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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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公开(公告)号：US11746659B2
公开(公告)日：2023-09-05
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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公开(公告)号：US11686211B2
公开(公告)日：2023-06-27
申请号：US17412222
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 , F01D17/08 , F05D2220/32 , F05D2240/12 , F05D2270/10 , F05D2270/102 , F05D2270/301
Abstract: A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan forces 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 adjusts a direction of the fan exit air, and includes a plurality of outlet guide vanes and a plurality of actuation assemblies that control rotation of the outlet guide vanes about a pitch axis. The outlet guide vanes include a leading edge portion and a trailing edge portion rotatably coupled to an axially aft edge of the leading edge portion. The actuation assembly rotates the leading edge portion and the trailing edge portion to minimize losses created by distortions in fan inlet air and created by the leading edge portion redirecting the fan exit air in the first direction.
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公开(公告)号：US20230060832A1
公开(公告)日：2023-03-02
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.
IPC: F01D17/16
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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Patent Agency Ranking
公开(公告)号：US11680524B1
公开(公告)日：2023-06-20
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 , F05D2250/283 , F05D2260/31 , F05D2260/96
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：US20230134727A1
公开(公告)日：2023-05-04
申请号：US17518897
申请日：2021-11-04
Applicant: Rolls-Royce Corporation
Inventor： Daniel E. Molnar, JR. , Christopher D. Hall
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：US20230061349A1
公开(公告)日：2023-03-02
申请号：US17412222
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 forces 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 adjusts a direction of the fan exit air, and includes a plurality of outlet guide vanes and a plurality of actuation assemblies that control rotation of the outlet guide vanes about a pitch axis. The outlet guide vanes include a leading edge portion and a trailing edge portion rotatably coupled to an axially aft edge of the leading edge portion. The actuation assembly rotates the leading edge portion and the trailing edge portion to minimize losses created by distortions in fan inlet air and created by the leading edge portion redirecting the fan exit air in the first direction.
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公开(公告)号：US11560801B1
公开(公告)日：2023-01-24
申请号：US17561632
申请日：2021-12-23
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Christopher D. Hall
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 magnetorheological fluid disposed in the cavity. A viscosity of the magnetorheological fluid increases in response to a magnetic field being generated proximate to the fluid in response to the airfoil experiencing an aeromechanic response or vibrations. As such, 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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公开(公告)号：US20190017387A1
公开(公告)日：2019-01-17
申请号：US15651156
申请日：2017-07-17
Applicant: Rolls-Royce Corporation
Inventor： Christopher D. Hall , Daniel E. Molnar
Abstract: According to one aspect, an airfoil assembly for a gas turbine engine comprises a first end wall, a second end wall, an airfoil and a sheath. The first end wall has surfaces defining a first recess, and the second end wall has surfaces defining a second recess. The airfoil includes a first portion disposed in the first recess, a second portion disposed in the second recess, and a leading edge disposed between the first and second portions. The sheath is in contact with the first and second portions of the airfoil covering the leading edge between the surfaces defining the first and second recesses.
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