Patents by Inventor Sanjay S. Hingorani
Sanjay S. Hingorani 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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Publication number: 20240060420Abstract: A turbine blade includes a root, tip, and airfoil. The turbine blade defines a serpentine interior passage having first through third legs, and first and second junctions. The first leg receives pressurized gas from a supply channel of the root. The first leg extends radially and the first junction connects it to the second leg proximate the tip. The second leg extends radially between the first and second junctions. The second junction connects the second and third legs. The third leg extends radially toward the tip. The tip defines cooling apertures open through a pressure side thereof. The cooling apertures include a forward aperture with a forward end opening into the first junction and an aftward end opening through the pressure side surface of the tip at a location that is radially outward of the third leg and axially aftward of at least a portion of the third leg.Type: ApplicationFiled: November 1, 2023Publication date: February 22, 2024Applicant: Mechanical Dynamics and Analysis LLCInventors: Leissner F. POTH, III, Sanjay S. HINGORANI, Bensy SAMUEL
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Patent number: 11840940Abstract: A turbine blade includes a blade tip defining pressure side cooling apertures. The turbine blade defines a serpentine cooling passage having a first, second, and third legs, and first and second junction portions. The first leg extends radially and is connected to the second leg by the first junction portion proximate the blade tip. The second leg extends radially between the first and second junction portions. The second junction portion connects the second leg to the third leg which extends radially toward the blade tip and is connected to a trailing edge cooling aperture to exhaust the gas to an exterior of the turbine blade. The turbine blade defines a plenum connected to the first junction portion. At least one tip cooling aperture connects to the plenum and is radially outward of the third leg and axially aftward of at least a portion of the third leg.Type: GrantFiled: March 9, 2021Date of Patent: December 12, 2023Assignee: Mechanical Dynamics and Analysis LLCInventors: Leissner F. Poth, III, Sanjay S. Hingorani, Bensy Samuel
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Publication number: 20220290568Abstract: A turbine blade includes a blade tip defining pressure side cooling apertures. The turbine blade defines a serpentine cooling passage having a first, second, and third legs, and first and second junction portions. The first leg extends radially and is connected to the second leg by the first junction portion proximate the blade tip. The second leg extends radially between the first and second junction portions. The second junction portion connects the second leg to the third leg which extends radially toward the blade tip and is connected to a trailing edge cooling aperture to exhaust the gas to an exterior of the turbine blade. The turbine blade defines a plenum connected to the first junction portion. At least one tip cooling aperture connects to the plenum and is radially outward of the third leg and axially aftward of at least a portion of the third leg.Type: ApplicationFiled: March 9, 2021Publication date: September 15, 2022Applicant: Mechanical Dynamics and Analysis LLCInventors: Leissner F. POTH, III, Sanjay S. HINGORANI, Bensy SAMUEL
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Patent number: 8997494Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.Type: GrantFiled: October 31, 2012Date of Patent: April 7, 2015Assignee: United Technologies CorporationInventors: Sue-Li Chuang, Yuan Dong, Sanjay S. Hingorani, Dilip Prasad
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Patent number: 8807951Abstract: A blade for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a platform and an airfoil that extends from the platform. The airfoil extends in span between a root and a tip region and in chord between a leading edge and a trailing edge. A sweep angle is defined at the leading edge and a dihedral angle is defined relative to the chord of the airfoil. The sweep angle and the dihedral angle are localized at the tip region and extend over a distance of the airfoil equivalent to about 10% to about 40% of the span.Type: GrantFiled: May 21, 2013Date of Patent: August 19, 2014Assignee: United Technologies CorporationInventors: Jody Kirchner, Yuan Dong, Sanjay S. Hingorani
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Publication number: 20140154087Abstract: A blade for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a platform and an airfoil that extends from the platform. The airfoil extends in span between a root and a tip region and in chord between a leading edge and a trailing edge. A sweep angle is defined at the leading edge and a dihedral angle is defined relative to the chord of the airfoil. The sweep angle and the dihedral angle are localized at the tip region and extend over a distance of the airfoil equivalent to about 10% to about 40% of the span.Type: ApplicationFiled: May 21, 2013Publication date: June 5, 2014Applicant: United Technologies CorporationInventors: Jody Kirchner, Yuan Dong, Sanjay S. Hingorani
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Patent number: 8464426Abstract: A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil.Type: GrantFiled: April 2, 2012Date of Patent: June 18, 2013Assignee: United Technologies CorporationInventors: Jody Kirchner, Yuan Dong, Sanjay S. Hingorani
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Publication number: 20120192421Abstract: A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil.Type: ApplicationFiled: April 2, 2012Publication date: August 2, 2012Inventors: Jody KIRCHNER, Yuan DONG, Sanjay S. HINGORANI
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Patent number: 8167567Abstract: A rotor blade for a gas turbine engine includes an airfoil that extends in span between a root and a tip region. A leading edge and a trailing edge of the airfoil section extend between a chord line of the airfoil. A sweep angle is defined at the leading edge of the airfoil section, and a dihedral angle is defined relative to the chord line of the airfoil section. The sweep angle and the dihedral angle are localized at the tip region of the airfoil section.Type: GrantFiled: December 17, 2008Date of Patent: May 1, 2012Assignee: United Technologies CorporationInventors: Jody Kirchner, Yuan Dong, Sanjay S. Hingorani
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Publication number: 20100150729Abstract: A rotor blade for a gas turbine engine includes an airfoil that extends in span between a root and a tip region. A leading edge and a trailing edge of the airfoil section extend between a chord line of the airfoil. A sweep angle is defined at the leading edge of the airfoil section, and a dihedral angle is defined relative to the chord line of the airfoil section. The sweep angle and the dihedral angle are localized at the tip region of the airfoil section.Type: ApplicationFiled: December 17, 2008Publication date: June 17, 2010Inventors: Jody Kirchner, Yuan Dong, Sanjay S. Hingorani
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Patent number: 7726937Abstract: A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The airfoils have dihedral and sweep.Type: GrantFiled: September 12, 2006Date of Patent: June 1, 2010Assignee: United Technologies CorporationInventors: P. William Baumann, Om Parkash Sharma, Charles R. LeJambre, Sanjay S. Hingorani
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Publication number: 20080063520Abstract: A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The airfoils have dihedral and sweep.Type: ApplicationFiled: September 12, 2006Publication date: March 13, 2008Inventors: P. William Baumann, Om Parkash Sharma, Charles R. LeJambre, Sanjay S. Hingorani