Plural Combustion Products Generators In Ring Coaxial With Turbine Patents (Class 60/39.37)
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Patent number: 9631814Abstract: An engine assembly includes a compressor section configured to supply compressed air and a combustion section coupled to the compressor section. The compressor section includes a diffuser with diffuser vanes to condition the compressed air, and the diffuser vanes have a vane count of a first value. The combustion section includes a combustion chamber to receive the compressed air and fuel injection assemblies configured to introduce fuel into the combustion chamber. The fuel injection assemblies have a fuel injection assembly count of a second value, and the first value is a whole number multiple of the second value.Type: GrantFiled: January 23, 2014Date of Patent: April 25, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Michael T. Todd Barton, Samir Rida, Ian Critchley
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Patent number: 9574460Abstract: A support arrangement (10) for a transition piece (12) of a gas turbine engine (14). The support arrangement includes a mounting bracket (16) for the transition piece and a pin (18) supporting the mounting bracket in an interior (20) of the gas turbine engine and extending through an opening (22) in a casing (24) to an exterior (26) of the gas turbine engine. The support arrangement further includes a spherical washer (28, 38) positioned between the pin and either the mounting bracket or the casing.Type: GrantFiled: October 30, 2014Date of Patent: February 21, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Andrew Carlson, William W. Pankey
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Patent number: 9506359Abstract: The present application provides a combustion system for use with a cooling flow. The combustion system may include a head end, an aft end, a transition nozzle extending from the head end to the aft end, and an impingement sleeve surrounding the transition nozzle. The impingement sleeve may define a first cavity in communication with the head end for a first portion of the cooling flow and a second cavity in communication with the aft end for a second portion of the cooling flow. The transition nozzle may include a number of cooling holes thereon in communication with the second portion of the cooling flow.Type: GrantFiled: April 3, 2012Date of Patent: November 29, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Won-Wook Kim, Kevin Weston McMahan, Jaime Javier Maldonado
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Patent number: 9482106Abstract: A combustor transition can be adapted to guide combustion gases in a hot gas flow path extending between a combustor and a first stage of a turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the combustor and a downstream end adapted for connection to a first stage of the turbine. The downstream end comprises an outer wall, an inner wall, a first side wall and a second side wall. At least one side wall has a side wall extension, which can extend in a downstream direction beyond the outlet. A gas turbine can be retrofitted with such a combustor transition and a gas turbine with such a combustor transition can also undergo a borescope inspection.Type: GrantFiled: October 24, 2013Date of Patent: November 1, 2016Assignee: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Michael Düsing, Mirko Ruben Bothien
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Patent number: 9470421Abstract: A combustor cap assembly includes an annular shroud and an impingement plate coupled to the shroud. The impingement plate at least partially defines a plurality of impingement cooling holes and a cooling flow return passage. A cap plate is coupled to the impingement plate. The cap plate includes an impingement side which faces a second side portion of the impingement plate where the impingement side is axially spaced from the second side portion to define an impingement air plenum therebetween. The cooling flow return passage is in fluid communication with the impingement air plenum. A fluid conduit extends from a first side portion of the impingement plate towards a first end portion of the shroud. The fluid conduit is in fluid communication with the cooling flow return passage and provides for fluid communication out of the impingement air plenum.Type: GrantFiled: August 19, 2014Date of Patent: October 18, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Lucas John Stoia, Patrick Benedict Melton, Carolyn Ashley Antoniono
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Patent number: 9470422Abstract: A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.Type: GrantFiled: October 22, 2013Date of Patent: October 18, 2016Assignee: Siemens Energy, Inc.Inventors: David J. Wiebe, Richard C. Charron, Jay A. Morrison
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Patent number: 9464809Abstract: Disclosed is a gas turbine combustor equipped with a burner constructed to fire a plurality of combustors at the same time at a fuel/air ratio suitable for gas turbine ignition. A plurality of supports mounted for fixing an air injection hole plate to the combustor are provided at substantially the same phase position as that of cross fire tubes, and combustion air allocations are adjusted. Thus, flame propagation during gas turbine ignition is accelerated and all combustor cans are fired. In addition, porous plates are disposed downstream of the supports and the combustion air allocations are readjusted. Furthermore, air injection holes proximate to the cross fire tubes are particularly reduced in diameter to further adjust the combustion air allocations.Type: GrantFiled: July 2, 2013Date of Patent: October 11, 2016Assignee: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Kazuki Abe, Tomomi Koganezawa, Takeo Saito, Keisuke Miura
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Patent number: 9447971Abstract: A system includes a compressor that compresses incoming airflow, and a combustor assembly mixing the compressed incoming airflow with fuel and combusting the air and fuel mixture in a combustion zone. The combustor assembly includes a hot side downstream of the combustion zone and a cold side upstream of the combustion zone. The system also includes a turbine receiving products of combustion from the combustor. The combustor assembly includes a resonator positioned in the cold side of the combustor assembly in an annular passage between a flow sleeve and a casing of the combustor assembly.Type: GrantFiled: May 2, 2012Date of Patent: September 20, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Kwanwoo Kim, Fei Han, Praveen Jain, Venkat Narra, Sven Georg Bethke
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Patent number: 9429032Abstract: A combustor transition adapted to guide combustion gases in a hot gas flow path extending between a can combustor and a first stage of turbine in a gas turbine is disclosed. The combustor transition includes a duct having an upstream end adapted for connection to the can combustor and a downstream end adapted for connection to a first stage of a turbine, wherein the downstream end includes an outer wall, an inner wall, a first and a second side wall. At least one side wall has a side wall extension which extends in a downstream direction beyond the outlet. The side wall extension at least partly encloses a first resonator volume and at least one side wall extension includes a resonator hole, which is configured as a neck of a Helmholtz-damper. A method for retrofitting a gas turbine and method for borescope inspection of a GT are disclosed.Type: GrantFiled: October 24, 2013Date of Patent: August 30, 2016Assignee: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Mirko Ruben Bothien, Michael Düsing
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Patent number: 9404421Abstract: A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (IEPs) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an IEP and an inner support structure on the engine. The bracket structure includes an axial bracket member attached to an IEP and extending axially in a forward direction. A transverse bracket member has an end attached to the inner support structure and extends circumferentially to a connection with a forward end of the axial bracket member. The transverse bracket member provides a fixed radial position for the forward end of the axial bracket member and is flexible in the axial direction to permit axial movement of the axial bracket member.Type: GrantFiled: January 23, 2014Date of Patent: August 2, 2016Assignee: SIEMENS ENERGY, INC.Inventors: Richard C. Charron, William W. Pankey, Clinton A. Mayer, Benjamin G Hettinger
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Patent number: 9366438Abstract: A combustor assembly in a gas turbine engine includes a liner defining a combustion zone, at least one fuel injector for providing fuel, and a flow sleeve. An inner surface of the flow sleeve defines an outer boundary for an air flow passageway. Upon the air reaching a head end of the combustor assembly at an end of the air flow passageway the air turns 180 degrees to flow into the combustion zone where it is burned with the fuel. The combustor assembly further includes an inlet assembly positioned radially between the liner and the flow sleeve. The inlet assembly defines an inlet to the air flow passageway and includes a plurality of overlapping conduits that are arranged such that the air entering the air flow passageway passes through radial spaces between adjacent conduits.Type: GrantFiled: February 14, 2013Date of Patent: June 14, 2016Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Rajesh Rajaram, Juan Enrique Portillo Bilbao, Danning You
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Patent number: 9359955Abstract: An apparatus for supporting an aft portion of a transition duct in a gas turbine engine includes a transition aft frame that engages with an annular shaped stator component disposed in a turbine section of the gas turbine engine. The transition aft frame includes radially inner and outer panels and circumferentially spaced first and second side panels connecting the inner and outer panels. A forward face of the stator component includes first and second connection points circumferentially spaced apart. The transition aft frame includes first and second attachment structures that respectively engage with the first and second connection points when the transition duct is aligned axially with the stator component. The first and second attachment structures are spaced apart in a manner effective to transfer moment load from the first and second attachment structures to the first and second side panels respectively.Type: GrantFiled: August 28, 2014Date of Patent: June 7, 2016Assignee: Siemens Energy, Inc.Inventor: William W. Pankey
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Patent number: 9347328Abstract: A compressed air supply system for routing compressed air from a compressor to at least one combustor of a gas turbine engine is disclosed. The compressed air supply system may be formed from one or more plenums having an upstream end in fluid communication with an inner chamber of the compressor in which air is compressed and having a downstream end in fluid communication with the at least one combustor. Channeling compressed air through the plenum reduces damage to other components by confining the compressed air within the plenum. An upstream end of the plenum may be sealed to at least a portion of the compressor, and a downstream end of the plenum may be sealed to at least a portion of one or more combustors.Type: GrantFiled: August 9, 2010Date of Patent: May 24, 2016Assignee: SIEMENS ENERGY, INC.Inventor: Richard Charron
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Patent number: 9335052Abstract: According to one aspect of the invention, a combustor assembly for a pair of adjacent combustors includes a first passage formed in a liner of a first combustor and a flow sleeve disposed outside the liner of the first combustor, wherein the flow sleeve includes a window and a second passage aligned with the first passage. The assembly also includes a cross-fire tube disposed in the first passage to provide fluid communication between the first combustor and a second combustor and a retention clip disposed through the window to urge the cross-fire tube against an outer surface of the liner to enable the cross-fire tube to receive fluid through the first passage.Type: GrantFiled: November 8, 2012Date of Patent: May 10, 2016Assignee: General Electric CompanyInventor: Richard Martin DiCintio
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Patent number: 9291102Abstract: A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each include a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures defines a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.Type: GrantFiled: September 7, 2011Date of Patent: March 22, 2016Assignee: SIEMENS ENERGY, INC.Inventors: Timothy A. Fox, Reinhard Schilp
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Patent number: 9200526Abstract: A transition piece 10 in an embodiment is provided with an inner duct 20 through which a combustion gas is led to a turbine part 130 and an outer duct 30 that is provided so as to cover an outer periphery of the inner duct 20 and has a plurality of ejection holes 31 to eject air onto an outer peripheral surface of the inner duct 20 formed therein. It is structured such that a channel cross-sectional area of a cooling air channel 50 that is formed between the inner duct 20 and the outer duct 30 and through which the air ejected from the ejection holes 31 flows gradually decreases at an air flow downstream side rather than the portion where the ejection holes 31 are formed, and gradually increases from a throat portion 60 having the minimized channel cross-sectional area to an air flow downstream side.Type: GrantFiled: December 20, 2011Date of Patent: December 1, 2015Assignee: Kabushiki Kaisha ToshibaInventors: Shoko Ito, Daizo Saito, Yoshiaki Sakai
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Patent number: 9182122Abstract: A device for supplying flow across a combustor includes an axial fluid injector configured to circumferentially surround at least a portion of the combustor. An inner annular passage extends through the axial fluid injector and provides fluid communication through the axial fluid injector and into a first annular passage that surrounds the combustor. An outer annular passage extends through the axial fluid injector radially outward from the inner annular passage and provides axial flow into the first annular passage. A method for supplying flow to a combustor includes flowing a first portion of a working fluid through a first axial flow path and flowing a second portion of the working fluid through a second axial flow path.Type: GrantFiled: October 5, 2011Date of Patent: November 10, 2015Assignee: GENERAL ELECTRIC COMPANYInventors: John M. Matthews, Keith C. Belsom, Ronald James Chila
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Patent number: 9133721Abstract: A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.Type: GrantFiled: November 15, 2010Date of Patent: September 15, 2015Assignee: SIEMENS ENERGY, INC.Inventors: Ching-Pang Lee, Jay A. Morrison
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Patent number: 9097117Abstract: A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.Type: GrantFiled: November 15, 2010Date of Patent: August 4, 2015Assignee: SIEMENS ENERGY, INCInventors: Richard C. Charron, Daniel J. Pierce, Jay A. Morrison, Ching-Pang Lee, Kenneth K. Landis, Walter Marussich
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Patent number: 9032704Abstract: A system and method for reducing combustion dynamics includes first and second combustors arranged about an axis, and each combustor includes a cap assembly that extends radially across at least a portion of the combustor and a combustion chamber downstream from the cap assembly. Each cap assembly includes a plurality of tubes that extend axially through the cap assembly to provide fluid communication through the cap assembly to the combustion chamber and a fuel injector that extends through each tube to provide fluid communication into each tube. Each cap assembly has an axial length, and the axial length of the cap assembly in the first combustor is different than the axial length of the cap assembly in the second combustor.Type: GrantFiled: August 21, 2012Date of Patent: May 19, 2015Assignee: GENERAL ELECTRIC COMPANYInventors: Sarah Lori Crothers, Gilbert Otto Kraemer
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Patent number: 9021783Abstract: The engine (10) includes at least one firing tube (12) wherein an exhaust stream (32) from the firing tube (12) drives a turbine (30). A scroll ejector attenuator (40) is secured between and in fluid communication with an outlet end (28) of the firing tube (12) and an inlet (76) of the turbine (30). The attenuator (40) defines a turning, narrowing passageway (72) that extends a distance the exhaust stream (32) travels before entering the turbine (30) to attenuate shockwaves and mix the pulsed exhaust stream (32) into an even stream with minimal temperature differences to thereby enhance efficient operation of the turbine (30) without any significant pressure decline of exhaust stream (32) pressure and without any backpressure from the attenuator (40) on the firing tube (12).Type: GrantFiled: October 12, 2012Date of Patent: May 5, 2015Assignee: United Technologies CorporationInventors: James D. Hill, Michael J. Cuozzo
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Patent number: 9010127Abstract: A transition piece aft frame assembly is provided, and includes a transition piece aft frame and a heat shield. The transition piece aft frame has an aft face. At least a portion of the aft face is exposed to an exhaust gas stream. The heat shield is connected to the transition piece aft frame. The heat shield is oriented to generally deflect the exhaust gas stream away from the aft face of the transition piece aft frame.Type: GrantFiled: March 2, 2012Date of Patent: April 21, 2015Assignee: General Electric CompanyInventors: Christopher Paul Willis, William Lawrence Byrne, David William Cihlar, Donald Timothy Lemon, Patrick Benedict Melton
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Patent number: 9003800Abstract: A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket.Type: GrantFiled: July 2, 2012Date of Patent: April 14, 2015Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Shinji Akamatsu, Hiroaki Kishida, Kenji Sato, Kentaro Tokuyama, Keisuke Matsuyama, Takayoshi Takashima
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Patent number: 8978389Abstract: A gas turbine engine (10), including: a turbine having radial inflow impellor blades (38); and an array of advanced transition combustor assemblies arranged circumferentially about the radial inflow impellor blades (38) and having inner surfaces (34) that are adjacent to combustion gases (40). The inner surfaces (34) of the array are configured to accelerate and orient, for delivery directly onto the radial inflow impellor blades (38), a plurality of discrete flows of the combustion gases (40). The array inner surfaces (34) define respective combustion gas flow axes (20). Each combustion gas flow axis (20) is straight from a point of ignition until no longer bound by the array inner surfaces (34), and each combustion gas flow axis (20) intersects a unique location on a circumference defined by a sweep of the radial inflow impellor blades (38).Type: GrantFiled: December 15, 2011Date of Patent: March 17, 2015Assignee: Siemens Energy, Inc.Inventor: David J. Wiebe
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Patent number: 8959919Abstract: A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket.Type: GrantFiled: July 2, 2012Date of Patent: February 24, 2015Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Shinji Akamatsu, Hiroaki Kishida, Kenji Sato, Kentaro Tokuyama, Keisuke Matsuyama, Takayoshi Takashima
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Patent number: 8959925Abstract: A method is disclosed for controlling gas turbine operation in response to lean blowout of a combustion can. The gas turbine comprises a pair of combustion cans. The method includes sensing that a first combustion can is extinguished during a full load operation of the gas turbine, adjusting a fuel ratio between the fuel nozzles in each can, delivering a richer fuel mixture to the fuel nozzles nearest to the cross-fire tubes, generating a cross-fire from the second combustion can to the first combustion can, detecting a recovery of the turbine load, and adjusting the fuel ratio to the normal balanced fuel distribution between the fuel nozzles in each can.Type: GrantFiled: January 18, 2012Date of Patent: February 24, 2015Assignee: General Electric CompanyInventors: Bryan Wesley Romig, Derrick Walter Simons, Venkat Narra
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Patent number: 8959886Abstract: A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having an inner surface, an outer surface, a region, an inlet, and an outlet. The inner surface defines an inner volume of the conduit. The region extends between the inner and outer surfaces and includes cooling fluid structure defining a plurality of cooling passageways. The inlet extends inwardly from the outer surface and provides fluid communication between the inlet and the passageways. The outlet extends from the passageways to the inner surface to provide fluid communication between the passageways and the inner volume. At least one first cooling passageway intersects with at least one second cooling passageway such that cooling fluid flowing through the first cooling passageway interacts with cooling fluid flowing through the second cooling passageway.Type: GrantFiled: July 8, 2010Date of Patent: February 24, 2015Assignees: Siemens Energy, Inc., Mikro Systems, Inc.Inventors: Ching-Pang Lee, Humberto A. Zuniga, Jay A. Morrison
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Patent number: 8955332Abstract: A gas turbine combustor including a fuel nozzle for injecting mixed gas of fuel and air, a cylindrical liner for burning and reacting the mixed gas of fuel and air in a combustion chamber, a transition piece which is a flow path for leading combustion gas generated in the liner to turbine blades, and a transition piece flow sleeve for wrapping an outside surface of the transition piece, wherein a plurality of air introduction holes for introducing air into the transition piece flow sleeve are formed in regions of the transition piece flow sleeve excluding regions which are corner portions of the transition piece flow sleeve in a sectional direction thereof.Type: GrantFiled: July 8, 2014Date of Patent: February 17, 2015Assignee: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Takeo Saitou, Yasuyuki Watanabe, Shouhei Yoshida
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Patent number: 8915706Abstract: A transition nozzle is provided and includes a liner in which combustion occurs and through which products of the combustion flow toward a turbine bucket stage. The liner includes opposing endwalls and opposing sidewalls extending between the opposing endwalls. The opposing sidewalls are oriented to tangentially direct the flow of the combustion products toward the turbine bucket stage. At least one of the opposing endwalls and the opposing sidewalls including a flow contouring feature to guide the flow of the combustion products.Type: GrantFiled: October 18, 2011Date of Patent: December 23, 2014Assignee: General Electric CompanyInventors: Alexander Stein, Gunnar Leif Siden
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Patent number: 8893501Abstract: The present application and the resultant patent provide a combustor for mixing a flow of air and a flow of fuel. The combustor may include an air path for the flow of air, a number of fuel injectors positioned in the air path for the flow of fuel, and a crossfire tube positioned within the air path upstream of the fuel injectors. The crossfire tube may include a number of purge holes positioned on a downstream side thereof to reduce a wake in the flow of air caused by the crossfire tube in the air path.Type: GrantFiled: March 28, 2011Date of Patent: November 25, 2014Assignee: General Eletric CompanyInventors: Carolyn Ashley Antoniono, Patrick Benedict Melton
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Patent number: 8868313Abstract: A method for controlling the combustion in a gas turbine including measuring, with one or more probes situated adjacent to the combustion chamber of the turbine, the amplitude of the pressure oscillations inside the combustion chamber and the persistence time or cycle of the same oscillations, evaluating the behavior under fatigue conditions of the combustion chamber, by constructing the Wohler curve for a certain material which forms the combustion chamber for a predefined combustion frequency and for the amplitude and cycle values of the pressure oscillations measured, measuring the cumulative damage to the combustion chamber during functioning under fatigue conditions of the turbine using the Palmgren-Miner hypothesis and exerting protection actions of the turbine if the cumulative damage value measured is exceeded.Type: GrantFiled: April 7, 2008Date of Patent: October 21, 2014Assignee: Nuovo Pignone S.p.A.Inventor: Antonio Asti
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Patent number: 8844260Abstract: A low calorific value fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the liner also defining inner combustion and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A nozzle assembly disposed at the closed housing end includes an air blast nozzle and surrounding swirl vanes. An impingement cooling sleeve coaxially disposed in the combustion air passage between the housing and the liner impingement cools the portion of the liner defining the combustion zone. The combustion liner has an L/D ratio of in the range 1?L/D?4, and a ratio of the combustion zone volume (m3) to heat energy flow rate Q (MJ/sec) in the range 0.0026?V/Q?0.018.Type: GrantFiled: November 9, 2010Date of Patent: September 30, 2014Assignee: Opra Technologies B.V.Inventors: Martin Beran, Michal Koranek, Axel Lars-Uno Eugen Axelsson
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Patent number: 8784096Abstract: An air-fuel burner includes a heat-transfer tube, an air-fuel mixing chamber, and an air-fuel nozzle. The air-fuel nozzle is coupled to the air-fuel chamber to communicate a combustible air-fuel mixture into a combustion chamber defined between the air-fuel nozzle and the heat-transfer tube. The combustible air-fuel mixture, when ignited, establishes a flame in the combustion chamber to produce heat which is transferred through heat-transfer tube to an adjacent medium external to the heat-transfer tube.Type: GrantFiled: September 29, 2009Date of Patent: July 22, 2014Assignee: Honeywell International Inc.Inventor: Pawel Mosiewicz
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Patent number: 8763401Abstract: There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage.Type: GrantFiled: May 30, 2011Date of Patent: July 1, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Enzo Macchia, Oleg Morenko, George Guglielmin
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Patent number: 8745986Abstract: A fuel supply system for a gas turbine includes a combustion section, a transition duct downstream from the combustion section, a turbine section downstream from the transition duct, and a first stage of stationary vanes circumferentially arranged inside the turbine section. A hot gas path is between the transition duct and the stationary vanes, and a fuel injector provides fluid communication into the hot gas path. A method of supplying fuel to a gas turbine includes combusting a first fuel in a combustion chamber to produce combustion gases, flowing the combustion gases through a transition duct to a hot gas path, and flowing the combustion gases through the hot gas path to a first stage of stationary vanes in a turbine section. The method further includes injecting a second fuel into the hot gas path downstream from the transition duct and upstream from the first stage of stationary vanes.Type: GrantFiled: July 10, 2012Date of Patent: June 10, 2014Assignee: General Electric CompanyInventors: Patrick Benedict Melton, Bryan Wesley Romig, Lucas John Stoia, Thomas Edward Johnson
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Patent number: 8739511Abstract: A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of fuel and air. Fuel, air and/or fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides an optimal mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.Type: GrantFiled: May 3, 2010Date of Patent: June 3, 2014Inventors: Majed Toqan, Brent Allan Gregory, Jonathan David Regele, Ryan Sadao Yamane
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Publication number: 20140144122Abstract: A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.Type: ApplicationFiled: November 29, 2012Publication date: May 29, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Brandon Taylor Overby, Keith Cletus Belsom, Jonathan Kay Allen, Kyle Eric Benson, Patrick Benedict Melton, Richard Martin DiCintio, Lucas John Stoia, Ronnie Ray Pentecost
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Publication number: 20140137535Abstract: The present application provides a clocked combustor can array for coherence reduction in a gas turbine engine. The clocked combustor can array may include a number of combustor cans positioned in a circumferential array. A first set of the combustor cans may have a first orientation and a second set of the combustor cans may have a second orientation.Type: ApplicationFiled: November 20, 2012Publication date: May 22, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Won-Wook Kim, Kevin Weston McMahan, Shiva Kumar Srinivasan
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Publication number: 20140137536Abstract: A super-telescoping cross-fire tube includes a cross-fire tube including a first portion and a second portion in mating engagement, the cross-fire tube extending from a first end region to a second end region for fluidly connecting a combustor chamber and an adjacent combustor chamber. Also included is an outer shield spaced radially outwardly and surrounding at least a portion of the cross-fire tube. Further included is a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and the outer shield, wherein the cross-fire tube is telescopingly moveable between a first position and a second position.Type: ApplicationFiled: November 21, 2012Publication date: May 22, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Joel Russell Cloninger, Patrick Benedict Melton, Lucas John Stoia, James Harold Westmoreland
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Publication number: 20140123619Abstract: According to one aspect of the invention, a combustor assembly for a pair of adjacent combustors includes a first passage formed in a liner of a first combustor and a flow sleeve disposed outside the liner of the first combustor, wherein the flow sleeve includes a window and a second passage aligned with the first passage. The assembly also includes a cross-fire tube disposed in the first passage to provide fluid communication between the first combustor and a second combustor and a retention clip disposed through the window to urge the cross-fire tube against an outer surface of the liner to enable the cross-fire tube to receive fluid through the first passage.Type: ApplicationFiled: November 8, 2012Publication date: May 8, 2014Applicant: GENERAL ELECTRIC COMPANYInventor: Richard Martin DiCintio
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Patent number: 8707707Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto is combustible, a turbine, including rotating turbine blades, into which products of at least the combustion of the first fuel are receivable to power a rotation of the turbine blades, a transition zone, including a second interior in which a second fuel supplied thereto and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are supported by the transition zone and coupled to a fuel circuit, and which are configured to supply the second fuel to the second interior in any one or more of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.Type: GrantFiled: January 7, 2009Date of Patent: April 29, 2014Assignee: General Electric CompanyInventors: Krishna Kumar Venkataraman, Jason Charles Terry, Chetan Babu Velkur, Hasan Karim
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Patent number: 8707673Abstract: Turbine systems are provided. A turbine system includes a transition duct comprising an inlet, an outlet, and a duct passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The duct passage includes an upstream portion and a downstream portion. The upstream portion extends from the inlet between an inlet end and an aft end. The downstream portion extends from the outlet between an outlet end and a head end. The turbine system further includes a joint coupling the aft end of the upstream portion and the head end of the downstream portion together. The joint is configured to allow movement of the upstream portion and the downstream portion relative to each other about or along at least one axis.Type: GrantFiled: January 4, 2013Date of Patent: April 29, 2014Assignee: General Electric CompanyInventors: James Scott Flanagan, Kevin Weston McMahan, Jeffrey Scott LeBegue, Ronnie Ray Pentecost
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Patent number: 8707672Abstract: A combustor includes an end cap having a perforated downstream plate and a combustion chamber downstream of the downstream plate. A plenum is in fluid communication with the downstream plate and supplies a cooling medium to the combustion chamber through the perforations in the downstream plate. A method for cooling a combustor includes flowing a cooling medium into a combustor end cap and impinging the cooling medium on a downstream plate in the combustor end cap. The method further includes flowing the cooling medium into a combustion chamber through perforations in the downstream plate.Type: GrantFiled: September 10, 2010Date of Patent: April 29, 2014Assignee: General Electric CompanyInventors: Baifang Zuo, Roy Marshall Washam, Chunyang Wu
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Patent number: 8701418Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel is combustible, the first fuel including natural gas and/or a blend of natural gas and alternate gas receivable by a fuel circuit from an external source, a turbine, a transition zone, including a second interior in which a second fuel, the second fuel including an unblended supply of the alternate gas receivable by the fuel circuit from the external source, and the products of the combustion of the first fuel are combustible, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.Type: GrantFiled: January 7, 2009Date of Patent: April 22, 2014Assignee: General Electric CompanyInventors: Krishna Kumar Venkataraman, Jason Charles Terry
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Patent number: 8701383Abstract: A gas turbine engine is provided and includes a late lean injection (LLI) compatible combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.Type: GrantFiled: January 7, 2009Date of Patent: April 22, 2014Assignee: General Electric CompanyInventors: Krishna Kumar Venkataraman, Roy Marshall Washam, Hasan Karim, Jason Charles Terry, Lewis Berkley Davis, Jr.
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Patent number: 8701382Abstract: A gas turbine engine is provided and includes a fuel circuit, including multiple fuel circuit branches, a combustor having a first interior in which a first fuel supplied thereto by any one of the multiple fuel circuit branches is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by any one of the multiple fuel circuit branches, the second fuel including gas receivable by the fuel circuit from an external source, and the products of the combustion of the first fuel are combustible, the transition zone being disposed to fluidly couple the combustor and the turbine to one another, and a plurality of fuel injectors which supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages.Type: GrantFiled: January 7, 2009Date of Patent: April 22, 2014Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Krishna Kumar Venkataraman, Willy Steve Ziminsky, Jason Charles Terry
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Patent number: 8695322Abstract: A turbomachine includes a plurality of injection nozzles arranged in a can-annular array and a transition piece including at least one wall that defines a combustion flow passage. A dilution orifice is formed in the at least one wall of the transition piece. The dilution orifice guides dilution gases to the combustion flow passage. A heat shield member is mounted to the at least one wall of the transition piece in the combustion flow passage. The heat shield member includes a body having a first surface and an opposing second surface through which extends a dilution passage. The dilution passage is off-set from the dilution orifice. The heat shield member is spaced from the at least one wall of the transition piece defining a flow region between the at least one wall and the second surface.Type: GrantFiled: March 30, 2009Date of Patent: April 15, 2014Assignee: General Electric CompanyInventors: Lewis Berkley Davis, Jr., Ronald James Chila
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Patent number: 8683808Abstract: A gas turbine engine is provided and includes a combustor having a first interior in which a first fuel supplied thereto by a fuel circuit is combustible, a turbine, a transition zone, including a second interior in which a second fuel supplied thereto by the fuel circuit and the products of the combustion of the first fuel are combustible, a plurality of fuel injectors, which are structurally supported by the transition zone and coupled to the fuel circuit, and which are configured to supply the second fuel to the second interior in any one of a single axial stage, multiple axial stages, a single axial circumferential stage and multiple axial circumferential stages, and a control system coupled to the fuel circuit and configured to control relative amounts of the first and second fuels supplied by the fuel circuit to the first and second interiors.Type: GrantFiled: January 7, 2009Date of Patent: April 1, 2014Assignee: General Electric CompanyInventors: Krishna Kumar Venkataraman, Lewis Berkley Davis, Jr.
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Patent number: 8671692Abstract: A combustor assembly includes a convergent segment followed by a divergent segment to advantageously improve combustion. The combustor assembly includes a first segment beginning at a forward end that transitions to a second segment past a transition segment in a direction along a combustor axis toward an aft end. The reduction in cross-sectional area within the first segment provides desirable fuel and air mixing properties. The convergent first segment in combination with the divergent second segment decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.Type: GrantFiled: October 3, 2011Date of Patent: March 18, 2014Assignee: United Technologies CorporationInventors: Steven W. Burd, William Sowa, Albert K. Cheung, Stephen Karl Kramer, Reid Dyer Curtis Smith, James Hoke
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Patent number: 8667801Abstract: An enhanced cooling system for the downstream end of a combustor liner assembly is provided. The downstream end region of the combustor liner assembly is formed by a subassembly comprising an outer tubular member, an inner tubular member and a middle band. The middle band includes a plurality of undulations having alternating peaks and valleys. The middle band is operatively positioned between the inner and outer tubular members to form a plurality of elongated cooling passages. A turbulence generator is provided along each of the cooling passages and extends radially inward from a portion of the peaks such that the turbulence generator and the valleys contact an outer peripheral surface of the inner tubular member. The surface area of the middle band that is in contact with the inner tubular member is greater than the surface area of the middle band that is in contact with the outer tubular member.Type: GrantFiled: September 8, 2010Date of Patent: March 11, 2014Assignee: Siemens Energy, Inc.Inventor: Carlos Roldan-Posada