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    Fan assembly
    1.
    发明授权
    Fan assembly 有权

    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

    IPC: F04D29/66 ,  F04D29/32 ,  F01D5/16 ,  F01D5/30

    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.

    PIEZOELECTRIC DAMPING RINGS
    2.
    发明申请
    PIEZOELECTRIC DAMPING RINGS 审中-公开

    公开(公告)号：US20170306772A1

    公开(公告)日：2017-10-26

    申请号：US15410129

    申请日：2017-01-19

    Applicant: Rolls-Royce Corporation

    Inventor： Roy D. Fulayter ,  Daniel Hoyniak

    IPC: F01D5/34 ,  F01D25/04 ,  F01D5/10 ,  F04D29/66

    CPC classification number: F01D5/34 ,  F01D5/10 ,  F01D25/04 ,  F04D29/321 ,  F04D29/324 ,  F04D29/668 ,  F05D2260/407 ,  F05D2260/96 ,  F05D2260/962 ,  Y02T50/672

    Abstract: A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.

    ULTRA HIGH BYPASS RATIO TURBOFAN ENGINE
    3.
    发明申请
    ULTRA HIGH BYPASS RATIO TURBOFAN ENGINE 审中-公开
    超高压比涡轮发动机

    公开(公告)号：US20140363276A1

    公开(公告)日：2014-12-11

    申请号：US14101438

    申请日：2013-12-10

    Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

    Inventor： Daniel K. Vetters ,  Michael Karam ,  Roy D. Fulayter

    IPC: F02K3/075

    CPC classification number: F02K3/075 ,  F02C7/36 ,  F02K3/04 ,  F05D2260/4031 ,  Y02T50/671

    Abstract: An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24.

    Abstract translation: 超高旁通比涡扇发动机包括可变桨距风扇，低压涡轮机，减速齿轮箱和多个出口导叶。 超高旁路比涡扇发动机的旁通比约为18至40左右。变桨距风机和低压涡轮机通过减速齿轮箱联结在一起。 减速齿轮箱相对于低压涡轮机降低了变桨距风扇的速度。 多个出口导向叶片在可变节距风扇的后部间隔开并且被轴向扫掠。 可变节距风扇和低压涡轮机构造成产生约1.15至约1.24之间的风扇压力比。

    Piezoelectric damping rings
    8.
    发明授权
    Piezoelectric damping rings 有权

    公开(公告)号：US10557352B2

    公开(公告)日：2020-02-11

    申请号：US14845478

    申请日：2015-09-04

    Applicant: Rolls-Royce Corporation

    Inventor： Roy D. Fulayter ,  Daniel Hoyniak

    IPC: F01D5/10 ,  F01D5/12 ,  G10K11/00

    Abstract: A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.

    Variable pitch fan for a gas turbine engine
    9.
    发明授权
    Variable pitch fan for a gas turbine engine 有权

    公开(公告)号：US10539024B2

    公开(公告)日：2020-01-21

    申请号：US15644159

    申请日：2017-07-07

    Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

    Inventor： Roy D. Fulayter ,  Daniel K. Vetters ,  Bronwyn Power

    IPC: F01D5/12 ,  F01D17/16 ,  F04D29/56

    Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.

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