Patents Examined by Katheryn Malatek
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Patent number: 11002188Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes an inlet lip for a nacelle inlet structure, a bulkhead and a nozzle. The bulkhead is configured with the inlet lip to form a cavity between the inlet lip and the bulkhead. The nozzle includes a distribution conduit and one or more nozzle ports. The distribution conduit projects longitudinally out from the bulkhead and into the cavity along a conduit centerline. At least a first portion of the distribution conduit tapers as the distribution conduit extends longitudinally along the conduit centerline. The first portion of the distribution conduit has an elongated geometry in a plane perpendicular to the conduit centerline. The one or more nozzle ports are arranged longitudinally along the conduit centerline and fluidly coupled with an internal passage of the distribution conduit.Type: GrantFiled: September 14, 2018Date of Patent: May 11, 2021Assignee: Rohr, Inc.Inventor: Radhakrishna Chilukuri
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Patent number: 10995679Abstract: A flame produced within a premixer is promptly extinguished and a reduction in output power of a gas turbine associated with extinguishment is suppressed.Type: GrantFiled: January 31, 2019Date of Patent: May 4, 2021Assignee: Mitsubishi, Power, Ltd.Inventors: Kazuki Abe, Akinori Hayashi, Yasuhiro Wada, Tetsuma Tatsumi, Shohei Yoshida
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Patent number: 10989408Abstract: A component for a gas turbine engine is disclosed. In various embodiments, the component includes a diffuser ring, a combustor and a spring element connecting the diffuser ring to the combustor.Type: GrantFiled: September 13, 2018Date of Patent: April 27, 2021Assignee: Raytheon Technologies CorporationInventors: Lawrence Binek, Evan Butcher, Matthew B. Kennedy, Vijay Narayan Jagdale, Jesse R. Boyer, Dmytro Mykolayovych Voytovych
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Patent number: 10989411Abstract: A turbo machine including a heat exchanger flowpath is generally provided. The turbo machine includes an outer casing extended along an axial direction, a prediffuser defining an inlet passage into a combustion section of the turbo machine, an inner casing extended from the prediffuser, in which a diffuser cavity is defined between the outer casing and the inner casing, a first plenum wall extended outward along a radial direction from the prediffuser, and a second plenum wall extended outward along a radial direction from the prediffuser. The second plenum wall is separated along the axial direction from the first plenum wall. A plenum is defined between the first plenum wall and the second plenum wall. The turbo machine includes a heat exchanger including a first conduit in fluid communication with the diffuser cavity. The first conduit is in fluid communication with a passage, and a second conduit in fluid communication with the passage and the plenum.Type: GrantFiled: January 3, 2019Date of Patent: April 27, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Karthikeyan Sampath, Varun Swaminathan Lakshmanan, Michael Anthony Benjamin, Veeraraju Vanapalli
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Patent number: 10982852Abstract: A combustion section of a gas turbine engine may include a cassette configured to couple to an annular combustor dome arranged around a flow path for the gas turbine engine. The annular combustor dome may include a dome wall comprising a plurality of inlets configured to receive compressed air for a combustion chamber located downstream, relative to the flow path, from the annular combustor dome. The cassette may include a combustor wall extended away from the dome wall in a downstream direction. The cassette may further include a cowl integral to the combustor wall. At least a portion of the cowl may extend away from the dome wall in an upstream direction relative to the flow path. The cowl may receive compressed air from a diffusor and guide the compressed air to a space upstream from the inlets, relative to the flow path.Type: GrantFiled: November 5, 2018Date of Patent: April 20, 2021Assignee: Rolls-Royce CorporationInventors: Kevin Sauer, Lewis Dailey, Keith McCormick
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Patent number: 10982856Abstract: A fuel nozzle for injecting fuel and air into a combustor of a gas turbine engine, the fuel nozzle comprising: an outer component having an outward surface adapted for exposure to a flow of hot gas within the combustor, and an inward surface; an inner component concentrically disposed within the inward surface of outer component along a nozzle axis, the inner component defining an axially extending air flow channel; an air passage bore extending through the outward surface of the outer component and communicating with the air flow channel; and a thermal insulating sleeve disposed within the air passage bore, the sleeve having a sleeve body spaced apart from the outer component by an air gap.Type: GrantFiled: February 1, 2019Date of Patent: April 20, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Saeid Oskooei, Gavin Rohiteswar Kisun, Nadia Cheri Swaby, Roger Neil Antony Francis
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Patent number: 10975774Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor, a compressor wash system in communication with the compressor, a condensate or boiler feed water system in communication with the compressor, and a dosing system in communication with the condensate or boiler feed water system.Type: GrantFiled: December 16, 2014Date of Patent: April 13, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Alston Ilford Scipio, Paul Robert Fernandez, Rebecca Evelyn Hefner, Sanji Ekanayake
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Patent number: 10941706Abstract: An aeronautical gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. The aeronautical gas turbine engine additionally includes a closed cycle heat engine including a compressor configured to compress a working fluid; a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid; an expander coupled to the compressor for expanding the working fluid; and an output shaft driven by the expander.Type: GrantFiled: February 13, 2018Date of Patent: March 9, 2021Assignee: General Electric CompanyInventors: Arnab Sen, Brandon Wayne Miller, Bhaskar Nanda Mondal, Kishanjit Pal, Daniel Alan Niergarth
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Patent number: 10928069Abstract: The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine by one or more fastening elements that are integrally formed with the annular ring. The fastening elements are mountable with corresponding features of the support element and removably fastened thereto.Type: GrantFiled: June 17, 2016Date of Patent: February 23, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Honza Stastny, Robert Sze
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Patent number: 10920713Abstract: A compression inner core cowl for a jet engine can have a concave annular section of the core cowl. The concave section can begin within the expanse of an outer fan cowl and extend aft of the fan cowl toward the tail cone, defining an annular bypass section between the fan cowling and the core cowling. The concave geometry of the core cowling reduces the strength of supersonic shock waves generated at the corners of the cowlings adjacent a supersonic airflow stream to increase overall efficiency of the engine.Type: GrantFiled: November 23, 2016Date of Patent: February 16, 2021Assignee: General Electric CompanyInventor: Tomasz Iglewski
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Patent number: 10907549Abstract: The invention concerns a method for a part load CO reduction operation and a low-CO emissions operation of a gas turbine with sequential combustion. The gas turbine essentially includes at least one compressor, a first combustor which is connected downstream to the compressor. The hot gases of the first combustor are admitted at least to an intermediate turbine or directly or indirectly to a second combustor. The hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery. At least one combustor runs under a caloric combustion path having a can-architecture, and wherein the air ratio (?) of the combustion at least of the second combustor is kept below a maximum air ratio (?max).Type: GrantFiled: December 19, 2014Date of Patent: February 2, 2021Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Michael Düsing, Adnan Eroglu
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Patent number: 10907833Abstract: A combustor for a gas turbine engine comprises a combustion chamber having a pilot injector at one end and at least one main injector spaced radially from the pilot injector. The main injector includes a fluid flow path with a plug that restricts flow at least at an interior portion of the flow path. A gas turbine engine is also disclosed.Type: GrantFiled: January 5, 2015Date of Patent: February 2, 2021Assignee: Raytheon Technologies CorporationInventors: Zhongtao Dai, Adam Takashi Holley, Randal G. McKinney
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Patent number: 10900419Abstract: 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. 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. A first accessory axis of rotation and a second accessory axis of rotation are substantially transverse to the shaft axis of rotation.Type: GrantFiled: August 7, 2018Date of Patent: January 26, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shawn Alstad, Tomasz Dobosz, Rocio Chavez
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Patent number: 10876731Abstract: A swirler for mixing fuel with air in a combustion engine includes a central axis, a swirler base with an upper surface, a central portion, a number of main swirler elements and a number of obstruction elements. The main swirler elements and the obstruction elements are located at the upper surface of the swirler base and are arranged around the central portion. The main swirler elements form a number of swirler slots configured for directing a fluid towards the central portion. Each swirler slot has a slot inlet and a slot outlet, wherein the slot outlet is located at a smaller radial distance from the central axis than the swirler inlet. Each obstruction element is located at a slot inlet and configured for forming a plurality of flow channels into the swirler slot.Type: GrantFiled: April 21, 2017Date of Patent: December 29, 2020Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Timothy Dolmansley, James Hird
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Patent number: 10865658Abstract: In a gas turbine exhaust member and an exhaust chamber maintenance method, the gas turbine exhaust member is provided with: an inside diffuser that forms a tubular shape and is divided into multiple parts in the circumferential direction; a first seal housing that forms a tubular shape and is integrally formed in the circumferential direction, the front end of which being coupled to the rear end of the inside diffuser; a second seal housing that forms a tubular shape and is integrally formed in the circumferential direction, the front end of which being coupled to the rear end of the first seal housing; and a supporting coupling part that supports the rear end of the first seal housing and the front end of the second seal housing so as to allow the rear end and the front end to move in the axial direction.Type: GrantFiled: July 3, 2015Date of Patent: December 15, 2020Assignee: MITSUBISHI POWER, LTD.Inventor: Shinya Hashimoto
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Patent number: 10865988Abstract: A plate for supporting a plurality of nozzle tubes in a combustion casing of a combustor stably supports the nozzle tubes and adsorbs displacement due to thermal expansion or natural vibrations, thereby reducing combustor maintenance and extending the lifetime of the combustor. The plate includes an inner frame having a plurality of through holes for respectively receiving the plurality of nozzle tubes; a fixing frame fixed on an inner circumferential surface of the combustion casing and configured to support the inner frame; and a mechanical buffer disposed between the fixing frame and the inner frame. The fixing frame has an inner circumferential surface in which a fixing recess having a U-shaped cross-section is formed to receive the mechanical buffer and an outer edge of the inner frame and to receive the mechanical buffer. A method of assembly the nozzle tube support plate facilitates its initial installation and subsequent maintenance.Type: GrantFiled: August 23, 2018Date of Patent: December 15, 2020Assignee: Doosan Heavy Industries Construction Co., LtdInventors: Byeong Ha Jeon, Moon Soo Cho
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Patent number: 10851998Abstract: A combustor includes: a first nozzle which extends along an axis and injects fuel toward a downstream side; a flame stabilizer which covers a downstream-side end portion of the first nozzle from an outer periphery side; and a plurality of second nozzles arranged at intervals in a circumferential direction around the axis on the outer periphery side of the flame stabilizer. The flame stabilizer has a cone portion expanding in diameter toward the downstream side from the upstream side, and a flange portion extending radially outward from a downstream-side end edge of the cone portion, and a penetrating portion which penetrates at least the flange portion in a direction of the axis is formed in the flame stabilizer.Type: GrantFiled: March 28, 2017Date of Patent: December 1, 2020Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Kenji Miyamoto, Satoshi Takiguchi, Keijiro Saito, Shinji Akamatsu, Shinichi Fukuba
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Patent number: 10837637Abstract: A heat shield provided with a gas turbine engine includes a heat shield body extending between a first heat shield end and a second heat shield end. The heat shield body has an exterior surface disposed proximate an inner surface of a first case and an interior surface disposed opposite the exterior surface. The interior surface defines a rib that extends towards a combustor vane support lock.Type: GrantFiled: March 22, 2016Date of Patent: November 17, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: David J. Sander, Jonathan Lemoine, Harvey C. Lee, Dalton C. Petrillo
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Patent number: 10830051Abstract: An engine component can comprise a cooled surface adjacent to a cooling flow and a hot surface adjacent to a hot flow of fluid. The component can comprise a wall separating the hot and cooling flows, defining the cooled surface and the hot surface, and having a plurality of film holes disposed in the wall. At least one turbulator and at least one film hole inlet can be disposed on the cooled surface. The turbulator and the inlet can be arranged to provide a steady flow of cooling fluid to the film hole. One arrangement can comprise spacing the film hole inlet at least two turbulator heights from the turbulator.Type: GrantFiled: December 11, 2015Date of Patent: November 10, 2020Assignee: General Electric CompanyInventor: Ronald Scott Bunker
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Patent number: 10816206Abstract: A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and a second major inner air passage. A combustor for a turbine engine includes an outer liner panel with a multiple of outer dilution passages. The multiple of outer dilution passages includes a repeating pattern of a first major outer air passage, a first minor outer air passage, a second major outer air passage, and a second minor outer air passage.Type: GrantFiled: October 20, 2014Date of Patent: October 27, 2020Assignee: Raytheon Technologies CorporationInventors: Dennis M. Moura, III, Reza Rezvani