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公开(公告)号：US11591927B1
公开(公告)日：2023-02-28
申请号：US17553702
申请日：2021-12-16
Inventor： Christopher D. Hall , Robert W. Heeter , Daniel E. Molnar, Jr.
Abstract: A fan case assembly is adapted to extend around blades of a fan rotor included in a gas turbine engine. The fan case assembly includes an annular case that extends around an axis, a fan track liner coupled to the annular case and extending circumferentially at least partway about the axis, and a bolting arrangement that couples the fan track liner to the annular case.
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公开(公告)号：US20230193824A1
公开(公告)日：2023-06-22
申请号：US17553701
申请日：2021-12-16
Inventor： Robert W. Heeter , Christopher D. Hall , Daniel E. Molnar, Jr.
CPC classification number: F02C7/045 , F01D25/243 , B64D2033/0206
Abstract: A gas turbine engine includes a fan case assembly adapted to extend around blades of a fan rotor included in the gas turbine engine. The fan case assembly includes an annular case that extends around an axis, an acoustic panel coupled to the annular case and configured to dampen vibrations and a bolting arrangement that couples the acoustic panel to the annular case.
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公开(公告)号：US20230193823A1
公开(公告)日：2023-06-22
申请号：US17553700
申请日：2021-12-16
Inventor： Robert W. Heeter , Christopher D. Hall , Daniel E. Molnar, JR.
IPC: F02C7/045 , G10K11/172 , G10K11/168
CPC classification number: F02C7/045 , G10K11/172 , G10K11/168 , F05D2260/963 , F05D2300/121 , F05D2300/603 , F05D2300/612 , F05D2220/323
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：US11725520B2
公开(公告)日：2023-08-15
申请号：US17518897
申请日：2021-11-04
Applicant: Rolls-Royce Corporation
Inventor： Daniel E. Molnar, Jr. , Christopher D. Hall
CPC classification number: F01D5/16 , F01D5/147 , F05D2220/32 , F05D2230/60 , F05D2240/30 , F05D2260/96
Abstract: An airfoil for use in a gas turbine engine is formed to define cavities formed in the airfoil and a passage that extends between and fluidly interconnects the cavities. The airfoil further includes damping fluid located in the cavities and the damping fluid is adapted to flow between the cavities via the passage.
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公开(公告)号：US20230203952A1
公开(公告)日：2023-06-29
申请号：US17561617
申请日：2021-12-23
Inventor： Robert W. Heeter , Daniel E. Molnar, JR. , Christopher D. Hall
CPC classification number: F01D5/16 , F01D5/147 , F05D2260/961
Abstract: An airfoil for use in a gas turbine engine is formed to define a cavity formed in the airfoil. The airfoil further includes at least one obstructing member arranged within the cavity and a shear-thickening fluid disposed in the cavity. A viscosity of the shear-thickening fluid increases in response to the airfoil experiencing an aeromechanic response or vibrations such that the obstruction of the movement of the thicker fluid by the obstructing member dampens the vibrations of the airfoil and reduces negative effects of a dynamic response of the airfoil.
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Patent Agency Ranking
公开(公告)号：US20230066627A1
公开(公告)日：2023-03-02
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.
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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公开(公告)号：US20230066572A1
公开(公告)日：2023-03-02
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.
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：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：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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