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公开(公告)号：US10156244B2
公开(公告)日：2018-12-18
申请号：US15042569
申请日：2016-02-12
Applicant: Rolls-Royce Corporation
Inventor： Roy D. Fulayter , Jonathan M. Rivers
Abstract: A fan assembly for use in a gas turbine engine includes a fan wheel and a plurality of blades extending radially from the fan wheel away from a central axis of the fan assembly. Each of the blades includes a root coupled with the fan wheel and an airfoil extending radially outwardly from the root. The blades are adapted to rotate about the central axis to push air.
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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：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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公开(公告)号：US20180119705A1
公开(公告)日：2018-05-03
申请号：US15337936
申请日：2016-10-28
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power , Jonathan M. Rivers
CPC classification number: F04D29/326 , B64C11/001 , B64C11/48 , B64C2201/162 , B64C2201/165 , B64D2027/005 , F01D5/143 , F01D5/225 , F02C9/58 , F02K3/04 , F02K3/072 , F04D19/002 , F04D29/023 , F05D2220/323 , F05D2220/326 , F05D2220/327 , F05D2220/36
Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about −5 degrees and about 45 degrees. Passive leading edge slats are attached to the ring airfoil and are configured to open and close using springs.
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公开(公告)号：US09932840B2
公开(公告)日：2018-04-03
申请号：US14698299
申请日：2015-04-28
Applicant: Rolls-Royce Corporation
Inventor： Roy D. Fulayter , Jonathan M. Rivers , Matthew Jordan , Daniel E. Molnar
CPC classification number: F01D5/26 , F01D5/027 , F01D5/10 , F01D5/146 , F01D5/16 , F05D2220/32 , F05D2260/96 , Y02T50/671 , Y02T50/673
Abstract: A rotor for a gas turbine engine includes a central wheel and a plurality of blades that extend outwardly from the central wheel. The blades are non-uniform to reduce flutter and forced response effects induced during operation of a gas turbine engine including the rotor.
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Patent Agency Ranking
公开(公告)号：US09759095B2
公开(公告)日：2017-09-12
申请号：US14145488
申请日：2013-12-31
Applicant: Rolls-Royce Corporation
Inventor： Jonathan M. Rivers , Roy D. Fulayter
CPC classification number: F01D25/24 , B23P15/04 , B64D29/08 , B64D33/02 , B64D2033/0273 , F02C7/04 , F02K3/06 , Y10T29/49238
Abstract: An integrated access panel is disclosed that can be used to assist in adjusting a component like a fan blade of a turbofan engine. in one form the integrated access panel is hinged at one end such that the panel remains attached during adjustment of the fan blade. The access panel can be positioned in an angled flow surface of a nacelle such that the fan blade cannot be removed from a wheel without removal of the nacelle or opening of the access panel. The integrated access panel can be spring-loaded and positioned to allow the fan blade to be removed from a wheel by moving the access panel out of the way. Subsequent blade removal can occur by rotation of the wheel to locate another blade in proximity to the access panel.
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7.发明申请公开(公告)号：US20140255187A1
公开(公告)日：2014-09-11
申请号：US14097865
申请日：2013-12-05
Applicant: Rolls-Royce Corporation
Inventor： Jonathan M. Rivers , Bronwyn Powers
IPC: F01D5/30
CPC classification number: F01D5/30 , F01D5/14 , F01D5/3007
Abstract: An airfoil member is disclosed having an attachment feature such as a fir tree or dovetail design that includes a curved profile formed from a combination of curves. In one embodiment, the curved profile can be a compound curve formed by a forward curve and a rearward curve that are joined at a point of common tangency. In another embodiment, the curved profile can include curves that do not meet at a common tangency. A cut out can be formed in the curved profile. In some forms, the cut out is formed on a pressure face of the attachment feature.
Abstract translation: 公开了一种翼型件，其具有诸如杉树或燕尾设计的附接特征，其包括由曲线的组合形成的弯曲轮廓。 在一个实施例中，弯曲轮廓可以是由正向曲线和向后曲线形成的复合曲线，其在公共切线点处相连。 在另一个实施例中，弯曲轮廓可以包括在公共切线处不符合的曲线。 可以在弯曲轮廓中形成切口。 在一些形式中，切口形成在附接特征的压力面上。
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公开(公告)号：US12286930B1
公开(公告)日：2025-04-29
申请号：US18537256
申请日：2023-12-12
Inventor： Robert W. Heeter , Jonathan M. Rivers , Daniel E. Molnar, Jr.
Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan casing and a bleed air flow control system. The fan casing includes an annular case and a fan track liner coupled with the annular case. The bleed air flow control system is configured to bleed selectively a portion of air flowing through a gas path of the fan case assembly for use as a cooling source in the fan case assembly.
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公开(公告)号：US12078070B1
公开(公告)日：2024-09-03
申请号：US18234656
申请日：2023-08-16
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Jonathan M. Rivers
CPC classification number: F01D17/14 , F01D25/24 , F05D2220/36 , F05D2270/301
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 plenum that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis.
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公开(公告)号：US20180231016A1
公开(公告)日：2018-08-16
申请号：US15338035
申请日：2016-10-28
Applicant: Rolls-Royce Corporation
Inventor： Bronwyn Power , Jonathan M. Rivers
CPC classification number: F04D29/282 , B23K2101/001 , B63H1/16 , B64C11/001 , B64C11/06 , B64C2201/162 , B64C2201/165 , B64D2027/005 , F01D5/143 , F01D5/225 , F02C9/58 , F02K3/04 , F02K3/072 , F04D29/326 , F04D29/329 , F04D29/34 , F05D2220/323 , F05D2220/326 , F05D2220/327 , F05D2220/36
Abstract: A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about −5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.
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