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).

  • Patent number: 9897320
    Abstract: 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: Grant
    Filed: July 30, 2009
    Date of Patent: February 20, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Thomas J. Bronson, Frank Joseph Zupanc, Paul Yankowich, Nagaraja Rudrapatna
  • Patent number: 8935925
    Abstract: 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: Grant
    Filed: March 22, 2012
    Date of Patent: January 20, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan Patel, Nagaraja Rudrapatna
  • Patent number: 8794005
    Abstract: 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: Grant
    Filed: December 21, 2006
    Date of Patent: August 5, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Nagaraja Rudrapatna, Oleg Morenko, Bhawan B. Patel
  • Patent number: 8695217
    Abstract: 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: Grant
    Filed: April 5, 2012
    Date of Patent: April 15, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Nagaraja Rudrapatna, Bhawan Patel
  • Patent number: 8555649
    Abstract: 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: Grant
    Filed: September 2, 2009
    Date of Patent: October 15, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Oleg Morenko, Nagaraja Rudrapatna
  • Publication number: 20120187095
    Abstract: 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: Application
    Filed: April 5, 2012
    Publication date: July 26, 2012
    Inventors: Nagaraja RUDRAPATNA, Bhawan Patel
  • Publication number: 20120174403
    Abstract: 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: Application
    Filed: March 22, 2012
    Publication date: July 12, 2012
    Inventors: Bhawan Patel, Nagaraja Rudrapatna
  • Patent number: 8196410
    Abstract: 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: Grant
    Filed: May 18, 2007
    Date of Patent: June 12, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan Patel, Nagaraja Rudrapatna
  • Patent number: 8171634
    Abstract: 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: Grant
    Filed: July 9, 2007
    Date of Patent: May 8, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Nagaraja Rudrapatna, Bhawan Patel
  • Patent number: 8033113
    Abstract: 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: Grant
    Filed: May 15, 2007
    Date of Patent: October 11, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Oleg Morenko, Nagaraja Rudrapatna
  • Patent number: 7926286
    Abstract: 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: Grant
    Filed: September 26, 2006
    Date of Patent: April 19, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Oleg Morenko, Bhawan B. Patel, Nagaraja Rudrapatna, Saeid Oskooei
  • Publication number: 20110048023
    Abstract: 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: Application
    Filed: September 2, 2009
    Publication date: March 3, 2011
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Morenko, Nagaraja Rudrapatna
  • Publication number: 20110023495
    Abstract: 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: Application
    Filed: July 30, 2009
    Publication date: February 3, 2011
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Thomas J. Bronson, Frank Joseph Zupanc, Paul Yankowich, Nagaraja Rudrapatna
  • Publication number: 20100212324
    Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner. The outer liner is a dual walled liner with a first wall and a second wall. The combustor includes a fuel igniter comprising a tip portion configured to ignite an air and fuel mixture in the combustion chamber and an igniter tube positioning the fuel igniter relative to the combustion chamber. The igniter tube includes a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter.
    Type: Application
    Filed: February 26, 2009
    Publication date: August 26, 2010
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Thomas J. Bronson, Nagaraja Rudrapatna, Jon Kettinger, Frank Joseph Zupanc
  • Publication number: 20100209633
    Abstract: A cylindrical test specimen is provided. The test specimen comprises a metallic sheet curved to form a cylindrical shape, an adhesive layer contacting the metallic sheet, and a thermal barrier coating coupled to the metallic sheet with the adhesive layer, the thermal barrier coating adapted to inhibit thermal transfer.
    Type: Application
    Filed: February 17, 2009
    Publication date: August 19, 2010
    Applicant: Honeywell International Inc.
    Inventors: Daniel Greving, Brian Hann, Jack McIver, Nagaraja Rudrapatna
  • Patent number: 7703289
    Abstract: A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold. The fuel manifold has at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defines at least one location susceptible to overheating between two of the plurality of fuel nozzles. A slot extends through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced.
    Type: Grant
    Filed: September 18, 2006
    Date of Patent: April 27, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Nagaraja Rudrapatna, Oleg Morenko, Bhawan B. Patel
  • Publication number: 20100077758
    Abstract: A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold. The fuel manifold has at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defines at least one location susceptible to overheating between two of the plurality of fuel nozzles. A slot extends through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced.
    Type: Application
    Filed: September 18, 2006
    Publication date: April 1, 2010
    Inventors: Nagaraja RUDRAPATNA, Oleg Morenko, Bhawan B. Patel
  • Patent number: 7559142
    Abstract: A method of manufacturing a heat shield for a manifold ring of a gas turbine engine, comprising forming a tubular portion of heat shield material with an arcuate longitudinal axis, deforming the tubular portion such that a cross-section thereof defines a profile corresponding to at least two complementary heat shield portions configured to cooperate to significantly surround at least a circumferential portion of the manifold ring, and cutting the tubular portion to divide the tubular portion into each of the heat shield portions.
    Type: Grant
    Filed: October 24, 2006
    Date of Patent: July 14, 2009
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Oleg Morenko, Nagaraja Rudrapatna
  • Publication number: 20090126368
    Abstract: 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: Application
    Filed: May 15, 2007
    Publication date: May 21, 2009
    Inventors: BHAWAN B. PATEL, Oleg Morenko, Nagaraja Rudrapatna
  • Publication number: 20090013530
    Abstract: 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: Application
    Filed: July 9, 2007
    Publication date: January 15, 2009
    Inventors: Nagaraja RUDRAPATNA, Shawan Patel