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公开(公告)号：US20240337228A1
公开(公告)日：2024-10-10
申请号：US18745410
申请日：2024-06-17
IPC分类号： F02K3/06
CPC分类号： F02K3/06 , F05D2200/14
摘要： A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes four rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 2.0-5.1. Additionally (or alternatively) the low-pressure turbine includes an area-EGT ratio within a range of 1.05-1.6.
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公开(公告)号：US20240336369A1
公开(公告)日：2024-10-10
申请号：US18750089
申请日：2024-06-21
摘要： An aircraft including a fuselage, a power generator configured to provide power to the aircraft, and at least one fuel tank for holding fuel for the power generator, and a fuel delivery assembly. The fuel tank is positioned in the fuselage and is configured to hold hydrogen fuel in a liquid phase. The fuel tank has a chamber for holding the hydrogen fuel and a fuel extraction line fluidly coupled to the chamber. The fuel extraction line extends from the fuel tank in a forward direction of the fuselage and at a downward angle relative to a centerline of the fuselage. The fuel delivery assembly is fluidly coupled to the fuel extraction line and fluidly connects the fuel tank to the power generator. The fuel delivery assembly is configured to provide the hydrogen fuel from the fuel tank to the power generator.
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63.发明授权公开(公告)号：US12111057B2
公开(公告)日：2024-10-08
申请号：US18320682
申请日：2023-05-19
摘要： A mixer for blending fuel and air in a combustor of a turbine engine. The mixer includes a central body having a central passageway and a central axis. The mixer includes a plurality of tubes positioned radially around the central axis and circumferentially around a periphery of the mixer. Each of the tubes of the mixer includes opposed openings and a tangential opening. Each of the tubes of the mixer includes a cylindrical interior mixing passage configured to receive air flow from the opposed openings and the tangential opening and a fuel flow. The opposed openings are configured to spread the fuel flow laterally and the tangential opening is configured to spread the fuel flow tangentially.
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公开(公告)号：US12110827B1
公开(公告)日：2024-10-08
申请号：US18311660
申请日：2023-05-03
CPC分类号： F02C7/236 , F02C7/32 , F05D2220/323 , F05D2270/07
摘要： A turbo engine for an aircraft includes a gas turbine engine having a combustion section and a fuel system to provide pressurized fuel to the combustion section. The fuel system includes a fuel tank and a boost pump and a main pump driven by an accessory gearbox that is powered by a shaft of the turbo engine. The boost pump and the main pump are arranged in series. The fuel system also includes an auxiliary pump and a controller to operate the fuel system in (1) a first mode in which the boost pump and the main pump produce pressurized fuel for the turbo engine and the auxiliary pump is deactivated, and (2) a second mode in which the auxiliary pump is activated and produces the pressurized fuel for the turbo engine while bypassing the boost pump and the main pump.
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公开(公告)号：US12104531B2
公开(公告)日：2024-10-01
申请号：US18059519
申请日：2022-11-29
CPC分类号： F02C7/12 , F02C3/04 , F05D2260/20
摘要： A cooling system for a turbine engine. The turbine engine includes a compressor, a turbine, and a shaft that drivingly couples the compressor and the turbine. The cooling system includes one or more cavities of the compressor. The cooling system includes a shaft flowpath defined in the shaft. The shaft includes one or more shaft apertures that provide fluid communication between the shaft flowpath and the one or more cavities. Air passes through the one or more shaft apertures and the shaft flowpath during a shutdown of the turbine engine to cool the one or more cavities.
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公开(公告)号：US20240323088A1
公开(公告)日：2024-09-26
申请号：US18579253
申请日：2022-07-15
发明人： Stephen Francis BUSH
IPC分类号： H04L41/0894 , H04L41/0895
CPC分类号： H04L41/0894 , H04L41/0895
摘要： Techniques for communication over a communication network may include determining a plurality of network slices based on a plurality of services supported by the communication network, wherein each of the plurality of network slices supports communication of data associated with at least one service. A plurality of data streams may be configured within the communication network. Each data stream being configured in accordance with at least one of a plurality of time-sensitive network policies. A first data stream of the plurality of data streams corresponding to a first network slice of the plurality of network slices may be determined.
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公开(公告)号：US20240318821A1
公开(公告)日：2024-09-26
申请号：US18186518
申请日：2023-03-20
IPC分类号： F23R3/06
摘要： A combustor having a casing, an inner liner, an outer liner, a compressed air passageway, a combustion chamber and at least one dilution passage. The compressed air passageway being formed between the casing, the inner liner and the outer liner. The combustion chamber being at least partially defined by the inner liner and the outer liner. The at least one dilution passage extending through at least one of the inner liner or the outer liner. The at least one dilution passage extending between an inlet fluidly coupled to the compressed air passageway and a dilution hole fluidly coupled to the combustion chamber.
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公开(公告)号：US20240318688A1
公开(公告)日：2024-09-26
申请号：US18313145
申请日：2023-05-05
发明人： Pravin Ganpati Patil , Ravindra Shankar Ganiger , Santosh Kumar Potnuru , Santosh Kumar Prasad , Pradeep Hemant Sangli , Rajesh Kumar , Mark L. Hopper
CPC分类号： F16C33/46 , F16C33/66 , F16C2360/23
摘要： Lubricant draining bearing assemblies are disclosed. An example apparatus includes a first race, a second race, roller bearings positioned between the first race and the second race, and a cage positioned around the roller bearings between the first race and the second race, the cage including a first radial surface, a second radial surface, and an axial surface, the first radial surface facing the first race, the second radial surface facing the second race, the axial surface facing away from the roller bearings, the cage including at least one conduit extending between the first radial surface and at least one of the second radial surface or the axial surface, the conduit defining a flow path for a fluid out of a cavity between the first race, the roller bearings, and the cage.
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公开(公告)号：US20240318613A1
公开(公告)日：2024-09-26
申请号：US18680469
申请日：2024-05-31
发明人： Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig Williams Higgins , Alexander Kimberley Simpson , Syed Arif Khalid , Jeffrey S. Spruill , Daniel Lawrence Tweedt , William Joseph Solomon , Kevin Edward Hinderliter
摘要： A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
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公开(公告)号：US20240318598A1
公开(公告)日：2024-09-26
申请号：US18736683
申请日：2024-06-07
摘要： A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
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