Patents Examined by Katheryn A Malatek
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Patent number: 11137141Abstract: A combustor includes a nozzle, a burner cylinder surrounding the outer circumference of the nozzle, and an outside flow path cylinder surrounding the outer circumference of a downstream end portion of the burner cylinder. A purge air flow path through which air flows is formed between the inner circumferential side of the outside flow path cylinder and the outer circumferential side of the burner cylinder. A tapered surface is formed in the downstream end portion of the burner cylinder such that the plate thickness of a burner cylinder-forming plate that forms the burner cylinder gradually thins toward the downstream side.Type: GrantFiled: September 1, 2015Date of Patent: October 5, 2021Assignee: MITSUBISHI POWER, LTD.Inventors: Kotaro Miyauchi, Koichi Nishida, Shinji Akamatsu, Keijiro Saito, Satoshi Takiguchi, Toshihiko Saito
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Patent number: 11136923Abstract: A device for regulating the fuel supply flow rate for a turbine engine, comprising at least a pump, an upstream line leading to the pump, a downstream line downstream of the pump, a recirculation duct branched off the downstream line, allowing to collect the fluid in the downstream line and channel it towards the upstream line, a means for regulating the flow rate disposed on the recirculation duct, a phase measurer disposed in the upstream line, a computing unit connected to the phase measurer and to the flow rate regulating means, said computing unit controlling the flow rate regulating means such as to control the degree of opening of said flow rate regulating means, according to the gas content value in the upstream line.Type: GrantFiled: December 16, 2019Date of Patent: October 5, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Abdallah Aounali, Petar Tomov
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Patent number: 11125159Abstract: The present disclosure provides systems and methods for power production. In particular, the systems and methods utilize the addition of heat to an expanded turbine exhaust stream in order to increase the available quantity of heat for recuperation and use therein for heating a compressed carbon dioxide stream for recycle back to a combustor of the power production system and method.Type: GrantFiled: August 27, 2018Date of Patent: September 21, 2021Assignee: 8 Rivers Capital, LLCInventor: Brock Alan Forrest
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Patent number: 11098678Abstract: A boundary layer ingestion engine includes a fan section configured to extend into a boundary layer of a full annulus of an aft end of a fuselage of an aircraft. The fan section includes a first fan stage and a second fan stage. The boundary layer ingestion engine also includes a differential planetary gear system is operable to transform rotation of an input shaft into counter rotation of a first shaft coupled to the first fan stage and a second shaft coupled to the second fan stage. The boundary layer ingestion engine further includes a motor operable to drive rotation of the input shaft.Type: GrantFiled: April 5, 2018Date of Patent: August 24, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Gabriel L. Suciu, Jesse M. Chandler
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Patent number: 11092085Abstract: A method for operating a gas turbine system includes utilizing a gas turbine controller to determine a schedule for a firing temperature for operative burners of a second combustor located downstream of a first combustor when the gas turbine system is operating in a low part load mode. During the low part load mode, multiple burners for the second combustor are switched-off. Further, the schedule is determined based on a position of inlet guide vanes of a compressor of the gas turbine system located upstream of both the first and second combustors. The method also includes controlling the firing temperature of the operative burners utilizing the schedule during the low part load mode to keep the gas turbine system within relevant operational limits of the gas turbine system.Type: GrantFiled: March 14, 2017Date of Patent: August 17, 2021Assignee: General Electric CompanyInventors: Martin Erwin Gassner, Paula Beneyto Satorres, Vincent Georges Christian Daniel Lonneux, Stefano Bernero, Dirk Therkorn, Sr.
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Patent number: 11085376Abstract: The invention concerns an assembly comprising: a fuel supply circuit (15, 15a, 15b) configured to supply fuel to a turbine heat engine, an electronic module (14, 14a, 14b), a power source (13, 13a, 13b) for supplying power to the electronic module (14, 14a, 14b), and a heat exchanger (16, 16a, 16b) positioned to allow a flow of heat from the electronic module (14, 14a, 14b) to the fuel supply circuit (15, 15a, 15b), the assembly being characterised in that the electronic module (14, 14a, 14b) comprises a phase-change material (PCM), configured to change state when the temperature of same reaches a predetermined phase-change temperature (Tf).Type: GrantFiled: June 12, 2017Date of Patent: August 10, 2021Assignee: SAFRAN HELICOPTER ENGINESInventors: Thomas Klonowski, Camel Serghine
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Patent number: 11073283Abstract: A turbulence generating structure for liner cooling enhancement is a liner cooling structure applied to a double-structured side portion formed by a liner and a flow sleeve and includes the liner and a first turbulence generator protruding from a surface space of the liner and including a plurality of ribs arranged in an axial direction, each of the ribs comprising blocks arranged at regular distances in the axial direction and interspaced by cooling holes. The ribs include a first set of adjacent ribs separated by a first passage distance, the first passage distance being repeated in a circumferential direction, and a second set of adjacent ribs separated by a second passage distance, the second passage distance being repeated in the circumferential direction, wherein the first and second sets of adjacent ribs have exactly one rib in common, and the first passage distance is greater than the second passage distance.Type: GrantFiled: August 27, 2018Date of Patent: July 27, 2021Inventors: Sung Wan Park, Jong Hwa Lee, In Chan Choi, Moon Soo Cho
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Patent number: 11073090Abstract: Systems and methods for adjusting airflow distortion in a gas turbine engine using a valved airflow passage assembly are provided. A gas turbine engine can include a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path. The compressor section can include a compressor. The gas turbine engine can further include a valved airflow passage assembly comprising a valve and a duct, the duct defining an inlet in airflow communication with the engine airflow path at a location downstream of the compressor and an outlet in airflow communication with the engine airflow path at a location upstream of the compressor, the duct comprising an airflow passage extending between the inlet and outlet. The valve can be operable with the airflow passage for controlling an airflow through the airflow passage to adjust airflow distortion.Type: GrantFiled: March 30, 2016Date of Patent: July 27, 2021Assignee: General Electric CompanyInventors: Brian Francis Nestico, Brian K. Kestner, Brandon Wayne Miller
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Patent number: 11060725Abstract: A gas turbine engine has a circumferential staging configuration of fuel injectors in a combustor. As a turbine blade revolves within the gas turbine engine it is subjected to lift and drag forces based on the configuration of lit injectors. A configuration of lit injectors that results in the minimum unsteady forces the turbine blade experiences is determined in order to increase the life span of the turbine blade and limit any structural failures.Type: GrantFiled: February 8, 2017Date of Patent: July 13, 2021Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventor: Marc Furi
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Patent number: 11053861Abstract: In accordance with one exemplary embodiment of the present disclosure, a method for providing overspeed protection for a gas turbine engine is provided. The gas turbine engine may include an engine core and an engine shaft. The method may include determining an overspeed condition of the engine. The overspeed condition may be indicative of an above normal rotational speed of the engine shaft. The method may also include reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.Type: GrantFiled: March 3, 2016Date of Patent: July 6, 2021Assignee: General Electric CompanyInventors: David Anthony Moster, William James Mailander, David Allen Gutz
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Patent number: 11053860Abstract: An accessory system for a gas turbine engine having a driveshaft with an axis of rotation is provided. The accessory system includes a towershaft coupled to the driveshaft and driven by the driveshaft along a towershaft axis of rotation. The accessory system also includes a shaft including a first shaft bevel gear coupled to a towershaft bevel gear. The shaft is rotatable by the towershaft along a shaft axis of rotation and defines an air-oil separator. The shaft axis of rotation is transverse to the towershaft axis of rotation. The accessory system includes a first accessory drive shaft having a first accessory bevel gear driven by the shaft. The accessory system also includes a second accessory drive shaft having a second accessory bevel gear driven by the shaft.Type: GrantFiled: April 21, 2020Date of Patent: July 6, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shawn Alstad, Tomasz Dobosz, Rocio Chavez
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Patent number: 11047308Abstract: An acoustic panel includes a base, a cantilevered portion, a gap, and a support member. The base has a surface defining a plurality of cavities configured to attenuate noise from an engine. The cantilevered portion extends from the base and is configured to be removably coupled with a portion of a transcowl. The gap is defined by the base and the cantilevered portion. The support member is coupled to the cantilevered portion and the base, and the supporting member is configured to support the cantilevered portion.Type: GrantFiled: June 29, 2018Date of Patent: June 29, 2021Assignee: THE BOEING COMPANYInventors: Alexandre D. Curaudeau, Brian L. Riedel, Taurus L. Brackett, II
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Patent number: 11047262Abstract: A propulsion system for an aircraft. The propulsion system comprises a core, an internal fixed structure secured to the core and arranged around the core, and a nacelle surrounding the core and the internal fixed structure in which a secondary flow path is delimited between the internal fixed structure and the nacelle. The internal fixed structure has a slot which permits fluidic communication between a compartment on the inside of the internal fixed structure and the secondary flow path.Type: GrantFiled: May 29, 2019Date of Patent: June 29, 2021Assignee: AIRBUS OPERATIONS SASInventors: Thierry Gaches, Lionel Czapla, Bastian Sabathier
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Patent number: 11047309Abstract: Herein provided are methods and systems for detecting an abnormal engine start of a gas turbine engine. An inter-turbine temperature of the engine is measured during engine start. The inter-turbine temperature is compared to an inter-turbine temperature threshold which depends on at least one additional parameter. An abnormal engine start is detected when the inter-turbine temperature exceeds the threshold. The at least one additional parameter may comprise engine rotational speed. The at least one additional parameter may comprise time.Type: GrantFiled: July 26, 2017Date of Patent: June 29, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Andrzej Fiedler, Michael Krynski
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Patent number: 11047336Abstract: A gas turbine engine that includes a nozzle assembly that has features that facilitate airflow into and through a bypass passage of the gas turbine engine during a reverse thrust operation is provided. The nozzle assembly of the gas turbine engine also includes features that increase the effectiveness of the thrust reverse system of the gas turbine engine. Methods for reversing the thrust of a gas turbine engine are also provided.Type: GrantFiled: February 20, 2019Date of Patent: June 29, 2021Assignee: GENERAL ELECTRIC COMPANYInventor: Tomasz Iglewski
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Patent number: 11046449Abstract: A gas inerting system for an aircraft includes a fuel tank configured to contain a liquid fuel, a fuel vaporization system in fluid communication with the fuel tank and configured to receive the liquid fuel from the fuel tank, a source of air in fluid communication with the fuel vaporization system and configured to deliver air into the liquid fuel to produce the fuel vapor, a heat exchanger in fluid communication with the source of air at a location upstream of the fuel vaporization system, and a catalytic oxidation unit in fluid communication with the fuel vaporization system. The heat exchanger is configured to cool the air from the air source. A fluid connection is configured to deliver the fuel vapor to the catalytic oxidation unit.Type: GrantFiled: March 29, 2018Date of Patent: June 29, 2021Assignee: Hamilton Sundstrand CorporationInventor: Eric Surawski
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Patent number: 11047306Abstract: A turbine engine includes: a core cowl, a core within the core cowl, the core including a compressor having a bleed port; an undercowl space; a cooling duct at least partially in the undercowl space and having an inlet and an outlet, the inlet communicating with a source of cooling air, the outlet communicating with the compressor bleed port; a valve assembly in the cooling duct; and a cooling blower operable to move air flow from the inlet of the cooling duct towards the outlet of the cooling duct and into the compressor bleed port. A method of cooling an engine having a core cowl and a compressor, combustor and turbine includes: operating the engine; shutting the engine down; after or during engine shutdown, operating a cooling blower internal to the engine cowl, to force air through the compressor by way of a compressor bleed port.Type: GrantFiled: February 25, 2020Date of Patent: June 29, 2021Assignee: General Electric CompanyInventors: Michael R. Millhaem, Byron Andrew Pritchard, Hendrik Pieter Jacobus de Bock, John Carl Glessner, Jeffrey Scott Ksander, Craig A. Gonyou, Christopher Jon Potokar
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Patent number: 11047574Abstract: A combustor assembly for a gas turbine engine defining a radial direction and a circumferential direction includes a liner assembly at least partially defining a combustion chamber and including at least one liner formed of a ceramic matrix composite material and extending between a downstream end and an upstream end, the downstream end of the at least one liner defining an interface surface extending along the circumferential direction; and a seal member also formed of a ceramic matrix composite material and bonded to the interface surface of the at least one liner, the seal member defining a downstream surface for contacting an adjacent component to form a seal with the adjacent component.Type: GrantFiled: December 5, 2018Date of Patent: June 29, 2021Assignee: General Electric CompanyInventors: Ernesto Andres Vallejo Ruiz, Douglas Craig Anderson
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Patent number: 11041626Abstract: A combustion chamber system has pilot and main fuel manifolds, and pilot and main fuel nozzles. Each pilot nozzle is connected to the pilot manifold. Each main nozzle is connected to the main manifold. A greater total amount of fuel is supplied to the pilot nozzles than to the main nozzles. A greater amount of fuel is supplied to pilot nozzles at, or in, a first region of the combustion chamber than to pilot fuel nozzles at, or in, a second region. A greater amount of fuel is supplied to the main nozzles at, or in, the first region than to the main nozzles at, or in, the second to improve combustion efficiency, weak extinction and relight of the combustion chamber in a first mode of operation. A greater total amount of fuel is supplied to the main nozzles than to the pilot nozzles in a second mode of operation.Type: GrantFiled: March 13, 2017Date of Patent: June 22, 2021Assignee: ROLLS-ROYCE plcInventors: Hua Wei Huang, Jochen Rupp, Michael Whiteman
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Patent number: 11041445Abstract: A valve assembly includes a body including an inlet port, an outlet port, and a flow passage extending therebetween. The flow passage includes a plurality of valve seats in a stepped arrangement between the inlet port and the outlet port. The valve assembly further includes a valve stem positioned within the flow passage. The valve stem includes at least one shaft and a poppet disk positioned at one end of the at least one shaft, and at least one reed petal coupled to the at least one shaft. The poppet disk is engageable with a first valve seat of the plurality of valve seats, and the at least one reed petal is engageable with a second valve seat of the plurality of valve seats.Type: GrantFiled: February 12, 2019Date of Patent: June 22, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: John Michael Cadman, David Richard Barnhart