Patents by Inventor Nagaraja Rudrapatna
Nagaraja Rudrapatna 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: 11988386Abstract: An injector module includes an injector stem that extends along an injector longitudinal axis between an inlet end and an outlet end of the injector module. The injector module also includes a first fuel line of a first fuel circuit at least partly extending through the injector stem. The first fuel line has a first outlet disposed at the outlet end of the injector stem. The injector module further includes a second fuel line of a second fuel circuit at least partly extending through the injector stem. The second fuel line has a second outlet disposed at the outlet end of the injector stem. The first outlet and the second outlet are spaced apart and have different orientations relative to the injector longitudinal axis. The first fuel line is thermally coupled to the second fuel line.Type: GrantFiled: December 3, 2021Date of Patent: May 21, 2024Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Duane Peterson, Girish Kanakagiri, Jaydeep Basani, Nagaraja Rudrapatna, Paul Yankowich, Richard R. Bohman, Rodolphe Dudebout, Venkatesha Prasad
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Patent number: 11674686Abstract: A coating occlusion resistant effusion cooling hole to form a film of a cooling fluid on a surface of a wall. The cooling hole extends along a longitudinal axis. The cooling hole includes an inlet section defined so as to be spaced apart from the surface. The inlet section is to receive the cooling fluid. The cooling hole includes a metering section fluidly coupled downstream of the inlet section. The cooling hole includes an outlet section fluidly coupled downstream of the metering section. The outlet section includes an overhang portion, a recessed portion, a first sidewall and a second sidewall. The first sidewall and the second sidewall interconnect the overhang portion with the recessed portion along a portion of the outlet section, and the first sidewall and the second sidewall converge and diverge in a plane transverse to the longitudinal axis.Type: GrantFiled: May 11, 2021Date of Patent: June 13, 2023Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Nagaraja Rudrapatna, Rodolphe Dudebout
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Publication number: 20230175696Abstract: An injector module includes an injector stem that extends along an injector longitudinal axis between an inlet end and an outlet end of the injector module. The injector module also includes a first fuel line of a first fuel circuit at least partly extending through the injector stem. The first fuel line has a first outlet disposed at the outlet end of the injector stem. The injector module further includes a second fuel line of a second fuel circuit at least partly extending through the injector stem. The second fuel line has a second outlet disposed at the outlet end of the injector stem. The first outlet and the second outlet are spaced apart and have different orientations relative to the injector longitudinal axis. The first fuel line is thermally coupled to the second fuel line.Type: ApplicationFiled: December 3, 2021Publication date: June 8, 2023Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Duane Peterson, Girish Kanakagiri, Jaydeep Basani, Nagaraja Rudrapatna, Paul Yankowich, Richard R. Bohman, Rodolphe Dudebout, Venkatesha Prasad
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Publication number: 20220364727Abstract: A coating occlusion resistant effusion cooling hole to form a film of a cooling fluid on a surface of a wall. The cooling hole extends along a longitudinal axis. The cooling hole includes an inlet section defined so as to be spaced apart from the surface. The inlet section is to receive the cooling fluid. The cooling hole includes a metering section fluidly coupled downstream of the inlet section. The cooling hole includes an outlet section fluidly coupled downstream of the metering section. The outlet section includes an overhang portion, a recessed portion, a first sidewall and a second sidewall. The first sidewall and the second sidewall interconnect the overhang portion with the recessed portion along a portion of the outlet section, and the first sidewall and the second sidewall converge and diverge in a plane transverse to the longitudinal axis.Type: ApplicationFiled: May 11, 2021Publication date: November 17, 2022Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Nagaraja Rudrapatna, Rodolphe Dudebout
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Publication number: 20220213797Abstract: A low-leakage seal assembly for a turbomachine's combustor-turbine interface. A turbomachine includes a combustion chamber that receives compressed air for combustion from a compressor. The combustion chamber is defined by a combustion liner terminating in a seal ring where the seal ring has an enlarged head that is thicker than the remainder of the seal ring. A transition liner directs combustion gases from the combustion chamber to the turbine and has three walls forming a cavity with an open end. The seal ring extends through the open end and the head nests in the cavity. The transition liner and the seal ring are parts of a low-leakage seal assembly that is exposed on one side to the compressed air and that is exposed on another side to the combustion gases.Type: ApplicationFiled: November 4, 2021Publication date: July 7, 2022Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Nagaraja Rudrapatna, Thomas Bronson, Christopher Zollars
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Publication number: 20220213796Abstract: A low-leakage seal assembly for a turbomachine's combustor-turbine interface. A turbomachine includes a combustion chamber that receives compressed air for combustion from a compressor. The combustion chamber is defined by a combustion liner terminating in a seal ring where the seal ring has an enlarged head that is thicker than the remainder of the seal ring. A transition liner directs combustion gases from the combustion chamber to the turbine and has three walls forming a cavity with an open end. The seal ring extends through the open end and the head nests in the cavity. The transition liner and the seal ring are parts of a low-leakage seal assembly that is exposed on one side to the compressed air and that is exposed on another side to the combustion gases.Type: ApplicationFiled: January 6, 2021Publication date: July 7, 2022Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Nagaraja Rudrapatna, Thomas Bronson, David Chou, Christopher Zollars
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Patent number: 11306659Abstract: An effusion cooling hole for a component associated with a gas turbine engine extends along a longitudinal axis. The effusion cooling hole includes an inlet section spaced apart from a first surface of the component. The inlet section includes a face orientated transverse to the first surface and defines an inlet through the face that has a first diameter. The effusion cooling hole includes an outlet at a second surface of the component and downstream from the inlet section. The effusion cooling hole includes a diverging section downstream from the inlet section and upstream from the outlet. The diverging section is defined substantially external to a thickness of the component, and the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section. The effusion cooling hole includes an intermediate section that fluidly connects the diverging section to the outlet.Type: GrantFiled: May 28, 2019Date of Patent: April 19, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Nagaraja Rudrapatna
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Publication number: 20200378305Abstract: An effusion cooling hole for a component associated with a gas turbine engine extends along a longitudinal axis. The effusion cooling hole includes an inlet section spaced apart from a first surface of the component. The inlet section includes a face orientated transverse to the first surface and defines an inlet through the face that has a first diameter. The effusion cooling hole includes an outlet at a second surface of the component and downstream from the inlet section. The effusion cooling hole includes a diverging section downstream from the inlet section and upstream from the outlet. The diverging section is defined substantially external to a thickness of the component, and the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section. The effusion cooling hole includes an intermediate section that fluidly connects the diverging section to the outlet.Type: ApplicationFiled: May 28, 2019Publication date: December 3, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Nagaraja Rudrapatna
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Patent number: 9897320Abstract: A gas turbine engine combustor is provided. An inner liner has an upstream end and a downstream end and extends in an axial direction between the upstream and downstream ends. A dual wall outer liner has a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end. The outer liner extends in the axial direction between the upstream and downstream ends. A dome assembly is coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner. Effusion cooling holes are disposed in the hot wall, including a first row disposed at a tangential angle of between about 70° and about 90° and a second row disposed at a tangential angle of between about 0° and about 20°.Type: GrantFiled: July 30, 2009Date of Patent: February 20, 2018Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Thomas J. Bronson, Frank Joseph Zupanc, Paul Yankowich, Nagaraja Rudrapatna
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Patent number: 8935925Abstract: A fuel nozzle sheath has a lateral opening for admitting air about a nozzle stem. The stress distribution along the perimeter of the window is smoothed out by increasing the corner radius of the window corner presenting higher stress concentration.Type: GrantFiled: March 22, 2012Date of Patent: January 20, 2015Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan Patel, Nagaraja Rudrapatna
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Patent number: 8794005Abstract: A reverse flow combustor for a gas turbine engine having an outer combustor liner and an inner combustor liner defining an annular combustion chamber, and a compound-angle frustoconical portion in the outer liner having a first and second conical slopes towards an engine centerline.Type: GrantFiled: December 21, 2006Date of Patent: August 5, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Nagaraja Rudrapatna, Oleg Morenko, Bhawan B. Patel
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Patent number: 8695217Abstract: A system for producing a plurality of spaced holes in a component which includes a hole producing machine, a control system in communication with the hole producing machine, and a hole pattern definition module which provides instructions to the control system for operating and controlling the hole producing machine. The hole pattern definition module determines a desired distribution of the holes in the component using predetermined input parameters.Type: GrantFiled: April 5, 2012Date of Patent: April 15, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Nagaraja Rudrapatna, Bhawan Patel
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Patent number: 8555649Abstract: A fuel nozzle air swirler assembly has a slotted cap to provide stress-relief. The stress-relief slits in the cap have an axial and a tangential component to impart a swirl to the air leaking therethrough in the same direction as that of the air exiting the swirler body.Type: GrantFiled: September 2, 2009Date of Patent: October 15, 2013Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Oleg Morenko, Nagaraja Rudrapatna
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Publication number: 20120187095Abstract: A system for producing a plurality of spaced holes in a component which includes a hole producing machine, a control system in communication with the hole producing machine, and a hole pattern definition module which provides instructions to the control system for operating and controlling the hole producing machine. The hole pattern definition module determines a desired distribution of the holes in the component using predetermined input parameters.Type: ApplicationFiled: April 5, 2012Publication date: July 26, 2012Inventors: Nagaraja RUDRAPATNA, Bhawan Patel
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Publication number: 20120174403Abstract: A fuel nozzle sheath has a lateral opening for admitting air about a nozzle stem. The stress distribution along the perimeter of the window is smoothed out by increasing the corner radius of the window corner presenting higher stress concentration.Type: ApplicationFiled: March 22, 2012Publication date: July 12, 2012Inventors: Bhawan Patel, Nagaraja Rudrapatna
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Patent number: 8196410Abstract: A fuel nozzle sheath has a lateral opening for admitting air about a nozzle stern. The stress distribution along the perimeter of the window is smoothed out by increasing the corner radius of the window corner presenting the highest stress concentration. The different corner radii of the window opening in the sheath allows to reduce stresses resulting from the load transferred from the combustor liner to the sheath.Type: GrantFiled: May 18, 2007Date of Patent: June 12, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan Patel, Nagaraja Rudrapatna
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Patent number: 8171634Abstract: A method of producing a plurality of effusion holes in a wall of a combustor of a gas turbine engine comprises: determining a hole pattern definition which provides a functional relationship of the spacing between each adjacent hole within the row of holes; using the hole pattern definition to identify individual positions of the effusion holes to be produced; and using a hole producing system to produce the effusion holes at the identified positions.Type: GrantFiled: July 9, 2007Date of Patent: May 8, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Nagaraja Rudrapatna, Bhawan Patel
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Patent number: 8033113Abstract: A fuel injection system comprises a fuel conveying member and a nozzle tip assembly threadably engaged thereto. A pair of sealing elements is engaged in a fuel passage between the fuel conveying member and the nozzle tip for sealing the junction therebetween. The pair of sealing elements includes a first and a second sealing element located proximate each other and having different cross-sectional shape.Type: GrantFiled: May 15, 2007Date of Patent: October 11, 2011Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Oleg Morenko, Nagaraja Rudrapatna
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Patent number: 7926286Abstract: A fuel injection system for a gas turbine engine having a manifold ring, a plurality of spray tip assemblies and a heat shield including at least two heat shield segments cooperating to at least substantially surround a cross-section of the manifold ring around a circumference of the manifold ring, and detachably retained around the manifold ring through a plurality of removable fasteners.Type: GrantFiled: September 26, 2006Date of Patent: April 19, 2011Assignee: Pratt & Whitney Canada Corp.Inventors: Oleg Morenko, Bhawan B. Patel, Nagaraja Rudrapatna, Saeid Oskooei
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Publication number: 20110048023Abstract: A fuel nozzle air swirler assembly has a slotted cap to provide stress-relief. The stress-relief slits in the cap have an axial and a tangential component to impart a swirl to the air leaking therethrough in the same direction as that of the air exiting the swirler body.Type: ApplicationFiled: September 2, 2009Publication date: March 3, 2011Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Bhawan B. Patel, Oleg Morenko, Nagaraja Rudrapatna