Patents Examined by Steven Sutherland
  • Patent number: 10371064
    Abstract: A method of operating a gas turbine engine includes measuring an exhaust gas temperature of the gas turbine engine. A first stage turbine nozzle assembly of the gas turbine engine is adjusted to a first position. A firing temperature of the gas turbine engine is determined based on the exhaust gas temperature. The firing temperature is compared to a threshold value and a difference value is determined therefrom. If the difference value exceeds a threshold value, the first stage turbine nozzle assembly is adjusted to a second position such that the firing temperature is substantially equal to the threshold value.
    Type: Grant
    Filed: February 11, 2016
    Date of Patent: August 6, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Narendra Digamber Joshi, Krishan Lal Luthra
  • Patent number: 10309341
    Abstract: Systems and methods are provided for a formed thrust reverser cascade. The formed thrust reverser cascade may be coupled to an aircraft propulsor and may include a first portion disposed at a first angle to a portion of the aircraft propulsor and a second portion disposed at a second angle to the first portion. The formed thrust reverser cascade may be circumferentially disposed around a core engine of the aircraft propulsor. The formed thrust reverser cascades may be retrofitted to aircraft propulsors using linear thrust reverser cascade and may increase airflow through the formed thrust reverser cascade due to a greater throat area as compared to the linear thrust reverser cascade. Alternatively, the formed thrust reverser cascades may allow for shorter cascades while retaining the same performance, thus resulting in shorter nacelles.
    Type: Grant
    Filed: January 15, 2016
    Date of Patent: June 4, 2019
    Assignee: The Boeing Company
    Inventors: Naimishkumar B. Harpal, Chen Chuck
  • Patent number: 10288010
    Abstract: 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: Grant
    Filed: January 13, 2017
    Date of Patent: May 14, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David P. Houston, Daniel Bernard Kupratis, Frederick M. Schwarz
  • Patent number: 10288011
    Abstract: 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: Grant
    Filed: April 17, 2017
    Date of Patent: May 14, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David P. Houston, Daniel Bernard Kupratis, Frederick M. Schwarz
  • Patent number: 10287914
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
    Type: Grant
    Filed: April 4, 2017
    Date of Patent: May 14, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu, William K. Ackermann, Daniel Bernard Kupratis, Michael E. McCune
  • Patent number: 10280843
    Abstract: A gas turbine engine includes a fan section including a fan hub. A speed reduction device includes a star gear system. A turbine section is connected to the fan section through the speed reduction device. A first fan bearing for supporting rotation of the fan hub is connected forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is connected aft of the speed reduction device. A first outer race of the first fan bearing is attached to the fan hub.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: May 7, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: William G. Sheridan
  • Patent number: 10267525
    Abstract: A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: April 23, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Douglas Anthony Pennell, Urs Benz, Adnan Eroglu, Ewald Freitag, Mirko Ruben Bothien, Andrea Ciani
  • Patent number: 10260420
    Abstract: According to the present disclosure, a gas turbine assembly includes a gas turbine engine and a gearbox. The gearbox includes a lubrication system including a first sump and a second sump. The lubrication system is configurable to use either of the first and second sumps to correspond to various configurations of the gas turbine assembly.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: April 16, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: John W. Ross, Christine E. Carter, John Yamashita
  • Patent number: 10260751
    Abstract: A combustor for a gas turbine engine comprises a single skin liner defining a combustion chamber. The single skin liner has an inner surface facing the combustion chamber and an outer surface exposed to a coolant flow discharged in a plenum extending from the outer surface of the single skin liner to the engine casing. Cooling holes extend through the single skin liner. Cooling protuberances, such as fins or pin fins, project integrally from the outer surface of the single skin liner into the plenum, the cooling fins being interspersed between the cooling holes.
    Type: Grant
    Filed: September 28, 2015
    Date of Patent: April 16, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tin-Cheung John Hu, Si-Man Amy Lao, Sri Sreekanth, Michael Papple
  • Patent number: 10260415
    Abstract: A power generation system includes an inert gas power source, a thermal/electrical power converter and a power plant. The thermal/electrical power converter includes a compressor with an output coupled to an input of the inert gas power source. The power plant has an input coupled in series with an output of the thermal/electrical power converter. The thermal/electrical power converter and the power plant are configured to serially convert thermal power produced at an output of the inert gas power source into electricity. The thermal/electrical power converter includes an inert gas reservoir tank coupled to an input of the compressor via a reservoir tank control valve and to the output of the compressor via another reservoir tank control valve. The reservoir tank control valve and the another reservoir tank control valve are configured to regulate a temperature of the output of the thermal/electrical power converter.
    Type: Grant
    Filed: August 1, 2016
    Date of Patent: April 16, 2019
    Assignee: Hi Eff Utility Rescue LLC
    Inventors: William Edward Simpkin, Donald R. Wilson
  • Patent number: 10260371
    Abstract: A method for providing an anti-icing airflow, including extracting a compressed airflow from a core flow path of an engine, heating the compressed airflow, mixing the heated compressed airflow with air extracted from a bypass flow path to create the anti-icing airflow having a higher temperature and pressure than that of the air extracted from the bypass flow path, and circulating the anti-icing airflow away from the bypass flow path. Also, an assembly located at least in part inside a turbofan engine and including a heat exchanger, a flow mixing device having a first inlet in the bypass flow path, a second inlet and an outlet, a first conduit providing fluid communication between the heat exchanger and a compressed air portion of the core flow path, a second conduit providing fluid communication between the heat exchanger and the second inlet, and a third conduit in fluid communication with the outlet.
    Type: Grant
    Filed: May 20, 2016
    Date of Patent: April 16, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Nashed Youssef, Andreas Eleftheriou, Daniel Alecu
  • Patent number: 10253696
    Abstract: An air-to-air cooler has a heat exchanger integrated to a housing. A first passage extends through the housing for directing a flow of cooling air through the heat exchanger. A second passage extends through the housing for directing a flow of hot air to be cooled through the heat exchanger. The first passage has a cooling air outlet tube disposed downstream of the heat exchanger. The cooling air outlet tube extends across the second passage between the heat exchanger and a hot air inlet of the second passage. The hot air inlet is disposed to cause incoming hot air to flow over the cooling air outlet tube upstream of the heat exchanger. An ejector drives the flow of cooling air through the first passage of the air-to-air cooler. A portion of the hot air flow may be used to drive the ejector.
    Type: Grant
    Filed: September 7, 2016
    Date of Patent: April 9, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Daniel Alecu, Richard Kostka
  • Patent number: 10253690
    Abstract: A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.
    Type: Grant
    Filed: February 3, 2016
    Date of Patent: April 9, 2019
    Assignees: General Electric Company, ExxonMobil Upstream Research Company
    Inventors: Jonathan Kay Allen, Bradford David Borchert, Jesse Edwin Trout, Ilya Aleksandrovich Slobodyanskiy, Almaz Valeev, Igor Petrovich Sidko, Andrey Pavlovich Subbota
  • Patent number: 10247030
    Abstract: Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine.
    Type: Grant
    Filed: September 2, 2015
    Date of Patent: April 2, 2019
    Assignees: MITSUBISHI HEAVY INDUSTRIES, LTD., TOHOKU ELECTRIC POWER COMPANY, INC.
    Inventors: Satoshi Mizukami, Tatsuo Ishiguro, Junichiro Masada, Kazumasa Takata, Yuya Fukunaga, Hiroki Takahashi, Masaki Satoh, Yoshiaki Nishimura, Norio Oogai, Souji Hasegawa, Masato Hayashi
  • Patent number: 10247097
    Abstract: A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.
    Type: Grant
    Filed: June 20, 2013
    Date of Patent: April 2, 2019
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler
  • Patent number: 10240533
    Abstract: A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: March 26, 2019
    Assignee: United Technologies Corporation
    Inventors: James B. Hoke, Timothy S. Snyder, David Kwoka, Robert M. Sonntag
  • Patent number: 10240526
    Abstract: A compressor section is in fluid communication with a fan, which includes a first compressor section and a second compressor section. A turbine section includes a first turbine section driving the fan and the first compressor section and a second turbine section driving the second compressor section and the second compressor rotor. A first performance quantity is defined as a product of the first speed squared and the first area. A second performance quantity is defined as a product of the second speed squared and the second exit area. A performance ratio of the first performance quantity to the second performance quantity is between about 0.2 and about 0.8. A gear reduction is included between the first turbine section and the first compressor section.
    Type: Grant
    Filed: August 22, 2017
    Date of Patent: March 26, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Frederick M. Schwarz, William K. Ackermann, Daniel Bernard Kupratis
  • Patent number: 10240534
    Abstract: A fuel supply manifold of a gas turbine engine, a method for assembling a fuel supply manifold for a gas turbine engine, and a gas turbine engine are disclosed. The fuel supply manifold for the gas turbine engine man include a plurality of fuel supply tubes, a fitting connecting at least two members of the plurality of fuel supply tubes, a bracket attached to the fitting, a bearing housing having a ball bearing, a bushing attached to a diffuser case of the gas turbine engine, wherein the bushing is surrounded by the ball bearing, and a removable fastener to connect the bearing housing to the bracket.
    Type: Grant
    Filed: May 23, 2014
    Date of Patent: March 26, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Robert F. Sheil, Thomas Bruce Avis, Peter Tu
  • Patent number: 10240529
    Abstract: An example gas turbine engine includes a turbine and first and second spools coaxial with one another. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool and supports the turbine. A housing is arranged downstream from the turbine. First and second bearings are mounted to the aft end of the first spool and supported by the housing portion.
    Type: Grant
    Filed: September 23, 2016
    Date of Patent: March 26, 2019
    Assignee: United Technologies Corporation
    Inventor: Gregory M. Savela
  • Patent number: 10240484
    Abstract: A gas accumulation detection and ventilation system for a gas turbine enclosure includes a pipe array positioned adjacent a floor of the gas turbine enclosure and a ventilation assembly including a fan, an air flow inlet and an air flow outlet. The pipe array includes at least one pipe having at least one opening therein. The fan of the ventilation assembly directs an air flow sweep through the air flow inlet along the floor of the gas turbine enclosure. A hazardous gas sensor panel in communication with the pipe array and the ventilation assembly detects an accumulation level of turbine fuel gas in the gas turbine enclosure based on input from the pipe array and activates the ventilation assembly according to the detected accumulation level.
    Type: Grant
    Filed: November 6, 2015
    Date of Patent: March 26, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Hua Zhang, Manuel Moises Cardenas, Jr.