Patents Examined by Steven Sutherland
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Patent number: 9803481Abstract: A rotor for a turbomachine includes a rim defining a base of a rotor, an airfoil shaped blade extending from said rim and defining a chord line and a bore extending from said rim opposite said airfoil shaped blade. The rim further includes at least one rail extending away from said airfoil shaped blade.Type: GrantFiled: June 16, 2015Date of Patent: October 31, 2017Assignee: United Technologies CorporationInventors: Nicholas Aiello, Bob S. Bamford
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Patent number: 9797289Abstract: The invention provides systems and methods for electric power production and integrated combustion and emissions control. The invention may include an engine capable of receiving air and fuel, and producing power and an engine exhaust gas. The invention may also include a first reaction zone receiving the engine exhaust gas from the engine configured to combust fuel and air having an equivalence ratio of more than one, thereby generating a first product. The combustion may reduce nitrogen containing species. The invention may also include a second reaction zone receiving the engine exhaust gas from the engine configured to combust fuel and air having an equivalence ratio of less than one, thereby generating a second product. The combustion may reduce or minimize NOx. The invention may also include a mixing zone configured to receive the first product and second product, and mix and react the first and second products, thereby generating an exhaust with reduced NOx levels.Type: GrantFiled: May 15, 2015Date of Patent: October 24, 2017Assignee: ALTEX TECHNOLOGIES CORPORATIONInventors: John T. Kelly, Carlo Castaldini, Mehdi Namazian
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Patent number: 9777926Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.Type: GrantFiled: January 9, 2015Date of Patent: October 3, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Zhongtao Dai, Jeffrey M. Cohen, Catalin G. Fotache, Lance L. Smith, Donald J. Hautman
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Patent number: 9752440Abstract: A component for a turbine engine includes a substrate that includes a first surface, and an insert coupled to the substrate proximate the substrate first surface. The component also includes a channel. The channel is defined by a first channel wall formed in the substrate and a second channel wall formed by at least one coating disposed on the substrate first surface. The component further includes an inlet opening defined in flow communication with the channel. The inlet opening is defined by a first inlet wall formed in the substrate and a second inlet wall defined by the insert.Type: GrantFiled: May 29, 2015Date of Patent: September 5, 2017Assignee: General Electric CompanyInventors: Carlos Miguel Miranda, Andrew Lee Trimmer, Srikanth Chandrudu Kottilingam, Benjamin Paul Lacy
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Patent number: 9752508Abstract: Air Turbine Starters (ATSs) having oil feed shutoff valves are provided, as are gas turbine engines including ATSs. In one embodiment, the ATS includes an ATS housing assembly containing a sump chamber, an oil inlet, and a valve cavity. A rejected oil return passage is further formed in the ATS housing assembly and fluidly coupled to the valve cavity. An oil feed shutoff valve is positioned in the valve cavity and contains a valve element movable between open and closed positions. In the open position, the valve element permits oil flow from the oil inlet, through the valve cavity, and into the sump chamber. In the closed position, valve element blocks oil flow from the oil inlet into the sump chamber, while redirecting the oil flow into rejected oil return passage to reduce the loss of engine oil through the ATS in the event of an ATS housing breach.Type: GrantFiled: June 30, 2015Date of Patent: September 5, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Kellan Geck, Gerhard Schroeder, Doug Smith
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Patent number: 9745918Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a core nacelle defined about an engine centerline axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path. A variable area fan nozzle is in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section. The second fan nacelle section is axially movable relative to the first fan nacelle section to define an auxiliary port at a non-closed position to vary a fan nozzle exit area and adjust fan bypass airflow. The second fan nacelle section includes an acoustic system that has an acoustic impedance located on a radially outer surface.Type: GrantFiled: January 30, 2015Date of Patent: August 29, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan Gilson, Dennis Cicon, Oliver V. Atassi
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Patent number: 9739173Abstract: A casing for a fan drive gear system includes a cast body with an upper and a lower portion. The cast body defines an oil inlet and an oil outlet arranged below the oil outlet. An integrally cast oil channel extends between the inlet and outlet for conveying oil from the upper portion of the cast body portion to the lower portion of the cast body for providing a supply of lubrication to the gear system when oil pools in an upper portion of an auxiliary oil reservoir during negative-G flight events.Type: GrantFiled: September 29, 2014Date of Patent: August 22, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Christopher M. Valva, Todd M. Lapierre
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Patent number: 9739206Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.Type: GrantFiled: December 29, 2016Date of Patent: August 22, 2017Assignee: United Technologies CorporationInventors: David P. Houston, Daniel Bernard Kupratis, Frederick M. Schwarz
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Patent number: 9732960Abstract: A pigtail assembly of a fuel supply manifold assembly for a gas turbine engine, includes a first coupling assembly defined along a first axis; a second coupling assembly defined along a second axis, the second axis is parallel to the first axis; a first conduit between the first coupling assembly and the second coupling assembly; a third coupling assembly that defines a third axis, the third axis is non-parallel to the second axis; and a second conduit between the second coupling assembly and the third coupling assembly.Type: GrantFiled: February 19, 2015Date of Patent: August 15, 2017Assignee: United Technologies CorporationInventor: Kari L. Cutler
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Patent number: 9726042Abstract: A gas turbine duct casing, in particular for an aircraft engine, is disclosed. The duct casing has a first wall segment and a second wall segment which is connected to the first wall segment by a clamp arrangement. The clamp arrangement has at least one clamp and one bolt which passes through a hole in the clamp and is screwed to a nut on a side of the clamp facing away from the wall segments. The nut braces at least one first leg of the clamp against the first wall segment, in particular by an intermediate element, and braces at least one second leg of the clamp against the second wall segment. The bolt has a head which is guided in a form-fitting manner in a groove on the outside of the first wall segment facing away from the gas duct.Type: GrantFiled: March 4, 2015Date of Patent: August 8, 2017Assignee: MTU Aero Engines AGInventors: Stefan Sasse, Martin Metscher, Jan Haegert
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Patent number: 9719377Abstract: The invention relates to a method for operating a gas turbine power plant, including a gas turbine, a HRSG following the gas turbine, an exhaust gas blower, and a carbon dioxide separation plant which separates the carbon dioxide contained in the exhaust gases and discharges it to a carbon dioxide outlet, the gas turbine, HRSG, exhaust gas blower, and carbon dioxide separation plant being connected by means of exhaust gas lines. According to the method a trip of the gas turbine power plant includes the steps of: stopping the fuel supply, switching off the exhaust gas blower, and controlling the opening angle of a VIGV at a position bigger or equal to a position required to keep a pressure in the exhaust gas lines between the HRSG and the exhaust gas blower above a minimum required pressure. The invention relates, further relates to a gas turbine power plant configured to carry out such a method.Type: GrantFiled: July 28, 2014Date of Patent: August 1, 2017Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Richard Carroni, Jürgen Hoffmann
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Patent number: 9708983Abstract: The present disclosure refers to a method for operating a gas turbine with sequential combustors having a first-burner, a first combustion chamber, and a second combustor arranged sequentially in a fluid flow connection. To minimize emissions and combustion stability problems during transient changes when the fuel flow to a second combustor is initiated the method includes the steps of increasing the second fuel flow to a minimum flow, and reducing the first fuel flow to the first-burner of the same sequential combustor and/or the fuel flow to at least one other sequential combustor of the sequential combustor arrangement in order keep the total fuel mass flow to the gas turbine substantially constant. Besides the method a gas turbine with a fuel distribution system configured to carry out such a method is disclosed.Type: GrantFiled: September 30, 2014Date of Patent: July 18, 2017Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Adnan Eroglu, Juergen Hoffmann
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Patent number: 9696217Abstract: A phosphor thermometer is disclosed. The phosphor thermometer may comprise a light source configured to emit an excitation light, and an input waveguide configured to transmit at least a portion of the excitation light from the light source to a temperature sensing end. A phosphor may be located at the temperature sensing end and it may be configured to emit a fluorescence signal upon absorption of at least a portion of the excitation light transmitted by the input waveguide. The phosphor thermometer may further comprise an output waveguide configured to transmit at least a portion of the fluorescence signal from the phosphor to a detector. The detector may determine a fluorescence decay constant from the time dependent decay of the fluorescence signal, and the fluorescence decay constant may be correlated with a temperature.Type: GrantFiled: June 11, 2014Date of Patent: July 4, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Bruce Hockaday
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Patent number: 9695751Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.Type: GrantFiled: December 30, 2016Date of Patent: July 4, 2017Assignee: United Technologies CorporationInventors: Daniel Bernard Kupratis, Frederick M. Schwarz
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Patent number: 9689280Abstract: A gas turbine plant including a gas turbine and a compressor is provided with a steam turbine plant including a steam turbine and a condenser, and, an exhaust heat recovery boiler. Steam from the exhaust heat recovery boiler is directly flown to the condenser of the steam turbine plant through a bypass control valve. A pressure sensor detects pressure in a turbine bypass system. A controller outputs, based on a set value from an input device and a process value from the pressure sensor, an open level instruction value to the control value so as to make the process value consistent with the set value in a predetermined sampling cycle. A corrector corrects the set value from the input device in a direction in which the open level instruction value decreases when the open level instruction value from the controller becomes a value that substantially fully opens the control valve.Type: GrantFiled: July 17, 2014Date of Patent: June 27, 2017Assignee: Kabushiki Kaisha ToshibaInventors: Hironori Watanabe, Masayuki Tobo, Takuji Yamasaki, Firman Bagja Juangsa
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Patent number: 9689313Abstract: A turbomachine injection manifold assembly including a main circuit for feeding fuel to sets of injectors, and an auxiliary circuit for feeding fuel to a set of injectors. The manifold assembly also includes a double coupling presenting a first endpiece receiving one end of a transfer tube of the main circuit, a second endpiece receiving one end of a transfer tube of the auxiliary circuit, and a mounting surface with a first orifice in fluid flow communication with the first endpiece and a second orifice in fluid flow communication with the second endpiece, the mounting surface of the double coupling being suitable for connecting the double coupling to an injector of said first set of injectors.Type: GrantFiled: July 29, 2013Date of Patent: June 27, 2017Assignee: TURBOMECAInventors: Cedric Roger Zordan, Xavier Francez
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Patent number: 9677475Abstract: A gas turbine engine includes a turbine section that includes a turbine rotor arranged in a plenum. A compressor section includes a compressor rotor assembly that has spaced apart inner and outer portions that provide an axially extending cooling channel. Compressor blades extend radially outward from the outer portion which provides an inner core flow path. A rotor spoke is configured to receive a first cooling flow and fluidly connect the outer portion to the cooling channel. The compressor rotor assembly has a coolant exit that is in fluid communication with the cooling channel. The compressor rotor assembly is configured to communicate the first cooling flow to the turbine rotor. A bleed source is configured to provide a second cooling flow. A combustor section includes an injector in fluid communication with the bleed source. The tangential onboard injector is configured to communicate the second cooling flow to the turbine rotor.Type: GrantFiled: January 15, 2015Date of Patent: June 13, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Brian D. Merry, Gabriel L. Suciu
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Patent number: 9677503Abstract: The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.Type: GrantFiled: August 20, 2012Date of Patent: June 13, 2017Assignee: TGV ROCKETS, INC.Inventor: Patrick R. E. Bahn
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Patent number: 9670843Abstract: A system includes a catalyst system having at least one catalyst to treat an exhaust gas from a gas turbine system, and a thermal storage system having at least one storage tank to store thermal energy in a medium, wherein the system is configured to transfer heat from the medium to the at least one catalyst.Type: GrantFiled: November 25, 2013Date of Patent: June 6, 2017Assignee: General Electric CompanyInventors: Raymond Pang, Parag Prakash Kulkarni, Huijuan Chen
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Patent number: 9664390Abstract: The invention refers to burner arrangement for producing hot gases to be expanded in a gas turbine, including a burner inside a plenum, where the burner has means for fuel injection, means for air supply and means for generating an ignitable fuel/air mixture inside the burner, and a combustion chamber following downstream said burner having an outlet being fluidly connected to the gas turbine. The invention is characterized in that the means for air supply includes at least two separate flow passages, and that the one of the two flow passages is fed by a first supply pressure and the other flow passage is fed by a second supply pressure.Type: GrantFiled: July 8, 2013Date of Patent: May 30, 2017Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Stefano Bernero, Ennio Pasqualotto, Ewald Freitag