Patents Examined by William H. Rodriguez
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Patent number: 12264820Abstract: A multi-stage micro-decomposition swirl burner with an ammonia-doped fuel, and a low NOx control method are provided. A natural gas central pipe, a primary air pipe and a burner housing are nested from inside to outside in sequence to form a primary air duct and an over-fire air channel which are isolated from each other. Natural gas is ejected from the natural gas central pipe, and swirl vanes are arranged in the primary air duct, such that the primary air can be mixed with the central natural gas in a swirl state, and then a diffusion flame is formed under the action of an ignition device. Therefore, a pilot flame with sustainable combustion is formed at the center of an injection end of the burner.Type: GrantFiled: September 24, 2024Date of Patent: April 1, 2025Assignee: Tsinghua UniversityInventors: Shuiqing Li, Tong Si, Peng Ma, Yuanping Yang, Xiang Wang
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Patent number: 12264621Abstract: The present disclosure relates to a gas turbine plant which decomposes ammonia into a decomposition gas including hydrogen and supplies the decomposition gas as fuel to a combustor of the gas turbine. The gas turbine plant supplies sufficient heat to the ammonia in order to thermally decompose the ammonia effectively and separates the residual ammonia present in the decomposition gas and supplies the decomposition gas to a combustor of the gas turbine.Type: GrantFiled: May 15, 2024Date of Patent: April 1, 2025Assignee: Doosan Enerbility Co., Ltd.Inventors: Byoung Gu Bak, Tae Woo Kim, Hong Geun Ha
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Patent number: 12241408Abstract: This performance evaluation device comprises: an acquisition unit which acquires a sampling value of a gas turbine output and a sampling value of a steam turbine output, measured at each time during the operation of a combined cycle power generation plant that generates power using the gas turbine and the steam turbine; and an output calculation unit which obtains a plant output that is a total output of the sampling value of the gas turbine output measured at a first time and the sampling value of the steam turbine that is the steam turbine output corresponding to the gas turbine output at the first time and is measured at a second time after a predetermined delay from the first time.Type: GrantFiled: September 13, 2021Date of Patent: March 4, 2025Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Yosuke Fujitomi, Takashi Ichimaru, Satoru Mori, Toshihiko Niinomi
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Patent number: 12241628Abstract: A swirler assembly for a combustor includes at least one swirler including a plurality of swirl vanes arrayed about an axis of the swirler. The plurality of swirl vanes includes a first ring of first sub-vanes and a second ring of second sub-vanes, the first ring of first sub-vanes and the second ring of second sub-vanes being separated by a gap therebetween.Type: GrantFiled: September 1, 2023Date of Patent: March 4, 2025Assignee: GENERAL ELECTRIC COMPANYInventors: Gurunath Gandikota, Karthikeyan Sampath, Perumallu Vukanti, Allen M. Danis, Scott M. Bush, Steven Clayton Vise, Hari Ravi Chandra, Rimple Rangrej, Saket Singh, Pradeep Naik, Neeraj Kumar Mishra, Arvind Kumar Rao, Balasubramaniam Venkatanarayanan, Ranjeet Kumar Mishra
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Patent number: 12234990Abstract: A combustion device includes: an ammonia tank; a combustor connected to the ammonia tank; an air supply source; and an ammonia autothermal cracking device having inlets connected to the ammonia tank and the air supply source and an outlet connected to the combustor.Type: GrantFiled: October 3, 2023Date of Patent: February 25, 2025Assignee: IHI CorporationInventors: Shintaro Ito, Masahiro Uchida
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Patent number: 12234989Abstract: The present disclosure provides a central staged combustion chamber with self-excited sweeping oscillating fuel injection nozzles, including an outer housing with a cavity inside, a main stage coaxially disposed with the outer housing, and a pilot stage coaxially disposed with the outer housing. An annular fuel passage is used for connecting a plurality of self-excited sweeping oscillating fuel injection nozzles, and the self-excited sweeping oscillating fuel injection nozzles are suitable for injecting oscillating liquid fuel into a primary swirling passage. The fuel is output in a fan shape through each of the self-excited sweeping oscillating fuel injection nozzles and is dispersed by an incoming flow through the swirling passage, so that the atomization performance and spatial distribution uniformity of the fuel can be greatly improved.Type: GrantFiled: December 15, 2023Date of Patent: February 25, 2025Assignee: AERO ENGINE ACADEMY OF CHINAInventors: Shiqi Wang, Quan Wen, Xiao Han, Qian Yang
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Patent number: 12234988Abstract: A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage and a liquid swirler concentrically disposed about the inflow tube, the liquid swirler including a liquid swirler inner wall having a liquid swirler inner wall end portion angled radially outward from the nozzle axis, a liquid swirler outer wall having a liquid swirler outer wall end portion angled radially outward from the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall having an RAS inner wall end portion angled radially inward toward the nozzle axis, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween.Type: GrantFiled: April 4, 2024Date of Patent: February 25, 2025Assignee: RTX CorporationInventors: Zhongtao Dai, Justin M. Locke
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Patent number: 12228072Abstract: A system includes a gas turbine having a turbine stage disposed in a combustion gas path, wherein the turbine stage includes turbine vanes disposed upstream from turbine blades. The system includes an isothermal expansion system coupled to the turbine stage. The isothermal expansion system includes multi-fluid injectors configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion, wherein at least one of the multi-fluid injectors is coupled to each of the turbine vanes. Each of the multi-fluid injectors includes a fuel port configured to inject a fuel, an oxidant port configured to inject an oxidant, and a barrier fluid port configured to inject a barrier fluid between the fuel and the oxidant, wherein the barrier fluid is configured to delay mixing between the fuel and the oxidant.Type: GrantFiled: February 5, 2024Date of Patent: February 18, 2025Assignee: GE Infrastructure Technology LLCInventors: John Farrior Woodall, Joel Meador Hall
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Patent number: 12228283Abstract: A fuel swirl nozzle for a gas turbine engine comprises, in axial fuel flow sequence, a fuel inlet portion, a fuel stem portion, and a fuel/air swirler portion. The fuel inlet portion is configured to receive a flow of a fuel, with an inlet to the fuel stem portion being fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion being fluidly sealed against the fuel/air swirler portion. The fuel/air swirler portion comprises an outer air swirler and an inner air swirler, with the inner air swirler being positioned concentrically within the outer air swirler. The outer air swirler comprises a plurality of first vanes that are arranged in an annular array within an outer air swirler body and is configured to impose a first rotational flow component on an air flow entering the outer air swirler.Type: GrantFiled: May 1, 2024Date of Patent: February 18, 2025Assignee: ROLLS-ROYCE PLCInventor: Frederic Witham
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Patent number: 12228282Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.Type: GrantFiled: January 10, 2024Date of Patent: February 18, 2025Assignee: General Electric CompanyInventors: Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan, Clayton Stuart Cooper, Michael A. Benjamin, Steven C. Vise, Manampathy G. Giridharan, Krishnakumar Venkatesan
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Gas turbine combustor fuel nozzle assembly and combustor liner having dilution holes in arrangements
Patent number: 12215869Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.Type: GrantFiled: August 21, 2023Date of Patent: February 4, 2025Assignee: General Electric CompanyInventors: Nayan Vinod Patel, Michael A. Benjamin -
Patent number: 12215868Abstract: An injector for a gas turbine engine includes an annular gas nozzle, a hydrogen feed conduit, and a disc. The annular gas nozzle is disposed along a central nozzle axis and includes a forward face, a frustoconical interior surface, and gas feed conduits that open at the frustoconical interior surface. The hydrogen feed conduit extends along the central nozzle axis through the annular gas nozzle. The hydrogen feed conduit and the frustoconical interior surface define there between an annular mixing chamber. The hydrogen feed conduit has an end portion that is axially displaced from the forward face. The end portion includes feed holes that open into the mixing chamber. The disc is disposed on the end portion and is diametrically larger than the end portion so as to form a forward boundary of the annular mixing chamber. The disc may have multiple teeth, serrated edges, single or multiple bleed holes that are normal or angularly drilled to enhance fuel and air mixing, and improve flame stability.Type: GrantFiled: January 26, 2024Date of Patent: February 4, 2025Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Tin Cheung John Hu
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Patent number: 12215870Abstract: A gas turbine engine including a compressor section, a combustor for combusting a fuel, and a turbine. Compressed air flows through a combustion liner of the combustor in a bulk airflow direction. The combustor includes a primary fuel nozzle and a secondary fuel nozzle. The secondary fuel nozzle is downstream of the primary fuel nozzle in the bulk airflow direction. The primary fuel nozzle is configured to inject a primary portion of the fuel into a primary combustion zone, and the secondary fuel nozzle is configured to inject a secondary portion of the fuel into a secondary combustion zone. The secondary combustion zone is located downstream of the primary combustion zone in the bulk airflow direction. The fuel may be one of diatomic hydrogen fuel and a hydrogen enriched fuel.Type: GrantFiled: December 5, 2023Date of Patent: February 4, 2025Assignee: GENERAL ELECTRIC COMPANYInventors: Manampathy G. Giridharan, Pradeep Naik
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Patent number: 12215626Abstract: There is provided a method of starting a gas turbine engine, comprising: selecting a baseline starting procedure of the gas turbine engine based on environmental data; receiving condition information for the gas turbine engine and/or for a starting system of the gas turbine engine, the condition information comprising at least one of: health information for the gas turbine engine and/or the starting system; maintenance information for the gas turbine engine and/or the starting system; and operation information relating to an expected future usage of the gas turbine engine. The method further comprises determining a predicted degradation profile for the gas turbine engine and/or the starting system based on the condition information; determining a starting procedure of the gas turbine engine by adapting the baseline starting procedure based on the predicted degradation profile; and controlling the gas turbine engine and/or the starting system according to the determined starting procedure.Type: GrantFiled: October 17, 2023Date of Patent: February 4, 2025Assignee: Rolls-Royce plcInventors: David M. Donnelly, Caroline L. Turner, Derek S. Wall, Peter F. Douglas
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Patent number: 12203414Abstract: The present disclosure provides a device to produce higher pressure and temperature in a gas, the device including a rotation device adapted to rotate a shaft, an inlet for gas, and at least one shovel wheel.Type: GrantFiled: July 1, 2022Date of Patent: January 21, 2025Assignee: Hyper Energy Australia Pty LtdInventor: Åge Jørgen Skomsvold
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Patent number: 12196420Abstract: A connecting apparatus for fluid connection between a fuel feed line system and a nozzle apparatus of a gas turbine arrangement, includes a gas fuel line which is surrounded by a wall for conducting a gaseous fuel, and a liquid fuel line which is surrounded by a wall for conducting a liquid fuel. Optimized operation is achieved by the connecting apparatus having at least one separate gas line portion arranged on the inlet side of the gas fuel line and a gas/liquid line portion which is arranged downstream of the separate gas line portion and within which the gas fuel line and the liquid fuel line are arranged to form a line arrangement for connection to the nozzle apparatus. The flow cross section of the gas fuel line is of at least substantially identically large configuration within the separate gas line portion and the gas/liquid line portion.Type: GrantFiled: July 17, 2023Date of Patent: January 14, 2025Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Carsten Clemen
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Patent number: 12196140Abstract: A method of operating a turbomachine includes producing an estimate of a power gain resulting from operation of an inlet conditioning system of the turbomachine using a statistical model and producing an estimate of an economic benefit resulting from operation of the inlet conditioning system of the turbomachine using an economic model. The method further includes activating the inlet conditioning system of the turbomachine based on the estimate of the economic benefit.Type: GrantFiled: April 18, 2024Date of Patent: January 14, 2025Assignee: GE Infrastructure Technology LLCInventors: Jose Leon Vega Paez, Monica Lizbeth Perez Gamboa, Jose Augusto Lomenzo, Jose Alfredo Guerrero Ochoa
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Patent number: 12188435Abstract: Disclosed is a dual-mode ramjet engine including: a combustor through which air flowing in from the front passes; a sliding injector configured to perform a sliding operation from an upper surface of the combustor along a height direction perpendicular to an air flow direction; and a cavity-type flame holder formed behind the sliding injector on the upper surface of the combustor and having a cavity that is concavely recessed, wherein the sliding injector includes: a plurality of fuel injection holes formed on both sides and configured to inject fuel; a fuel injection passage passing through the inside along the height direction to be opened downward, and configured to inject fuel; and a first sliding drive unit configured to drive the sliding injector to perform the sliding operation.Type: GrantFiled: March 19, 2024Date of Patent: January 7, 2025Assignee: AGENCY FOR DEFENSE DEVELOPMENTInventors: Juhyun Bae, Sangwook Jin, Haeseung Jeong, Minchan Kwon, Seokjin Oh
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Patent number: 12181152Abstract: A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage, and a liquid swirler concentrically disposed about the inflow tube, the liquid swirler including a liquid swirler inner wall, liquid swirler outer wall having a liquid swirler outer wall end portion angled radially inward toward the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall having an RAS inner wall end portion angled radially inward toward the nozzle axis such that it is parallel to the liquid swirler outer wall end portion, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween. The end cap includes a radiused inner surface and an outer surface.Type: GrantFiled: April 4, 2024Date of Patent: December 31, 2024Assignee: RTX CorporationInventors: Zhongtao Dai, Justin M. Locke
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Patent number: 12173651Abstract: A propulsion system is provided for an aircraft. This propulsion system includes a turbine engine, and the turbine engine includes a propulsor rotor, an engine core and a heat exchanger. The propulsor rotor is configured to rotate about an axis and direct a first air stream along a primary flowpath that bypasses the engine core. The propulsor rotor is configured to direct a second air stream along a secondary flowpath with a geometry extending at least eighty degrees about the axis. The turbine engine is configured such that the first air stream enters the primary flowpath at a first pressure and the second air stream enters the secondary flowpath at a second pressure that is different than the first pressure. The engine core is configured to drive rotation of the propulsor rotor. The heat exchanger is disposed within the secondary flowpath.Type: GrantFiled: May 15, 2023Date of Patent: December 24, 2024Assignee: RTX CORPORATIONInventors: Neil J. Terwilliger, Simon W. Evans