Patents by Inventor Narendra Digamber Joshi

Narendra Digamber Joshi 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).

  • Publication number: 20190309951
    Abstract: A combustor includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.
    Type: Application
    Filed: May 23, 2018
    Publication date: October 10, 2019
    Applicant: General Electric Company
    Inventors: Narendra Digamber Joshi, Shawn David Wehe, ShihYang Hsieh, Changjin Yoon, Owen James Sullivan Rickey, Joseph Douglas Monty
  • Patent number: 10381889
    Abstract: A permanent magnet machine and a rotor assembly for the permanent magnet machine. The permanent magnet machine includes a stator assembly including a stator core configured to generate a magnetic field and extending along a longitudinal axis with an inner surface defining a cavity and a rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and configured to rotate about the longitudinal axis. The rotor assembly further including a plurality of permanent magnets for generating a magnetic field which interacts with the stator magnetic field to produce torque. The permanent magnets are disposed within one or more cavities formed in a sleeve component. The sleeve component configured to include a plurality of cavities or voids therein and thus provide minimal weight to the permanent magnet machine. The permanent magnet machine providing increased centrifugal load capacity, increased power density and improved electrical performance.
    Type: Grant
    Filed: June 27, 2014
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: Narendra Digamber Joshi, Manoj Ramprasad Shah, James William Bray, Randy Marinus Vondrell, Kurt David Murrow, Jeffrey Anthony Hamel, Samuel Jacob Martin
  • Patent number: 10371064
    Abstract: A method of operating a gas turbine engine includes measuring an exhaust gas temperature of the gas turbine engine. A first stage turbine nozzle assembly of the gas turbine engine is adjusted to a first position. A firing temperature of the gas turbine engine is determined based on the exhaust gas temperature. The firing temperature is compared to a threshold value and a difference value is determined therefrom. If the difference value exceeds a threshold value, the first stage turbine nozzle assembly is adjusted to a second position such that the firing temperature is substantially equal to the threshold value.
    Type: Grant
    Filed: February 11, 2016
    Date of Patent: August 6, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Narendra Digamber Joshi, Krishan Lal Luthra
  • Publication number: 20190226398
    Abstract: Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.
    Type: Application
    Filed: September 17, 2018
    Publication date: July 25, 2019
    Inventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi, Peter Daniel Silkowski
  • Patent number: 10323532
    Abstract: The present disclosure generally relates to variable cellular structures, methods of making such cellular structures, and variable cellular flow discouragers for turbine engines for jet aircraft.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: June 18, 2019
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Narendra Digamber Joshi, Samar Jyoti Kalita, Paul Marsland, Wayne Spence
  • Publication number: 20190165652
    Abstract: An electric machine comprising a rotor, a stator, a plurality of bare conductors forming a plurality of windings in at least one of the stator and the rotor, and a fluid in direct physical contact with a plurality of outer surfaces of the plurality of bare conductors, wherein the fluid is electrically insulating and provides direct fluid cooling, to provide cooling for the plurality of bare conductors and electrical insulation between consecutive bare conductors of the plurality of bare conductors
    Type: Application
    Filed: November 30, 2017
    Publication date: May 30, 2019
    Inventors: Anoop Kumar Jassal, Mohamed Osama, Francesco Papini, Narendra Digamber Joshi
  • Patent number: 10288291
    Abstract: An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.
    Type: Grant
    Filed: August 15, 2014
    Date of Patent: May 14, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sarah Marie Monahan, Joel Meier Haynes, Narendra Digamber Joshi, David James Walker, Junwoo Lim, Krishna Kumar Venkatesan
  • Publication number: 20190136761
    Abstract: An integrated fuel cell and engine combustor assembly includes an engine combustor having a combustion chamber fluidly coupled with a compressor and a turbine. The assembly also includes a fuel cell stack circumferentially extending around the combustion chamber of the combustor. The fuel cell stack includes fuel cells configured to generate electric current. The fuel cell stack is positioned to receive discharged air from the compressor and fuel from a fuel manifold. The fuel cells in the fuel cell stack generate electric current using the discharged air and at least some of the fuel. The fuel cell stack is positioned to radially direct partially oxidized fuel from the fuel cells into the combustion chamber of the combustor. The combustor combusts the partially oxidized fuel into one or more gaseous combustion products that are directed into and drive the downstream turbine.
    Type: Application
    Filed: November 7, 2017
    Publication date: May 9, 2019
    Inventors: Andrew Philip Shapiro, Narendra Digamber Joshi
  • Patent number: 10280760
    Abstract: A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: May 7, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Narendra Digamber Joshi, Christian Lee Vandervort, Krishan Lal Luthra, Ronald Scott Bunker, Joel Meier Haynes, Venkat Eswarlu Tangirala
  • Publication number: 20190128529
    Abstract: A rotating detonation combustion system is generally provided. The rotating detonation combustion system includes an outer wall, an upstream wall, and a radial wall. The outer wall is defined circumferentially around a combustor centerline extended along a lengthwise direction. The outer wall defines a first radius portion generally upstream along the outer wall. A second radius portion is defined generally downstream along the outer wall and a transition portion is defined between the first and second radius portions. The first radius portion defines a first radius greater than a second radius at the second radius portion. The transition portion defines a generally decreasing radius from the first radius portion to the second radius portion. The upstream wall is defined circumferentially around the combustor centerline and is extended along the lengthwise direction and inward radially of the first radius portion of the outer wall. An oxidizer passage is defined within the upstream wall.
    Type: Application
    Filed: October 27, 2017
    Publication date: May 2, 2019
    Inventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi
  • Publication number: 20190120492
    Abstract: A fuel and air injection handling system for a rotating detonation engine is provided. The system includes a compressor configured to compress air received via a compressor inlet and configured to output the air that is compressed as swirling, compressed air through a compressor outlet. The system also includes an annular rotating detonation combustor fluidly coupled with the compressor outlet. The annular rotating detonation combustor has a detonation cavity that extends around an annular axis, the annular rotating detonation combustor configured to combust the compressed air from the compressor in detonations that rotate within the detonation cavity around the annular axis of the annular rotating detonation combustor. The annular rotating detonation combustor is fluidly and directly coupled with the compressor outlet.
    Type: Application
    Filed: October 18, 2018
    Publication date: April 25, 2019
    Inventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi
  • Publication number: 20190086091
    Abstract: A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.
    Type: Application
    Filed: September 15, 2017
    Publication date: March 21, 2019
    Inventors: Owen James Sullivan Rickey, Venkat Eswarlu Tangirala, Narendra Digamber Joshi, Shashank Yellapantula
  • Publication number: 20190086086
    Abstract: A cavity stabilized detonation combustor assembly for a rotating detonation engine includes opposing inner and outer walls that are radially spaced apart from each other and that both extend around a center axis of the rotating detonation engine. Detonations in the rotating detonation engine rotate around the center axis of the rotating detonation engine. The assembly also includes opposing leading and trailing cavity walls that are coupled with the inner and outer walls and which radially extend away from the center axis, and an axial wall that is coupled with and connects the leading and trailing cavity walls with each other. The axial wall and the leading and trailing cavity walls define a detonation stabilizing cavity in which detonations of the rotating detonation engine occur and are stabilized.
    Type: Application
    Filed: September 21, 2017
    Publication date: March 21, 2019
    Inventors: Venkat Eswarlu Tangirala, Anthony Dean, Narendra Digamber Joshi, Sarah Monahan
  • Patent number: 10202206
    Abstract: A method implemented using at least one of the processor includes disposing a power source on a vehicle, wherein the power source is configured to power auxiliary loads of the aircraft. The method also includes connecting a power source disposed on a vehicle configured to engage an aircraft for ground operation, to auxiliary loads of the aircraft via an on-board power system. The method also includes performing energy management of the aircraft during the period of ground operation. The method further includes disconnecting the power source when an alternate electrical power is available to the on-board power system.
    Type: Grant
    Filed: December 4, 2014
    Date of Patent: February 12, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Zhi Zhou, Narendra Digamber Joshi, Rui Zhou, Hongwei Liao
  • Patent number: 10196898
    Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: February 5, 2019
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Narendra Digamber Joshi, Samar Jyoti Kalita, Paul Gerard Marsland, Wayne Allen Spence
  • Publication number: 20190017441
    Abstract: A gas turbine engine combustor includes a dome plate, an inner liner, and an outer liner. The inner liner and the outer liner are separately coupled to a rear side of the dome plate and both extend rearward therefrom. The outer and inner liners define an annular combustion chamber therebetween that extends rearward from the dome plate. At least one of the outer liner or the dome plate includes an igniter cavity formed therein that is separated from the combustion chamber by a partition wall. The partition wall defines one or more transfer holes therethrough that fluidly connect the igniter cavity to the combustion chamber.
    Type: Application
    Filed: July 17, 2017
    Publication date: January 17, 2019
    Inventors: Krishnakumar Venkatesan, Narendra Digamber Joshi
  • Publication number: 20190017437
    Abstract: A gas turbine engine includes a primary combustor, a secondary combustor, a high pressure (HP) turbine, and a mixing duct. The HP turbine is downstream of the primary combustor and fluidly connected to a rear end of the primary combustor via a first exhaust duct. The mixing duct is disposed downstream of the HP turbine and the secondary combustor. The mixing duct has a first inlet fluidly connected to the HP turbine via a turbine exit duct, a second inlet fluidly connected to a rear end of the secondary combustor via a second exhaust duct, and an outlet. The turbine exit duct directs a primary exhaust stream, which is emitted from the primary combustor and expanded through the HP turbine, into the mixing duct. The second exhaust duct directs a secondary exhaust stream emitted from the secondary combustor into the mixing duct.
    Type: Application
    Filed: July 13, 2017
    Publication date: January 17, 2019
    Inventors: Venkat Eswarlu Tangirala, Aaron Glaser, Sibtosh Pal, Narendra Digamber Joshi
  • Publication number: 20190003713
    Abstract: An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.
    Type: Application
    Filed: September 16, 2018
    Publication date: January 3, 2019
    Inventors: Sarah Marie Monahan, Joel Meier Haynes, Narendra Digamber Joshi, David James Walker, Junwoo Lim, Krishna Kumar Venkatesan
  • Publication number: 20190003315
    Abstract: A heat exchanger includes an airfoil configured to be positioned in a coolant stream. The airfoil includes a pressure sidewall and a suction sidewall coupled to the pressure sidewall. The suction sidewall and the pressure sidewall define a leading edge and a trailing edge opposite the leading edge. The leading edge defines an impingement zone wherein the coolant stream is configured to impinge the airfoil. The heat exchanger also includes at least one channel defined within the airfoil between the pressure sidewall and the suction sidewall. The at least one channel is at least partially defined within the impingement zone proximate the leading edge.
    Type: Application
    Filed: February 3, 2017
    Publication date: January 3, 2019
    Inventors: Daniel Jason Erno, Narendra Digamber Joshi, William Dwight Gerstler
  • Patent number: 10161310
    Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
    Type: Grant
    Filed: February 1, 2016
    Date of Patent: December 25, 2018
    Assignee: General Electric Company
    Inventors: William Paul Minnear, Ronald Scott Bunker, Narendra Digamber Joshi, Andrei Tristan Evulet