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公开(公告)号：US20240360784A1
公开(公告)日：2024-10-31
申请号：US18309023
申请日：2023-04-28
IPC分类号： F02C3/04
CPC分类号： F02C3/04
摘要： A propulsion system for an aircraft includes a fan that is rotatable about a fan axis, a core engine that is configured for generating a gas flow utilized to generate shaft power for driving the fan, a nacelle that surrounds the core engine and the fan, a condenser where water in the gas flow is condensed into a liquid form, an exhaust duct assembly where the gas flow exhausted from the core engine is directed to the condenser, an ejector duct where a portion of a bypass airflow is thermally communicated with the condenser to cool the gas flow, and an evaporator assembly that is in thermal communication with the exhaust duct where water recovered by the condenser is heated to generate a steam flow that is subsequently communicated to the core engine.
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公开(公告)号：US20240360772A1
公开(公告)日：2024-10-31
申请号：US18308960
申请日：2023-04-28
发明人： Michael G. McCaffrey
IPC分类号： F01D11/22
CPC分类号： F01D11/22 , F05D2220/323 , F05D2240/11
摘要： A blade outer airseal assembly of a gas turbine engine includes a blade outer airseal (BOAS) segment, and a BOAS carrier positioned radially outboard of the BOAS segment relative to an engine central longitudinal axis. The BOAS segment is secured to the BOAS carrier, and an adjustment lever is operably connected to the BOAS carrier. Rotation of the adjustment lever about a pivot axis at a pivot urges movement of the BOAS segment in a radial direction.
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公开(公告)号：US12129802B2
公开(公告)日：2024-10-29
申请号：US17903681
申请日：2022-09-06
发明人： Paul R. Hanrahan
IPC分类号： F02C7/36
CPC分类号： F02C7/36 , F05D2220/323 , F05D2260/40311 , F05D2260/902
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a compressor section, a combustor section, a turbine section and a flowpath extending sequentially through the compressor section, the combustor section and the turbine section. The assembly also includes a turbine rotor, a propulsor rotor and an auxiliary turbine. The turbine rotor is within the turbine section. The turbine rotor is configured to rotatably drive the propulsor rotor. The auxiliary turbine includes an auxiliary turbine rotor. The auxiliary turbine rotor is configured to rotatably drive the propulsor rotor with the turbine rotor. The auxiliary turbine is configured to receive bleed gas from the flowpath.
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公开(公告)号：US20240353186A1
公开(公告)日：2024-10-24
申请号：US18304771
申请日：2023-04-21
发明人： ORIN G. AVIDANE , TYLER G. VINCENT , SUBHADEEP GAN
CPC分类号： F28F9/02 , F02C7/12 , F05D2260/20 , F05D2260/22141 , F28F2009/0292 , F28F2215/00
摘要： A heat exchanger can comprise: a housing; a heat transfer region disposed within the housing; and an inlet manifold or an inlet conduit defined at least partially by an interior surface extending axially from a first end of the heat exchanger to an inlet defined by the heat transfer region, the inlet manifold or the inlet conduit comprising a protrusion configuration disposed in the interior surface. The heat exchanger can further comprise an outlet manifold or an outlet conduit including a protrusion configuration disposed on an interior surface of the outlet manifold or outlet conduit.
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公开(公告)号：US20240352968A1
公开(公告)日：2024-10-24
申请号：US18137865
申请日：2023-04-21
CPC分类号： F16C32/0442 , F01D25/125 , F02C7/06 , F16C17/024 , F05D2240/51 , F05D2260/232
摘要： An assembly is provided for a turbine engine. This assembly includes a stationary structure, a rotating structure, a magnetic-foil bearing and a cooling system. The rotating structure is rotatable about an axis. The magnetic-foil bearing radially supports the rotating structure within the stationary structure. The magnetic-foil bearing includes a magnetic bearing stator, a magnetic bearing rotor and a foil bearing. The foil bearing is disposed radially between the magnetic bearing stator and the magnetic bearing rotor. The cooling system includes a cooling circuit configured to deliver cooling air to at least a first bearing component. The first bearing component is configured as or otherwise includes one of the magnetic bearing stator, the magnetic bearing rotor and the foil bearing.
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公开(公告)号：US20240352967A1
公开(公告)日：2024-10-24
申请号：US18137867
申请日：2023-04-21
CPC分类号： F16C32/0402 , F16C17/024 , F16C32/0474 , F16C37/005 , F16C2360/23
摘要： A bearing system is provided that includes a stationary structure, a rotating structure, a magnetic-foil bearing and a cooling jacket. The rotating structure is rotatable about an axis. The magnetic-foil bearing radially supports the rotating structure within the stationary structure. The magnetic-foil bearing includes a magnetic bearing stator, a magnetic bearing rotor and a foil bearing. The foil bearing is disposed radially between the magnetic bearing stator and the magnetic bearing rotor. The cooling jacket circumscribes and radially engages the magnetic bearing stator. A cooling circuit is configured to flow cooling fluid within the cooling jacket to cool the magnetic bearing stator.
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公开(公告)号：US20240352966A1
公开(公告)日：2024-10-24
申请号：US18137862
申请日：2023-04-21
CPC分类号： F16C32/0402 , F16C17/024 , F16C32/0474 , F16C2360/23
摘要： A bearing assembly is provided that includes a frame, a magnetic bearing stator and a foil bearing. The frame extends axially along and circumferentially about an axis. The frame includes an inner bore and a plurality of channels arranged circumferentially about the axis. The magnetic bearing stator includes a stator body and a plurality of windings. The stator body circumscribes the frame. The stator body includes a plurality of stator protrusions arranged circumferentially about the axis. Each of the stator protrusions projects radially inward into a respective one of the channels. Each of the windings is wrapped around a respective one of the stator protrusions. The foil bearing is disposed within the inner bore and retained to the frame.
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公开(公告)号：US20240352867A1
公开(公告)日：2024-10-24
申请号：US18136115
申请日：2023-04-18
发明人： Scott Goyette , Gregory S. Hagen , Zaffir A. Chaudhry , Paul Attridge , Janet Shaw , David L. Lincoln , Jeffrey P. King
CPC分类号： F01D21/003 , H04N7/188 , H04N23/90 , F05D2260/83
摘要： An assembly for an aircraft propulsion system includes a propulsor and an imaging assembly. The propulsor includes a propulsor disk, a plurality of propulsor blades, and a nose cone. The plurality of propulsor blades are circumferentially distributed about the propulsor disk. Each propulsor blade of the plurality of propulsor blades extends radially between and to a root end and a tip end. The root end is disposed at the propulsor disk. The propulsor disk and the plurality of propulsor blades are configured to rotate about the rotational axis. The nose cone is disposed axially adjacent the propulsor disk. The imaging assembly includes an imaging device disposed on the nose cone. The imaging device includes a camera. The camera is configured to capture image data of each propulsor blade of the plurality of propulsor blades as the plurality of propulsor blades rotate about the rotational axis.
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公开(公告)号：US20240352861A1
公开(公告)日：2024-10-24
申请号：US18304922
申请日：2023-04-21
发明人： Emma J. Place , Bryan P. Dube , Pedro D. Laureano , Bernard Joseph Reilly, III , Mohamed Hassan , Edwin Otero , Andrew Correia , William R. Hackbarth, II , Jeffrey M. Jacques
CPC分类号： F01D5/3007 , F01D5/02
摘要： An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.
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公开(公告)号：US12123373B2
公开(公告)日：2024-10-22
申请号：US16931685
申请日：2020-07-17
CPC分类号： F02K3/06 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2240/35 , F05D2240/60 , F05D2260/40311
摘要： A gas turbine engine includes a fan shaft rotatable about an axis, a fan connected to the fan shaft, and an outer housing surrounding the fan to define a bypass passage. A compressor section has both a low pressure compressor that is fixed to rotate with the fan shaft and a high pressure compressor. A turbine section has a low pressure turbine driving a low speed spool and a high pressure turbine driving the high pressure compressor. The low pressure turbine includes rotating blades and a static structure aft of the rotating blades. A fan drivetrain includes a geared architecture connecting the low speed spool to the fan shaft such that the fan and low pressure compressor rotate at a lower speed than the low pressure turbine. A thrust bearing is axially aft of the geared architecture and axially forward of the high pressure compressor. A tower shaft is rotatably driven by the low speed spool.
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