Patents by Inventor Domenico Gambacorta

Domenico Gambacorta 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: 20200063959
    Abstract: A system effective for dual utilization of cooling fluid in a gas turbine engine is provided. A cooling annulus is subject to a hot-temperature combustion flow received from a combustor basket and includes a liner including a feed channel to receive cooling fluid. A feed manifold is in fluid communication with feed channel to feed cooling fluid to a plurality of conduits in fluid communication with a plurality of exit orifices that is in fluid communication with a plurality of resonators. A distributor manifold includes a plurality of manifold sectors in fluid communication with a plurality of conduits arranged to convey cooling fluid. Some of the plurality of resonators operates with different amounts of cooling fluid. A group of the plurality of exit orifices is configured to supply an amount of cooling fluid appropriate for a resonator in fluid communication with the group of the plurality of exit orifices.
    Type: Application
    Filed: March 22, 2018
    Publication date: February 27, 2020
    Inventors: Domenico Gambacorta, Wojciech Dyszkiewicz, Daniel Cassar, Clifford E. Johnson
  • Publication number: 20180313535
    Abstract: An improved combustion system in a combustion turbine engine is provided. The combustor system may include an injector assembly disposed in a combustion stage disposed downstream from a main combustion stage of the combustor system. The injector assembly may include a reactant-guiding structure arranged to deliver to the combustion stage respective jets of reactants through an array of ejection orifices disposed on one or more side walls of the reactant-guiding structure. The reactant-guiding structure may be configured to form a stream-lined body relative to a flow of a fluid to be mixed with the jets of reactants delivered to the combustion stage. The ejection orifices of the array may be aerodynamically-shaped to define a respective stream-lined orifice cross-section, (e.g., airfoil shaped).
    Type: Application
    Filed: October 28, 2015
    Publication date: November 1, 2018
    Inventors: Andrew J. North, Juan Enrique Portillo Bilbao, Walter Ray Laster, Domenico Gambacorta, Reinhard Schilp
  • Publication number: 20180306440
    Abstract: A cooling ring (102) of a combustor basket system (110) has a transition zone 108 that extends to a cooling channel (106) at a cooling channel entrance (104). The transition zone (108) has the substantially the same material strength throughout the length of the transition zone (108). By having the same material strength throughout the length of the transition zone (108), the cooling ring (102) is able to withstand greater stresses than previously used cooling rings. One way in which this is accomplished is by having a uniform thickness.
    Type: Application
    Filed: June 24, 2015
    Publication date: October 25, 2018
    Inventors: Kevin J. Spence, Domenico Gambacorta, Stephen A. Ramier
  • Publication number: 20140208757
    Abstract: A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure. The main body has an inlet end and an outlet end and defines a longitudinal axis extending between the outlet and inlet ends. The main body comprises a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet. The fuel supply structure communicates with and supplies fuel to the air/fuel passages for providing an air/fuel mixture within each air/fuel passage. The air/fuel mixtures exit the main body through respective air/fuel passage outlets.
    Type: Application
    Filed: April 3, 2014
    Publication date: July 31, 2014
    Inventors: Timothy Fox, Reinhard Schilp, Domenico Gambacorta
  • Patent number: 8752386
    Abstract: A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure. The main body has an inlet end and an outlet end and defines a longitudinal axis extending between the outlet and inlet ends. The main body comprises a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet. The fuel supply structure communicates with and supplies fuel to the air/fuel passages for providing an air/fuel mixture within each air/fuel passage. The air/fuel mixtures exit the main body through respective air/fuel passage outlets.
    Type: Grant
    Filed: May 25, 2010
    Date of Patent: June 17, 2014
    Assignees: Siemens Energy, Inc., Mikro Systems, Inc.
    Inventors: Timothy A. Fox, Reinhard Schilp, Domenico Gambacorta
  • Patent number: 8516819
    Abstract: A gas turbine combustor having a Helmholtz resonator in a post-swirler homogenization zone upstream of the combustor zone. Embodiments of the present invention provide Helmholtz resonators that include cavities that occupy a remainder of a post-swirler homogenization zone, which also includes at least one flow-directing structure that passes a fuel/oxidizer mixture from a main swirler assembly into a combustion zone of a combustor. Thus, an open annular region of the combustor is converted into a multi-purpose zone that includes at least one Helmholtz resonator.
    Type: Grant
    Filed: July 16, 2008
    Date of Patent: August 27, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: Domenico Gambacorta, Clifford E. Johnson
  • Patent number: 8146364
    Abstract: Embodiments of the present invention provide resonators (260, 460) that have lateral walls (268, 270) disposed at non-square angles relative to the liner's longitudinal (and flow-based) axis (219) such that a film cooling of substantial portions of an intervening strip (244, 444) is provided from apertures (226A, 226B, 426) in a resonator box (262, 462) adjacent and upstream from the intervening strip (244, 444). This film cooling also cools weld seams (280) along the lateral walls (268, 270) of the resonator boxes (262, 462). In various embodiments the lateral wall angles are such that film cooling may be provided to include the most of the downstream portions of the intervening strips (244, 444). These downstream portions are closer to the combustion heat source and therefore expected to be in greater need of cooling.
    Type: Grant
    Filed: September 14, 2007
    Date of Patent: April 3, 2012
    Assignee: Siemens Energy, Inc.
    Inventors: Clifford E. Johnson, Robert J. Bland, Domenico Gambacorta, Samer P. Wasif
  • Patent number: 8113000
    Abstract: A pre-mixer assembly associated with a fuel supply system for mixing of air and fuel upstream from a main combustion zone in a gas turbine engine. The pre-mixer assembly includes a swirler assembly disposed about a fuel injector of the fuel supply system and a pre-mixer transition member. The swirler assembly includes a forward end defining an air inlet and an opposed aft end. The pre-mixer transition member has a forward end affixed to the aft end of the swirler assembly and an opposed aft end defining an outlet of the pre-mixer assembly. The aft end of the pre-mixer transition member is spaced from a base plate such that a gap is formed between the aft end of the pre-mixer transition member and the base plate for permitting a flow of purge air therethrough to increase a velocity of the air/fuel mixture exiting the pre-mixer assembly.
    Type: Grant
    Filed: September 15, 2008
    Date of Patent: February 14, 2012
    Assignee: Siemens Energy, Inc.
    Inventors: Walter R. Laster, Domenico Gambacorta
  • Publication number: 20110289928
    Abstract: A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure. The main body has an inlet end and an outlet end and defines a longitudinal axis extending between the outlet and inlet ends. The main body comprises a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet. The fuel supply structure communicates with and supplies fuel to the air/fuel passages for providing an air/fuel mixture within each air/fuel passage. The air/fuel mixtures exit the main body through respective air/fuel passage outlets.
    Type: Application
    Filed: May 25, 2010
    Publication date: December 1, 2011
    Inventors: Timothy A. Fox, Reinhard Schilp, Domenico Gambacorta
  • Publication number: 20100064691
    Abstract: A pre-mixer assembly associated with a fuel supply system for mixing of air and fuel upstream from a main combustion zone in a gas turbine engine. The pre-mixer assembly includes a swirler assembly disposed about a fuel injector of the fuel supply system and a pre-mixer transition member. The swirler assembly includes a forward end defining an air inlet and an opposed aft end. The pre-mixer transition member has a forward end affixed to the aft end of the swirler assembly and an opposed aft end defining an outlet of the pre-mixer assembly. The aft end of the pre-mixer transition member is spaced from a base plate such that a gap is formed between the aft end of the pre-mixer transition member and the base plate for permitting a flow of purge air therethrough to increase a velocity of the air/fuel mixture exiting the pre-mixer assembly.
    Type: Application
    Filed: September 15, 2008
    Publication date: March 18, 2010
    Inventors: Walter R. Laster, Domenico Gambacorta
  • Publication number: 20100011769
    Abstract: A gas turbine combustor having a Helmholtz resonator in a post-swirler homogenization zone upstream of the combustor zone. Embodiments of the present invention provide Helmholtz resonators that include cavities that occupy a remainder of a post-swirler homogenization zone, which also includes at least one flow-directing structure that passes a fuel/oxidizer mixture from a main swirler assembly into a combustion zone of a combustor. Thus, an open annular region of the combustor is converted into a multi-purpose zone that includes at least one Helmholtz resonator.
    Type: Application
    Filed: July 16, 2008
    Publication date: January 21, 2010
    Applicant: SIEMENS POWER GENERATION, INC.
    Inventors: Domenico Gambacorta, Clifford E. Johnson
  • Publication number: 20090094985
    Abstract: Embodiments of the present invention provide resonators (260, 460) that have lateral walls (268, 270) disposed at non-square angles relative to the liner's longitudinal (and flow-based) axis (219) such that a film cooling of substantial portions of an intervening strip (244, 444) is provided from apertures (226A, 226B, 426) in a resonator box (262, 462) adjacent and upstream from the intervening strip (244, 444). This film cooling also cools weld seams (280) along the lateral walls (268, 270) of the resonator boxes (262, 462). In various embodiments the lateral wall angles are such that film cooling may be provided to include the most of the downstream portions of the intervening strips (244, 444). These downstream portions are closer to the combustion heat source and therefore expected to be in greater need of cooling.
    Type: Application
    Filed: September 14, 2007
    Publication date: April 16, 2009
    Applicant: Siemens Power Generation, Inc.
    Inventors: Clifford E. Johnson, Robert J. Bland, Domenico Gambacorta, Samer P. Wasif