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公开(公告)号：US20240229726A1
公开(公告)日：2024-07-11
申请号：US18152903
申请日：2023-01-11
CPC分类号： F02C9/18 , F02C3/04 , F02C7/057 , F05D2220/10 , F05D2220/3217 , F05D2220/323
摘要： A propulsion system includes (a) a turbine engine including a compressor section, a combustor, and a turbine section, (b) a ramjet engine, and (c) an inlet section including a turbine engine inlet portion and a ramjet inlet portion, the inlet section providing an inlet airflow to the turbine engine and to the ramjet engine. The turbine engine inlet portion includes an expansion turbine arranged upstream of the compressor section.
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公开(公告)号：US11821366B2
公开(公告)日：2023-11-21
申请号：US17351023
申请日：2021-06-17
发明人： Brandon W. Miller , Robert Jon McQuiston , Stefan Joseph Cafaro , Eric Richard Westervelt , Michael A. Benjamin , Joel M. Haynes , Hejie Li
CPC分类号： F02C7/22 , F02C7/224 , F02C9/28 , F23R3/28 , F05D2220/32 , F05D2240/35 , F23R2900/00
摘要： A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.
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公开(公告)号：US20230366353A1
公开(公告)日：2023-11-16
申请号：US17663314
申请日：2022-05-13
CPC分类号： F02C7/25 , F02C7/232 , F02C7/224 , F02C3/22 , F02C7/222 , F05D2220/323 , F05D2240/36 , F05D2260/605
摘要： A hydrogen fuel system including a fuel delivery assembly, a purge gas source, and a vent. The fuel delivery assembly is configured to receive hydrogen fuel from a hydrogen fuel source and to provide the hydrogen fuel from the hydrogen fuel source to a power generator. The purge gas source is fluidly coupled to the fuel delivery assembly and configured to provide a purge gas to the fuel delivery assembly. The vent is fluidly coupled to the fuel delivery assembly and configured to vent hydrogen fuel from the fuel delivery assembly when the purge gas is provided to the fuel delivery assembly.
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公开(公告)号：US20230272749A1
公开(公告)日：2023-08-31
申请号：US17652790
申请日：2022-02-28
发明人： Hejie Li , Mathew Paul Thariyan , Diana Julieta Méndez Maya , Jorge Omar Mañón Cantú , Brandon W. Miller , Michael A. Benjamin , Brian Devendorf
摘要： A fuel system including a fuel metering unit, a heat exchanger, a plurality of fuel nozzles, and a coke filtration system. The fuel metering unit is configured to meter a flow of a hydrocarbon fuel. The heat exchanger is fluidly connected to the fuel metering unit. The heat exchanger is configured to heat the hydrocarbon fuel to improve engine performance or efficiency. The plurality of fuel nozzles is fluidly connected to the heat exchanger downstream of the heat exchanger to receive the hydrocarbon fuel heated by the heat exchanger. The coke filtration system includes at least one filter to remove coke particles in the heated fuel. The coke filtration system is located upstream of the plurality of fuel nozzles and directly downstream of the heat exchanger.
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公开(公告)号：US12116935B2
公开(公告)日：2024-10-15
申请号：US18310386
申请日：2023-05-01
发明人： Brandon W. Miller , Robert Jon McQuiston , Stefan Joseph Cafaro , Eric Richard Westervelt , Michael A. Benjamin , Joel M. Haynes , Hejie Li
CPC分类号： F02C7/22 , F02C7/224 , F02C9/28 , F05D2220/32 , F05D2240/35 , F05D2260/20
摘要： A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.
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公开(公告)号：US20240174375A1
公开(公告)日：2024-05-30
申请号：US18316450
申请日：2023-05-12
摘要： An aircraft fuel system includes a first fuel storage tank arranged to store a first fuel, a second fuel storage tank arranged to store a reduced oxygen fuel, and a fuel tank inerting system arranged to provide a reduced oxygen gas through a fuel contained within the second fuel storage tank to generate the reduced oxygen fuel within the second fuel storage tank. The fuel tank inerting system may include a fuel tank sparging system to inject the reduced oxygen gas directly into the fuel contained within the second fuel storage tank to generate the reduced oxygen fuel.
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公开(公告)号：US20230059995A1
公开(公告)日：2023-02-23
申请号：US17406930
申请日：2021-08-19
摘要： Acoustic turbofan airfoil apparatus are disclosed. An example apparatus includes a platform of a turbofan engine, the platform including perforations to receive acoustic waves, acoustic chambers protruding from a first side of the platform, the acoustic chambers aligned with the perforations in a radial direction defined by the turbofan engine, the acoustic chambers to attenuate the acoustic waves, and an airfoil protruding from a second side of the platform opposite the first side of the platform.
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公开(公告)号：US20240271542A1
公开(公告)日：2024-08-15
申请号：US18169328
申请日：2023-02-15
发明人： Brandon W. Miller , Arda Unsal , Paul Pezzi
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D5/085 , F05D2220/30 , F05D2220/32 , F05D2240/55
摘要： A low-pressure (LP) turbine includes an LP shaft, one or more stages of LP turbine stator vanes and LP turbine rotor blades, and one or more interstage seals. The LP turbine rotor blades are coupled to, and rotate with, the LP shaft. The one or more interstage seals are disposed between the one or more stages. The one or more interstage seals each includes a seal disk that extends radially inward of the LP turbine stator vanes. Each seal disk includes an outer shell that supports one or more seal teeth, and the outer shell rotates as the LP shaft rotates.
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公开(公告)号：US12055960B2
公开(公告)日：2024-08-06
申请号：US17702563
申请日：2022-03-23
发明人： Biao Fang , David Justin Brady , John C. Glessner , Brandon W. Miller , Stephanie Glynn Cotten , William Dwight Gerstler , Daniel A. Niergarth , Michael Joseph Murray
CPC分类号： G05D7/0635 , F16K11/0712 , F16K31/406 , G05D7/005 , G05D11/003 , F16K11/065 , Y10T137/86598
摘要： Example split valves for regulating a first flowrate and a second flowrate of a fluid within a closed loop systems are disclosed herein. An example split valve includes an electrohydraulic servo valve coupled to a first piston via a first hydraulic flowline and a second hydraulic flowline, the first piston to include a piston shaft, a first head, and a second head; one or more bellows fixed to at least one of the first head or the second head, the one or more bellows to hermetically seal the fluid from a hydraulic fluid; and a control system connected to the electrohydraulic servo valve, the control system to adjust the first flowrate and the second flowrate of the fluid through a first fluid chamber, the first piston to be located in the first fluid chamber.
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公开(公告)号：US11808214B2
公开(公告)日：2023-11-07
申请号：US18058034
申请日：2022-11-22
发明人： Narayanan Payyoor , Weize Kang , Brandon W. Miller , Bugra Ertas , Andrea Piazza
CPC分类号： F02C7/36 , F02C7/06 , F05D2220/32 , F05D2240/50 , F05D2240/60 , F05D2260/40
摘要： A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.
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