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公开(公告)号：US12209502B1
公开(公告)日：2025-01-28
申请号：US18758996
申请日：2024-06-28
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Jonathan M. Rivers
Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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公开(公告)号：US12065258B2
公开(公告)日：2024-08-20
申请号：US18101567
申请日：2023-01-25
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Kathryn A. Sontag , Michael G. Meyer
IPC: B64D33/02
CPC classification number: B64D33/02 , B64D2033/0226 , B64D2033/0286
Abstract: An aircraft includes a duct system configured to receive a flow of air therethrough and a gas turbine engine. The duct system includes a main duct and inlet ducts arranged fluidly upstream of the main duct so as to conduct the flow of air from the inlet ducts into the main duct. The gas turbine engine in downstream fluid communication with the main duct.
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公开(公告)号：US12025059B1
公开(公告)日：2024-07-02
申请号：US18088994
申请日：2022-12-27
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Kathryn A. Sontag , Michael G. Meyer
CPC classification number: F02C9/20 , F02C3/04 , F02C6/00 , F05D2220/32 , F05D2220/70 , F05D2270/05 , F05D2270/101
Abstract: A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.
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24.发明授权公开(公告)号：US12018621B1
公开(公告)日：2024-06-25
申请号：US18234657
申请日：2023-08-16
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Michael S. Krautheim
CPC classification number: F02C9/22 , F01D17/141 , F02K3/06 , F04D29/542 , F05D2220/36 , F05D2240/12 , F05D2240/14
Abstract: A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a channel that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.
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公开(公告)号：US11970985B1
公开(公告)日：2024-04-30
申请号：US18234654
申请日：2023-08-16
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Jonathan M. Rivers , Michael S. Krautheim
CPC classification number: F02C9/22 , F01D17/141 , F04D29/526 , F04D29/542 , F04D29/68
Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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Patent Agency Ranking
公开(公告)号：US11946414B2
公开(公告)日：2024-04-02
申请号：US17553700
申请日：2021-12-16
Inventor： Robert W. Heeter , Christopher D. Hall , Daniel E. Molnar, Jr.
IPC: F02C7/045 , F02K1/82 , G10K11/168 , G10K11/172
CPC classification number: F02C7/045 , F02K1/827 , G10K11/168 , G10K11/172 , F05D2220/323 , F05D2260/963 , F05D2300/121 , F05D2300/603 , F05D2300/612
Abstract: An acoustic panel for a gas turbine engine, includes a panel body, a panel-body cover, and a support bracket. The panel body is configured to dampen vibrations caused by the gas turbine engine. The forward support bracket is configured to mount the acoustic panel to portions of the gas turbine engine.
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公开(公告)号：US11879343B2
公开(公告)日：2024-01-23
申请号：US17412220
申请日：2021-08-25
Applicant: Rolls-Royce Corporation
Inventor： Christopher D. Hall , William B. Bryan , Daniel E. Molnar, Jr.
CPC classification number: F01D17/162 , F01D17/02 , F01D9/041 , F04D29/563 , F05D2220/32 , F05D2240/12 , F05D2270/05 , F05D2270/101 , F05D2270/304 , F05D2270/334
Abstract: A fan assembly includes a fan duct, an inlet fan, an outlet guide vane assembly, and a control system. The inlet fan includes fan blades adapted to rotate about a central axis to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air. The outlet guide vane assembly includes a plurality of guide vanes that extend radially relative to the central axis and are configured to rotate to a first vane-pitch angle. The control system is configured to rotate the guide vanes redirect the fan exit air, vary a pressure downstream of the fan inlet, minimize intake flow distortion experienced by the inlet fan, reduce inlet fan vibratory response and/or improve fan operability margins.
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公开(公告)号：US11835064B1
公开(公告)日：2023-12-05
申请号：US18089029
申请日：2022-12-27
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Kathryn A. Sontag , Michael G. Meyer
CPC classification number: F04D29/661 , F02C3/04 , F02C6/00 , F02C9/16 , F04D25/06 , F04D27/004 , F05D2220/76
Abstract: A gas turbine engine comprises an engine core and an electric fan array. The engine core includes a compressor, a combustor, and a turbine. The compressor compresses and delivers air to the combustor. The combustor mixes fuel with the compressed air received from the compressor and ignites the fuel. The hot, high-pressure products of the combustion reaction in the combustor are directed into the turbine to cause the turbine to rotate about an axis and drive the compressor. The electric fan array may include at least two non-concentric fans having parallel shafts.
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公开(公告)号：US11802490B2
公开(公告)日：2023-10-31
申请号：US17412218
申请日：2021-08-25
Applicant: Rolls-Royce Corporation
Inventor： Christopher D. Hall , William B. Bryan , Daniel E. Molnar, Jr.
CPC classification number: F01D17/162 , F01D7/02 , F01D17/06 , F05D2240/12 , F05D2250/90 , F05D2260/56
Abstract: A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan includes blades adapted to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air received from the blades. The outlet guide vane assembly includes a first plurality of outlet guide vanes including a first outlet guide vane configured to rotate to a first angle so as to redirect the fan exit air in a first direction and a second outlet guide vane configured to rotate to a second angle so as to redirect the fan exit air in a second direction. The second outlet guide vane is located at a different circumferential position than the first outlet guide vane.
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公开(公告)号：US11788429B2
公开(公告)日：2023-10-17
申请号：US17412226
申请日：2021-08-25
Applicant: Rolls-Royce Corporation
Inventor： Christopher D. Hall , William B. Bryan , Daniel E. Molnar, Jr.
CPC classification number: F01D17/162 , F01D17/02 , F01D17/06 , F05D2220/32 , F05D2240/12 , F05D2270/102 , F05D2270/304
Abstract: A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan includes blades adapted to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air received from the blades. The outlet guide vane assembly includes a first plurality of vanes configured to rotate to redirect the fan exit air in a first direction, and a second plurality of vanes located downstream of the first plurality of vanes. The second plurality of vanes are configured to rotate to redirect the fan exit air flowing in the first direction in a second direction to minimize losses created by distortions in fan inlet air and created by the first vanes.
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