Patents by Inventor Samer P. Wasif

Samer P. Wasif 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: 20180003384
    Abstract: A combustor inlet mixing system (10) formed from a plurality of circumferentially spaced swirler vanes (38) extending radially outward from a nozzle hub. Each of the swirler vanes (38) may have a length (62) that extends downstream along at least a portion of the combustor inlet mixing system (10), and may further have a thickness (66) that extends along a circumference of the nozzle hub. At least one of the swirler vanes (38) may further have at least one slot (42) cut entirely through the thickness (66) of a portion of the swirler vane (38). The slot (42) may separate the swirler vane (38) from the nozzle hub along a portion of the length (62) of the swirler vane (38).
    Type: Application
    Filed: January 22, 2015
    Publication date: January 4, 2018
    Inventor: Samer P. Wasif
  • 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
  • Patent number: 9297532
    Abstract: A can annular combustion arrangement (12) for a gas turbine engine (10), including: a combustor can (14) having an inlet (46) at a head end (62); an annular chamber (30) surrounding the combustor can (14) for delivering a flow of compressed air from a plenum (18) to the inlet (46); a fuel injector (49) configured to inject a flow of fuel into the flow of compressed air; and a flow tripping device (60) surrounding the combustor can (14) and disposed in the annular chamber (30) downstream of the fuel injector (49).
    Type: Grant
    Filed: December 3, 2012
    Date of Patent: March 29, 2016
    Assignee: Siemens Aktiengesellschaft
    Inventors: Samer P. Wasif, Juergen Meisl, Bertram Janus, Andreas Koch
  • Patent number: 9038393
    Abstract: A fuel gas cooling system for a combustion basket spring clip seal support is disclosed. The fuel gas cooling system may be formed from one or more fuel gas supply channels terminating proximate to a spring clip at the intersection between a combustor basket and a transition section such that fuel gas may be supplied to the hot gas path proximate to the intersection between the combustor basket and the transition section. The fuel gas supply channel may create an intermediate fuel gas burn at this intersection, which may reduce the firing temperature at the fuel nozzles and reduce NOx emissions.
    Type: Grant
    Filed: August 27, 2010
    Date of Patent: May 26, 2015
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Samer P. Wasif, Muzaffer Sutcu, Walter R. Laster
  • Publication number: 20150128600
    Abstract: A fuel system for a turbine engine for improving efficiency in a fuel system where a major stage and secondary stage can be combined and held to a relatively constant fuel ratio while maintaining acceptable engine dynamics and NOx emissions is disclosed. The fuel system may be formed from a first premix injector assembly stage positioned upstream from a combustor basket, whereby the first premix injector assembly stage is a secondary injector system. The fuel system may be formed from a first primary injector assembly stage, which is a main injector system, positioned downstream from the first premix injector assembly stage. The first premix injector assembly stage and the first primary injector assembly stage may be coupled together such that the fuel system is capable of emitting fuel into a combustor of the turbine engine via the first premix injector assembly stage and the first primary injector assembly stage simultaneously.
    Type: Application
    Filed: November 13, 2013
    Publication date: May 14, 2015
    Inventors: Krishna C. Miduturi, Samer P. Wasif
  • Patent number: 9017064
    Abstract: A method of influencing combustion dynamics, including measuring a combustion dynamics parameter, and controlling a diluent flow (26) delivered to a fuel flow (32) upstream of a pilot burner fuel outlet (40) in response to the measured combustion dynamics parameter.
    Type: Grant
    Filed: June 8, 2010
    Date of Patent: April 28, 2015
    Assignee: Siemens Energy, Inc.
    Inventor: Samer P. Wasif
  • Publication number: 20130160423
    Abstract: A can annular combustion arrangement (12) for a gas turbine engine (10), including: a combustor can (14) having an inlet (46) at a head end (62); an annular chamber (30) surrounding the combustor can (14) for delivering a flow of compressed air from a plenum (18) to the inlet (46); a fuel injector (49) configured to inject a flow of fuel into the flow of compressed air; and a flow tripping device (60) surrounding the combustor can (14) and disposed in the annular chamber (30) downstream of the fuel injector (49).
    Type: Application
    Filed: December 3, 2012
    Publication date: June 27, 2013
    Inventors: Samer P. Wasif, Juergen Meisl, Bertram Janus, Andreas Koch
  • 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: 20120047904
    Abstract: A fuel gas cooling system for a combustion basket spring clip seal support is disclosed. The fuel gas cooling system may be formed from one or more fuel gas supply channels terminating proximate to a spring clip at the intersection between a combustor basket and a transition section such that fuel gas may be supplied to the hot gas path proximate to the intersection between the combustor basket and the transition section. The fuel gas supply channel may create an intermediate fuel gas burn at this intersection, which may reduce the firing temperature at the fuel nozzles and reduce NOx emissions.
    Type: Application
    Filed: August 27, 2010
    Publication date: March 1, 2012
    Inventors: Samer P. Wasif, Muzaffer Sutcu, Walter R. Laster
  • Publication number: 20110300491
    Abstract: A method of influencing combustion dynamics, including measuring a combustion dynamics parameter, and controlling a diluent flow (26) delivered to a fuel flow (32) upstream of a pilot burner fuel outlet (40) in response to the measured combustion dynamics parameter.
    Type: Application
    Filed: June 8, 2010
    Publication date: December 8, 2011
    Inventor: Samer P. Wasif
  • 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
  • Patent number: 7926279
    Abstract: A gas sleeve (120) for a combustor (408) of gas turbine engine (400) attaches to a support housing (100) of the combustor (408) to convey a fuel gas and to fit within a fuel rocket (110). The gas sleeve (120) comprises a plurality of apertures (128) formed to provide impingement cooling. The apertures (128) comprise a tilt angle directed toward a structure in need of impingement cooling, for instance a weld joint (114) that attaches the fuel rocket (110) to the support housing (100). The apertures (128) additionally may comprise a rotational angle effective to create a rotationally swirling flow of the portion of fuel gas that passes through the apertures (128). A method of operation using this structure also is provided.
    Type: Grant
    Filed: September 21, 2006
    Date of Patent: April 19, 2011
    Assignee: Siemens Energy, Inc.
    Inventors: Samer P. Wasif, Robert J. Bland
  • 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: 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
  • Patent number: 7413053
    Abstract: Aspects of the invention are directed to an acoustic resonator with improved impingement cooling effectiveness. The resonator includes a plate with an inside face and an outside face. A plurality of passages extend through the plate. The resonator includes a side wall that extends from and about the plate. A plurality of cooling tubes are attached to the resonator plate such that an inner passage of each cooling tube is in fluid communication with a respective passage in the resonator plate. The resonator can be secured to a surface of a turbine engine combustor component to define a closed cavity. The ends of the cooling tubes are spaced from the surface. Thus, a coolant can enter the passages in the plate and can be directed to the surface so as to impingement cool the surface. The cooling tubes can minimize coolant loss by dispersion in the cavity.
    Type: Grant
    Filed: January 25, 2006
    Date of Patent: August 19, 2008
    Assignee: Siemens Power Generation, Inc.
    Inventors: Samer P. Wasif, Clifford E. Johnson
  • Publication number: 20080072602
    Abstract: A gas sleeve (120) for a combustor (408) of gas turbine engine (400) attaches to a support housing (100) of the combustor (408) to convey a fuel gas and to fit within a fuel rocket (110). The gas sleeve (120) comprises a plurality of apertures (128) formed to provide impingement cooling. The apertures (128) comprise a tilt angle directed toward a structure in need of impingement cooling, for instance a weld joint (114) that attaches the fuel rocket (110) to the support housing (100). The apertures (128) additionally may comprise a rotational angle effective to create a rotationally swirling flow of the portion of fuel gas that passes through the apertures (128). A method of operation using this structure also is provided.
    Type: Application
    Filed: September 21, 2006
    Publication date: March 27, 2008
    Inventors: Samer P. Wasif, Robert J. Bland
  • Publication number: 20080041058
    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: Application
    Filed: August 18, 2006
    Publication date: February 21, 2008
    Inventors: Clifford E. Johnson, Samer P. Wasif
  • Patent number: 7080515
    Abstract: A gas turbine engine (120) includes a cylindrical basket (146) having an axis (14) and a single main burner assembly (12) disposed within the basket. A burner insert (34) is disposed in an annular space between the burner assembly and the basket. The insert includes a face perpendicular to the axis of the basket. A plurality of passageways (114) are formed in the basket, positioned proximate to and downstream of the burner insert for allowing passage of a portion of an oxidizer flow (42) into a combustion chamber (30). A fluid flow path (38), defined between a combustion chamber liner portion (32) of the basket and a casing (40) spaced radially outward from the combustion liner portion, discharges a fluid into a flow reversal region (118) proximate an inlet (20) of the burner assembly. A fuel outlet (44) is disposed in the flow reversal region.
    Type: Grant
    Filed: September 19, 2003
    Date of Patent: July 25, 2006
    Assignee: Siemens Westinghouse Power Corporation
    Inventors: Samer P. Wasif, Udo Schmitz, Robert Bland, Karsten Jordan, John Carl Glessner, J. Scott Markovitz, Bernd Prade, David Kargetta, Stephen Ramier, Stefan Dahlk