Patents by Inventor Clifford E. Johnson

Clifford E. Johnson 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: 11067279
    Abstract: A method, including: operating an industrial gas turbine engine having a plurality of combustor cans arranged in an annular array, each can having burner stages and a pilot burner arrangement having a premix pilot burner and a diffusion pilot burner; operating in asymmetric combustion, wherein at least one can is a warm can where respective burners stages are off and remaining cans operate as hot cans where respective burner stages are on; and while maintaining a constant rate of fuel flow to the pilot burner arrangement of the warm can, changing fuel fractions within the pilot burner arrangement of the warm can.
    Type: Grant
    Filed: May 12, 2016
    Date of Patent: July 20, 2021
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Clifford E. Johnson, Weidong Cai, Krishna C. Miduturi, Ben Karanja, Michael Huth, Werner Krebs, Mark Seifarth, Thomas Primke, Yohannes Ghermay
  • Publication number: 20200309375
    Abstract: A method, including: operating an industrial gas turbine engine having a plurality of combustor cans arranged in an annular array, each can having burner stages and a pilot burner arrangement having a premix pilot burner and a diffusion pilot burner; operating in asymmetric combustion, wherein at least one can is a warm can where respective burners stages are off and remaining cans operate as hot cans where respective burner stages are on; and while maintaining a constant rate of fuel flow to the pilot burner arrangement of the warm can, changing fuel fractions within the pilot burner arrangement of the warm can.
    Type: Application
    Filed: May 12, 2016
    Publication date: October 1, 2020
    Inventors: Clifford E. Johnson, Weidong Cai, Krishna C. Miduturi, Ben Karanja, Michael Huth, Werner Krebs, Mark Seifarth, Thomas Primke, Yohannes Ghermay
  • 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
  • Patent number: 10100737
    Abstract: A cooling arrangement (100), including: a substrate having a pocket (24) defined by a rib side surface (28) and a bottom surface (26); a feature (112) formed in the rib side surface; and an impingement plate (102). In an installed configuration (116) a resilience of the impingement plate enables an interference between the impingement plate and the feature that locks the impingement plate in an installed position (118). An elastic compression of the impingement plate from the installed configuration eliminates the interference.
    Type: Grant
    Filed: May 16, 2013
    Date of Patent: October 16, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: David A. Little, Clifford E. Johnson
  • Publication number: 20170268777
    Abstract: An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include one or more resonator chambers (18) that provide enhanced cooling with reduced risk of cracking and other damage. The resonator housing (18) may include resonator exhaust orifices (26) that are positioned closer to an area of maximum temperature within the combustor (12), thereby enabling the resonator (16) to reduce the temperature gradient within the combustor (12).
    Type: Application
    Filed: September 5, 2014
    Publication date: September 21, 2017
    Inventors: Matthias Hase, Sachin Terdalkar, Rajesh Rajaram, Clifford E. Johnson
  • Publication number: 20170234219
    Abstract: A fuel burner system (10) for a turbine engine (12) configured to operate with syngas fuel, whereby the fuel burner system (10) is configured to reduce nozzle and combustor basket temperatures is disclosed. The fuel burner system (10) may include a plurality of first and second fuel injection ports (16) positioned within a combustor (18), whereby the first fuel injection ports (14) are larger than the second fuel injection ports (16). One or more air injection ports (20) may be aligned with the first fuel injection ports (14). During operation, fuel injected into the combustor (18) from the first fuel injection ports (14) mixes better with the incoming air, causing reduced NOx emissions and lower flame temperatures. Also, the regions between adjacent air injection ports (20), which typically run the hottest, are cooler than conventional combustion system due, in part, to the smaller, second fuel injection ports (16) aligned with regions (22) between adjacent air injection ports (20).
    Type: Application
    Filed: September 11, 2014
    Publication date: August 17, 2017
    Inventors: Vinayak V. Barve, Rafik N. Rofail, Samer P. Wasif, Clifford E. Johnson, Khalil Farid Abou-Jaoude, Stephan Buch, Bernd Prade, J├╝rgen Meisl
  • Publication number: 20170211479
    Abstract: A cooling arrangement (100), including: a substrate having a pocket (24) defined by a rib side surface (28) and a bottom surface (26); a feature (112) formed in the rib side surface; and an impingement plate (102). In an installed configuration (116) a resilience of the impingement plate enables an interference between the impingement plate and the feature that locks the impingement plate in an installed position (118). An elastic compression of the impingement plate from the installed configuration eliminates the interference.
    Type: Application
    Filed: May 16, 2013
    Publication date: July 27, 2017
    Inventors: David A. Little, Clifford E. Johnson
  • Patent number: 8726671
    Abstract: A method of transitioning from a first operating mode to a second operating in a gas turbine engine. An amount of fuel provided to a primary fuel injection system of the combustor apparatus is reduced. An amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus is reduced, wherein the secondary fuel/air injection system provides fuel to a secondary combustion zone downstream from a main combustion zone. A total amount of air provided to the combustor apparatus is reduced, wherein portions of the air are provided to each of the injection systems. Upon reaching operating parameters corresponding to the second operating mode, the amount of fuel provided to the primary fuel injection system is increased, the amount of fuel provided to the secondary fuel/air injection system is reduced, and the total amount of air provided to the combustor apparatus is increased.
    Type: Grant
    Filed: July 14, 2010
    Date of Patent: May 20, 2014
    Assignee: Siemens Energy, Inc.
    Inventors: Weidong Cai, Clifford E. Johnson
  • 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: 8413443
    Abstract: A resonator system for a turbine engine can improve acoustic performance and cooling effectiveness. During engine operation, a combustor liner exhibits alternating hot and cold regions in the circumferential direction corresponding to the non-uniform temperature distribution of the combustion flame. Accordingly, high flow resonators are formed with the liner in substantial alignment with the hot regions of the fluid flow within the liner, and low flow resonators are formed with the liner in substantial alignment with cold regions of the fluid flow within the liner. As a result, appropriate amounts of cooling can be provided to the liner so that cooling air usage is optimized. Alternatively or in addition, the liner can include two or more rows of resonators, which can provide an enhanced acoustic damping response. The resonators in the first row can be aligned with or offset from the resonators in the second row.
    Type: Grant
    Filed: December 15, 2009
    Date of Patent: April 9, 2013
    Assignee: Siemens Energy, Inc.
    Inventor: 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
  • Publication number: 20120011855
    Abstract: A method of transitioning from a first operating mode to a second operating in a gas turbine engine. An amount of fuel provided to a primary fuel injection system of the combustor apparatus is reduced. An amount of fuel provided to a secondary fuel/air injection system of the combustor apparatus is reduced, wherein the secondary fuel/air injection system provides fuel to a secondary combustion zone downstream from a main combustion zone. A total amount of air provided to the combustor apparatus is reduced, wherein portions of the air are provided to each of the injection systems. Upon reaching operating parameters corresponding to the second operating mode, the amount of fuel provided to the primary fuel injection system is increased, the amount of fuel provided to the secondary fuel/air injection system is reduced, and the total amount of air provided to the combustor apparatus is increased.
    Type: Application
    Filed: July 14, 2010
    Publication date: January 19, 2012
    Inventors: Weidong Cai, Clifford E. Johnson
  • Patent number: 8061141
    Abstract: A combustor assembly is provided comprising a combustor casing; a liner coupled to the combustor casing; a burner assembly coupled to the combustor casing; and at least one resonator assembly. The resonator assembly comprises a resonator outer plate having at least one opening, a resonator side wall coupled to the resonator outer plate, and a resonator inner plate defined by a portion of the liner. The resonator inner plate is coupled to the resonator side wall and has at least one slot formed therein having an aspect ratio of at least 4:1.
    Type: Grant
    Filed: September 27, 2007
    Date of Patent: November 22, 2011
    Assignee: Siemens Energy, Inc.
    Inventors: Clifford E. Johnson, Joachim Lepers, Samer P. Wasif
  • Publication number: 20110138812
    Abstract: A resonator system for a turbine engine can improve acoustic performance and cooling effectiveness. During engine operation, a combustor liner exhibits alternating hot and cold regions in the circumferential direction corresponding to the non-uniform temperature distribution of the combustion flame. Accordingly, high flow resonators are formed with the liner in substantial alignment with the hot regions of the fluid flow within the liner, and low flow resonators are formed with the liner in substantial alignment with cold regions of the fluid flow within the liner. As a result, appropriate amounts of cooling can be provided to the liner so that cooling air usage is optimized. Alternatively or in addition, the liner can include two or more rows of resonators, which can provide an enhanced acoustic damping response. The resonators in the first row can be aligned with or offset from the resonators in the second row.
    Type: Application
    Filed: December 15, 2009
    Publication date: June 16, 2011
    Inventor: Clifford E. Johnson
  • Publication number: 20100236245
    Abstract: A gas turbine combustion system has a combustion system wall delimiting a flow path for hot and pressurized combustion gas and at least one resonator with a resonator volume. The resonator volume is delimited by resonator walls, where one of the resonator walls is located adjacent to or is formed by the combustion system wall. The resonator has at least one cooling fluid supply opening which is open towards a cooling fluid source. It further has a neck opening which is open towards the flow path and which is implemented in the form of a neck slot.
    Type: Application
    Filed: March 19, 2009
    Publication date: September 23, 2010
    Inventors: Clifford E. Johnson, Joachim Lepers, Samer P. Wasif
  • Patent number: 7788926
    Abstract: One or more Helmholtz-type resonators (270) is/are provided at the junction (260) of a combustor (220) and a combustion chamber (240) of a gas turbine engine (100). In one embodiment, adjacent Helmholtz-type resonators (290, 291, 292), which may be separated by respective baffles (285), have different volumes that help provide for damping different undesired combustion-generated acoustic pressure waves. In some embodiments, a structural member (435) may be provided between adjacent Helmholtz-type resonators (425, 426, 427, 428) at the junction. At least one of the plurality of Helmholtz-type resonators comprises one or more inlet openings (480), and one or more exit openings (482). Embodiments (370, 425-429) are described in which Helmholtz-type resonators provided at the junction are enlarged in size using various approaches.
    Type: Grant
    Filed: August 18, 2006
    Date of Patent: September 7, 2010
    Assignee: Siemens Energy, Inc.
    Inventors: Clifford E. Johnson, Samer P. Wasif
  • 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
  • Patent number: 7584617
    Abstract: A method and system (14) for monitoring a health of a combustion dynamics sensing system (10) includes monitoring respective dynamic conditions of at least two combustor cans (16) of a can annular combustor (12) of a gas turbine engine with respective dynamic condition sensors (20) associated with each of the cans. The method also includes establishing a baseline relationship between the respective dynamic conditions and then identifying a variance from the baseline relationship indicative of a degraded signal quality provided by a dynamic condition sensor associated with at least one of the cans.
    Type: Grant
    Filed: March 17, 2006
    Date of Patent: September 8, 2009
    Assignee: Siemens Energy, Inc.
    Inventors: Robert J. Bland, 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
  • Publication number: 20090084100
    Abstract: A combustor assembly is provided comprising a combustor casing; a liner coupled to the combustor casing; a burner assembly coupled to the combustor casing; and at least one resonator assembly. The resonator assembly comprises a resonator outer plate having at least one opening, a resonator side wall coupled to the resonator outer plate, and a resonator inner plate defined by a portion of the liner. The resonator inner plate is coupled to the resonator side wall and has at least one slot formed therein having an aspect ratio of at least 4:1.
    Type: Application
    Filed: September 27, 2007
    Publication date: April 2, 2009
    Applicant: SIEMENS POWER GENERATION, INC.
    Inventors: Clifford E. Johnson, Joachim Lepers, Samer P. Wasif