Patents Examined by Gerald Sung
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Patent number: 8186142Abstract: Systems and a method for controlling a temperature of an exhaust gas stack are provided. The system includes a first heat exchanger positioned upstream in exhaust gas flow communication to an exhaust gas inlet to the stack, a second heat exchanger positioned upstream in exhaust gas flow communication to the first heat exchanger, and a water side conduit configured to direct a flow of relatively hot water from the second heat exchanger to the first heat exchanger such that a temperature of a flow of exhaust gas flowing through the first exchanger is maintained within a predetermined range.Type: GrantFiled: August 5, 2008Date of Patent: May 29, 2012Assignee: General Electric CompanyInventors: Prakash Narayan, Shinoj Vakkayil Chandrabose, Pemmi Bhaskar
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Patent number: 8186144Abstract: A dual-flow turbomachine (10), essentially comprising a fan (14), a compressor (20), a combustion chamber (21), a turbine (22) and an exhaust casing (24), which comprises an auxiliary air compressor (48) driven by a Stirling engine (53) mounted downstream of the combustion chamber (21) and having a hot chamber in thermal contact with the flow (B) of hot gases leaving the turbine and a cold chamber in thermal contact with a flow (A) of cold gases generated by the fan (14) and flowing around the turbine (22) and the exhaust casing (24).Type: GrantFiled: August 28, 2008Date of Patent: May 29, 2012Assignee: SNECMAInventors: Laurent Donatien Behaghel, Pascal Coat, Arnaud Jean-Marie Pierrot, Stephane Rousselin
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Patent number: 8171717Abstract: A coordinated air-fuel controller and associated method provide a fuel controller, a combustion air controller and a steady-state air versus fuel model. The fuel controller generates a fuel control output signal and the combustion air controller generates a combustion air control output signal. The fuel controller determines a preliminary fuel control signal based on at least one of first and second loop control signals, and determines the fuel control output signal based on the preliminary fuel control signal. The steady-state air versus fuel model processes the preliminary fuel control signal to determine an expected steady-state combustion air control signal. The combustion air controller determines a preliminary combustion air control signal based on at least one of a third loop control signal and a fourth loop control signal, and determines the combustion air control output signal based on the preliminary combustion air control signal and the expected steady-state combustion air control signal.Type: GrantFiled: May 14, 2010Date of Patent: May 8, 2012Assignee: General Electric CompanyInventors: Matthew John Mosley, Christopher Eugene Long, David Spencer Ewens
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Patent number: 8171739Abstract: An apparatus for internally mounting a fuel manifold within a surrounding casing in a gas turbine engine which includes a fuel manifold and support pins which are displaceable relative to mounting portions on the fuel manifold between a retracted position, wherein the fuel manifold is able to be inserted within a casing of the engine, and an extended position, wherein the support pins project outwardly from the fuel manifold for engagement with the casing.Type: GrantFiled: April 27, 2009Date of Patent: May 8, 2012Assignee: Pratt & Whitney Canada Corp.Inventor: Jason Araan Fish
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Patent number: 8161754Abstract: Varying the fan nozzle flow area in a gas turbine engine allows adjustment of the bypass flow for varying operational conditions such as cruise and take off. However, care must be taken with regard to variation in order not to introduce drag or operational susceptibility to failure. By provision of a deformable member having a contiguous surface, which is deformed laterally from a splitter such as a pylon variation in flow area is achieved. A deformable member will be secured through seals to ensure a smooth surface. Actuation may be through a shape memory alloy material or provision of mechanical actuators to cause deformation of the contiguous surface.Type: GrantFiled: December 17, 2007Date of Patent: April 24, 2012Assignee: Rolls-Royce PLCInventors: Christopher Thomas John Sheaf, Miles Thomas Trumper
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Patent number: 8161727Abstract: A device for, in a gas turbine engine, braking a turbine including a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking is disclosed. The device includes a first braking member provided with at least one abrasive element and a second braking member including a ring-shaped element (120A) made of a material capable of being eroded by the abrasive element. One of the two braking members being secured to the rotor and the other of the two braking members being secured to the stator. The braking members come into contact with one another through axial displacement of the rotor once the shaft has broken. The abrasive element of the first braking member eroding the ring-shaped element of the second braking member.Type: GrantFiled: May 23, 2008Date of Patent: April 24, 2012Assignee: SNECMAInventors: Jacques Rene Bart, Didier Rene Andre Escure, Claude Marcel Mons, Stephane Rousselin
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Patent number: 8156745Abstract: An aircraft gas turbine engine exhaust nozzle basesheet includes longitudinally extending plurality of basesheet segments. Each of the basesheet segments includes a panel body between segment leading and trailing edges and slidable sealing joints with slidingly un-restrained center surfaces between adjacent segment leading and trailing edges. Segmented first and second basesheet side edges first and second segment side edges of the basesheet segments respectively. Slidably sealingly engaged overlapping flanges at the segment leading and trailing edges include tacked together transversely spaced apart first and second distal ends of the overlapping flanges. Leading and trailing edge ribs supporting the overlapping flanges are clipped together with longitudinally spaced apart and transversely extending forward and aft slits in retainers.Type: GrantFiled: February 29, 2008Date of Patent: April 17, 2012Assignee: General Electric CompanyInventors: Darrell Glenn Senile, Valentine Robert Boehm, Jr., Bernard James Renggli
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Patent number: 8151549Abstract: A high humidity gas turbine equipment includes a turbine; a compressor; a humidifier, which brings the air compressed by the compressor into contact with feed water to humidify the air; a regenerative heat exchanger, which causes the air humidified by the humidifier to be heated by exhaust gas from the turbine; a combustor, which burns the air heated by the regenerative heat exchanger and fuel to generate the combustion gas; a deaerating equipment including a deaerating section, a water storage tank, and a steam generating section, which causes feed water and makeup water in the water storage tank to be heated by exhaust gas from the turbine to evaporate and supplies the steam to the deaerating section; and a feed water supply pipe, through which the feed water and the makeup water in the water storage tank are supplied to the humidifier.Type: GrantFiled: August 5, 2008Date of Patent: April 10, 2012Assignee: Hitachi, Ltd.Inventors: Kenji Sasaki, Yoshiki Noguchi, Kenji Sakka, Hirotsugu Fukuhara
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Patent number: 8136361Abstract: A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.Type: GrantFiled: May 4, 2006Date of Patent: March 20, 2012Assignee: General Electric CompanyInventors: Carl Gerard Schott, Kevin W. Kinzie, John Joseph Lynch, David W. Ball, Gunnar Leif Siden, Kenneth Neil Whaling
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Patent number: 8127548Abstract: A turbine engine fuel supply system includes a priority flow line, a plurality of secondary fuel loads, an electric fuel metering pump, and a mechanically-driven fuel pump. The priority flow line is used to supply fuel to one or more gas turbine engine fuel manifolds. The electric fuel metering pump has a fuel inlet and a fuel outlet, and is adapted to be selectively energized and, upon being energized, to draw fuel into its fuel inlet and discharge the fuel from its fuel outlet for supply to the priority flow line. The mechanically-driven fuel pump has a fuel inlet, and a fuel outlet that is in fluid communication with the electric fuel metering pump fuel inlet and the plurality of secondary fuel loads. As such, fuel may be supplied to the secondary fuel loads independent of the electric fuel metering pump, which advantageously reduces the electrical power consumption of the electric fuel metering pump.Type: GrantFiled: February 21, 2008Date of Patent: March 6, 2012Assignee: Honeywell International Inc.Inventors: Bruce Anson, Jay Sims, Jack Carpenter, William Nolan
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Patent number: 8127533Abstract: The system and method described herein uses a hybrid pulsed detonation engine (PDE) system to drive a turbine that powers an electric generator. The combustion chamber of the PDE is shaped in a helical form, so that the external length of the section is reduced, while maintaining the distance for acceleration to detonation. This allows the achievement of deflagration to detonation transition without the help of turbulence enhancing obstacles, while keeping the overall size of the detonation tube small. The PDE output can be scaled by: increasing the cross sectional area of the detonation chamber; increasing the number of detonation tubes; and increasing the frequency of operation of the PDE. The replacement of conventional deflagrative internal combustion engines, including gas turbines and reciprocating engines, with pulsed detonation engines for electric power generation, may provide fuel savings and have a lower environmental impact.Type: GrantFiled: September 2, 2009Date of Patent: March 6, 2012Assignee: Board of Regents, The University of Texas SystemInventors: Frank K. Lu, Philip K. Panicker, Donald R. Wilson, Jiun-Ming Li
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Patent number: 8127534Abstract: There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle.Type: GrantFiled: February 19, 2008Date of Patent: March 6, 2012Assignee: Raytheon CompanyInventors: Robert J. Cavalleri, Thomas A. Olden
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Patent number: 8122725Abstract: Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustors of the plurality of can annular combustors wherein each set of combustors is supplied by a separately controllable respective fuel delivery system. The method includes supplying fuel at a first fuel schedule to the first set of combustors and supplying fuel at a second fuel schedule to the second set of combustors during a first mode of operation wherein the second fuel schedule is different than the first fuel schedule, and supplying fuel at the second fuel schedule to the first and second sets of combustors during a second mode of operation.Type: GrantFiled: November 1, 2007Date of Patent: February 28, 2012Assignee: General Electric CompanyInventors: Geoffrey David Myers, David August Snider, Eric Motter, Daniel R. Tegel, James Harper, Stephen R. Watts, Joseph Citeno
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Patent number: 8109074Abstract: An engine system comprises at least a first volumetric device, and a second volumetric device in which said second volumetric device is larger in volume than said first volumetric device, in which, during continuous flow of a compressible fluid from said first to said second volumetric device work is performed.Type: GrantFiled: March 10, 2003Date of Patent: February 7, 2012Assignee: Newton Propuslion TechnologiesInventor: Haim Rom
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Patent number: 8099960Abstract: A fuel-air mixer includes an annular shroud, inner and outer counter-rotating swirlers, a hub separating the inner and outer swirlers, a center body extending axially along the annular shroud, a fuel shroud disposed radially outwardly from the outer swirler circumferentially around the annular shroud, and a radial swirler disposed downstream of the inner and outer swirlers, the radial swirler being configured to allow an independent radial rotation of a second gas stream entering the annular shroud from a region outside a wall of the annular shroud separately from a stream flowing through the inner and outer swirlers, the radially rotating second gas stream entering the annular shroud at a region adjacent an outer wall of the annular shroud.Type: GrantFiled: November 17, 2006Date of Patent: January 24, 2012Assignee: General Electric CompanyInventors: Ahmed Mostafa Elkady, Andrei Tristan Evulet
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Patent number: 8096131Abstract: An inlet tube within a gas turbine engine which includes a primary fuel channel and a secondary fuel channel formed in a cylindrical tube body. The secondary channel has a substantially crescent shaped cross-sectional area which is complementary in shape to the primary fuel channel, such as to maximize the combined fuel flow area through the primary and secondary fuel channels relative to an outer diameter of the cylindrical tube body.Type: GrantFiled: November 14, 2007Date of Patent: January 17, 2012Assignee: Pratt & Whitney Canada Corp.Inventors: Reza Ziaei, Eduardo Hawie
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Patent number: 8096130Abstract: A gas turbine engine fuel conveying member in fluid flow communication with at least one fuel nozzle, the fuel conveying member having at least first and second member portions sealingly engaged to one another, and means for conveying fuel defined at a junction between the first and second member portions. The means for conveying fuel is defined by at least part of two different walls of each of the first and second member portions.Type: GrantFiled: July 20, 2006Date of Patent: January 17, 2012Assignee: Pratt & Whitney Canada Corp.Inventor: Oleg Morenko
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Patent number: 8070453Abstract: A centrifugal impeller having an inlet and a plurality of outlets, the outlets including at least one outlet in a forward direction of the impeller and at least one outlet in a rearward direction of the impeller. A flow path distance of the outlet in the forward direction can be greater than a flow path distance of the outlet in the rearward direction in order to provide a greater pressure in the outlet having the greater flow path distance. In another embodiment, the flow path volume in the forward direction can be greater than the flow path volume in the rearward direction in order to provide a greater flow volume in the forward direction. In another embodiment, the number of flow paths in the forward direction can be greater than the number of flow paths in the rearward direction in order to provide a greater flow volume in the forward direction.Type: GrantFiled: December 13, 2009Date of Patent: December 6, 2011Assignee: Florida Turbine Technologies, Inc.Inventor: Alfred P Matheny
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Patent number: 8069671Abstract: A burner (1) for a combustion chamber of a turbogroup includes a swirl generator (2), a mixer (3), and a lance (4) for introducing pilot fuel into a combustion space (10). In order to stabilize combustion, the lance (4) is designed and/or arranged so that, at least in the pilot mode of the burner (1), it extends far enough into the burner interior (5) for a flame front (16) of a combustion reaction, which takes place in the combustion space (10), to extend at least partially into the burner interior (5).Type: GrantFiled: January 27, 2010Date of Patent: December 6, 2011Assignee: ALSTOM Technology Ltd.Inventors: Jaan Hellat, Adnan Eroglu, Jan Cerny, Douglas Anthony Pennell
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Patent number: 8061119Abstract: An actuation mechanism for use in a convertible gas turbine propulsion system comprises a plenum, a pneumatically powered drive body and a spring system. The plenum receives pressurized air from the convertible gas turbine propulsion system. The pneumatically powered drive body is connected to the plenum to receive pressurized air to axially move the drive body in a first direction. The spring system is connected to the drive body to axially move the drive body in a second direction.Type: GrantFiled: November 29, 2007Date of Patent: November 22, 2011Assignee: United Technologies CorporationInventors: Rajendra K. Agrawal, Gregory E. Reinhardt