Patents Assigned to Power Systems Mfg, LLC
  • Patent number: 8504276
    Abstract: Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.
    Type: Grant
    Filed: February 28, 2008
    Date of Patent: August 6, 2013
    Assignee: Power Systems Mfg., LLC
    Inventors: Vincent C. Martling, Peter So, Zhenhua Xiao, Plazi Ricklin
  • Patent number: 8136359
    Abstract: Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.
    Type: Grant
    Filed: December 10, 2007
    Date of Patent: March 20, 2012
    Assignee: Power Systems Mfg., LLC
    Inventors: Peter Stuttaford, Paul Economo, Khalid Oumejjoud, Max Dufflocq, Hany Rizkalla
  • Patent number: 8091363
    Abstract: Embodiments for an apparatus and associated method for reducing the residence time in a gas turbine combustor are disclosed. The embodiments of the present invention comprise a fuel nozzle that extends to a downstream plane of an end cap for a combustion liner where the axial distance of the premixer is reduced, however the swirl for mixing the fuel and air, is increased. As a result, the mixing of the fuel and air is essentially unchanged, thereby allowing higher air pressures and operating temperatures within the premixer without inducing auto-ignition.
    Type: Grant
    Filed: November 29, 2007
    Date of Patent: January 10, 2012
    Assignee: Power Systems Mfg., LLC
    Inventors: Daniel J. Sullivan, Peter Stuttaford, Robert J. Kraft, Khalid Oumejjoud, Yan Chen
  • Patent number: 7841186
    Abstract: An inlet bleed heat and power augmentation system utilizing a bi-directional and common piping arrangement is disclosed. The piping arrangement includes a plurality of feed tubes arranged to communicate either steam to a compressor discharge plenum or compressed air from the compressor discharge plenum. Various embodiments of the invention are discussed including operation methods.
    Type: Grant
    Filed: January 31, 2007
    Date of Patent: November 30, 2010
    Assignee: Power Systems Mfg., LLC
    Inventors: Peter So, Jesse Sewell, Donald Adams
  • Patent number: 7837435
    Abstract: A system and method for reducing vibration and wear to adjacent platform surfaces and mounting locations of a vane segment in a gas turbine engine is disclosed. The present invention seeks to improve the interaction between mating faces of adjacent gas turbine vane assemblies by increasing the surface area where contact between the adjacent vanes occurs, so as to increase the damping capability and reduce the wear to the mating surfaces.
    Type: Grant
    Filed: May 4, 2007
    Date of Patent: November 23, 2010
    Assignee: Power System Mfg., LLC
    Inventors: Charles Ellis, Terry Hollis, David Medrano
  • Patent number: 7685823
    Abstract: An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.
    Type: Grant
    Filed: October 28, 2005
    Date of Patent: March 30, 2010
    Assignee: Power Systems Mfg., LLC
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Patent number: 7677045
    Abstract: A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1. The coordinates are taken at a sweep angle ? wherein ? is an angle measured from the inlet end and X, Y, and Z are coordinates defining the panel assembly profile at each angle ? from the inlet end. An alternate embodiment is also disclosed defining an envelope for the uncoated internal profile of the panel assembly.
    Type: Grant
    Filed: April 14, 2006
    Date of Patent: March 16, 2010
    Assignee: Power Systems Mfg., LLC
    Inventors: Stephen W. Jorgensen, Heather Johnston
  • Patent number: 7677025
    Abstract: A gas turbine combustor having a self-purging pilot fuel injection system and method of operation thereof is disclosed. The pilot fuel injection system comprises a radial inflow swirler, a generally axially extending centerbody, and at least one fuel injection source. In operation a fluid containing at least air passes along the centerbody outer surface clearing any remaining fuel from proximate the fuel injection source so as to prevent flame attachment proximate the fuel injection source.
    Type: Grant
    Filed: February 1, 2005
    Date of Patent: March 16, 2010
    Assignee: Power Systems Mfg., LLC
    Inventors: Peter Stuttaford, Stephen Jennings
  • Patent number: 7624564
    Abstract: A fuel supply system and method thereof that utilizes an off-gas in addition to the primary fuel to lower the emissions of a gas turbine combustion system is disclosed. The fuel supply system apparatus comprises a fuel gas supply conduit and an off-gas supply conduit in fluid communication with the fuel gas supply conduit such that the flow of an off-gas to the fuel gas supply conduit can be regulated as required by the operator to the desired fuel nozzle(s). The fuel gas supply preferably operates with natural gas and the off-gas supply preferably comprises the constituents hydrogen and methane.
    Type: Grant
    Filed: July 23, 2004
    Date of Patent: December 1, 2009
    Assignee: Power Systems Mfg., LLC
    Inventors: Peter Stuttaford, Jon Glende, Peter So, Lee Rosen, Khalid Oumejjoud
  • Publication number: 20090222187
    Abstract: Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.
    Type: Application
    Filed: February 28, 2008
    Publication date: September 3, 2009
    Applicant: POWER SYSTEMS MFG., LLC
    Inventors: VINCENT C. MARTLING, Peter SO, ZHENHUA XIAO, PLAZI RICKLIN
  • Publication number: 20090145983
    Abstract: Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.
    Type: Application
    Filed: December 10, 2007
    Publication date: June 11, 2009
    Applicant: POWER SYSTEMS MFG., LLC
    Inventors: Peter Stuttaford, Paul Economo, Khalid Oumejjoud, Max Dufflocq, Hany Rizkalla
  • Publication number: 20090145099
    Abstract: Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct.
    Type: Application
    Filed: December 6, 2007
    Publication date: June 11, 2009
    Applicant: POWER SYSTEMS MFG., LLC
    Inventors: Stephen Jennings, Peter Stuttaford, Stephen W. Jorgensen
  • Publication number: 20090139237
    Abstract: Embodiments for an apparatus and associated method for reducing the residence time in a gas turbine combustor are disclosed. The embodiments of the present invention comprise a fuel nozzle that extends to a downstream plane of an end cap for a combustion liner where the axial distance of the premixer is reduced, however the swirl for mixing the fuel and air, is increased. As a result, the mixing of the fuel and air is essentially unchanged, thereby allowing higher air pressures and operating temperatures within the premixer without inducing auto-ignition.
    Type: Application
    Filed: November 29, 2007
    Publication date: June 4, 2009
    Applicant: POWER SYSTEMS MFG., LLC
    Inventors: Daniel J. Sullivan, Peter Stuttaford, Robert J. Kraft, Khalid Oumejjoud, Yan Chen
  • Patent number: 7513115
    Abstract: A gas turbine combustor having improved flashback margin is disclosed. Multiple embodiments of the present invention are disclosed including combustors having a single premix chamber as well as multiple premix chambers. Flashback margin is increased for the combustor by incorporating a means for introducing an inert gas, such as nitrogen, into the premix chamber(s) at the region proximate the boundary layer to purge the boundary layer of combustible mixture, thereby ensuring that no combustion reaction occurs in the boundary layer.
    Type: Grant
    Filed: May 23, 2005
    Date of Patent: April 7, 2009
    Assignee: Power Systems Mfg., LLC
    Inventor: Peter John Stuttaford
  • Publication number: 20080273964
    Abstract: A system and method for reducing vibration and wear to adjacent platform surfaces and mounting locations of a vane segment in a gas turbine engine is disclosed. The present invention seeks to improve the interaction between mating faces of adjacent gas turbine vane assemblies by increasing the surface area where contact between the adjacent vanes occurs, so as to increase the damping capability and reduce the wear to the mating surfaces.
    Type: Application
    Filed: May 4, 2007
    Publication date: November 6, 2008
    Applicant: POWER SYSTEMS MFG., LLC
    Inventors: Charles Ellis, Terry Hollis, David Medrano
  • Patent number: 7386980
    Abstract: A combustion liner having enhanced heat transfer over at least a portion of the liner is disclosed. The combustion liner comprises, amongst other features, an outer surface wherein at least a region of the outer surface is textured in a substantially uniform pattern such that the surface area exposed to a passing cooling medium is increased, thereby increasing the heat transfer through the combustion liner. Multiple embodiments of textured patterns are also disclosed.
    Type: Grant
    Filed: February 2, 2005
    Date of Patent: June 17, 2008
    Assignee: Power Systems Mfg., LLC
    Inventors: Andrew Green, Peter Stuttaford, John Carella, Vamsi Duraibabu, Stephen Jennings
  • Patent number: 7334800
    Abstract: A seal extending between adjacent slots of a gas turbine engine is disclosed. The seal comprises a plurality of generally planar members fixed together along a central axis. The outer member further comprises rounded ends that encompass the second and plurality of third generally planar members. The seal disclosed herein improves sealing capability by providing a more compliant seal over the prior art while reducing the mechanical loads experienced along the seal weld joint, thereby improving seal durability.
    Type: Grant
    Filed: March 16, 2005
    Date of Patent: February 26, 2008
    Assignee: Power Systems Mfg., LLC
    Inventor: Mark Minnich
  • Patent number: 7308793
    Abstract: The present invention discloses an apparatus and method for reducing the carbon monoxide emissions emitted by a pilot injector of a gas turbine combustor. Multiple embodiments of a means for establishing a recirculation zone are disclosed whereby a portion of the fuel and air mixture from the pilot injector recirculates and a flame is held, thereby increasing the local reaction temperature at the desired location and lowering carbon monoxide emissions.
    Type: Grant
    Filed: January 7, 2005
    Date of Patent: December 18, 2007
    Assignee: Power Systems Mfg., LLC
    Inventors: Khalid Oumejjoud, Peter Stuttaford, Yan Chen, Nuria Margarit-Bel, Stephen Jennings
  • Patent number: 7293957
    Abstract: A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing its resistance to thermal deflection. This is accomplished by placing an opening along the innermost vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.
    Type: Grant
    Filed: March 28, 2007
    Date of Patent: November 13, 2007
    Assignee: Power Systems Mfg., LLC
    Inventors: Charlie Ellis, David Parker, J. Page Strohl, David Medrano
  • Publication number: 20070240422
    Abstract: A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1. The coordinates are taken at a sweep angle ? wherein ? is an angle measured from the inlet end and X, Y, and Z are coordinates defining the panel assembly profile at each angle ? from the inlet end. An alternate embodiment is also disclosed defining an envelope for the uncoated internal profile of the panel assembly.
    Type: Application
    Filed: April 14, 2006
    Publication date: October 18, 2007
    Applicant: Power Systems Mfg. LLC
    Inventors: Stephen Jorgensen, Heather Johnston