to the transition duct. The combustion liner is formed with heat transfer columns adjacent the downstream end, and radially inwardly of the hula seal.Type: ApplicationFiled: July 10, 2008Publication date: January 14, 2010Inventors: John S. Tu, Craig F. Smith, Jaisukhlal V. Chokshi