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公开(公告)号：US20190120250A1
公开(公告)日：2019-04-25
申请号：US15789456
申请日：2017-10-20
Inventor： Christopher Hall , Russell White , Jonathan Acker , Lyle Helvie
CPC classification number: F04D29/563 , F04D29/644
Abstract: An apparatus and method of controlling the position of a variable vane in a compressor and a kit for adding such apparatus to the compressor are disclosed. The vane is coupled to a unison ring, a cam is secured to a torque tube, a cam follower is secured to the unison ring. The cam follower is secured such that a wall of the cam follower is in contact with the cam. Rotation of the torque tube causes movement of the cam, and movement of the cam moves the cam follower, thereby moving the unison ring and the variable vane coupled thereto.
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公开(公告)号：US11008887B2
公开(公告)日：2021-05-18
申请号：US16229615
申请日：2018-12-21
Applicant: Rolls-Royce Corporation
Inventor： Christopher Hall , Matthew Kappes , Glenn Patterson , Robert Heeter
Abstract: A containment assembly is disclosed for a turbofan engine. The containment assembly comprises a forward fence, an aft fence, a fan track liner, an intermediate casing member, an outer casing member, and an annular nesting cavity. The fan track liner is disposed axially between the forward and aft fences. The intermediate casing member is disposed radially outward of at least a portion of the fan track liner. The outer casing member is disposed radially outward of at least a portion of the intermediate member. The annular nesting cavity is bounded at least in part by the intermediate casing member and the outer casing member.
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公开(公告)号：US10883379B2
公开(公告)日：2021-01-05
申请号：US15977446
申请日：2018-05-11
Applicant: Rolls-Royce Corporation , Rolls-Royce plc
Inventor： Christopher Hall , Glenn Knight
Abstract: A variable diffuser comprises a passage, at least two vanes disposed within the passage, and at least two pennies. The passage is defined between opposing disk faces of a hub and a tip. Each of the vanes comprises a body having a leading edge and a trailing edge. The body extends between the hub face and the disk face. Each of the pennies is coupled to a respective vane body near an edge of the penny and an actuator. Rotation of at least one penny changes the orientation of the respective vane relative to the hub face.
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公开(公告)号：US10883373B2
公开(公告)日：2021-01-05
申请号：US15448318
申请日：2017-03-02
Applicant: Rolls-Royce Corporation
Inventor： Christopher Hall , M. Stephen Krautheim
Abstract: A blade tip sealing portion forms the distal end of a rotor blade in a turbine engine to reduce or prevent leakage through the blade tip clearance. A rotor assembly comprises a casing, a rotor, and at least one rotor blade coupled to the rotor. The rotor blade comprises a root portion coupled to the rotor, a main airfoil body extending radially from the root portion, and a blade tip sealing portion. The blade tip sealing portion comprises a blade tip platform and a plurality of sealing members. The sealing members are positioned on the blade tip platform at an angle substantially perpendicular to an air flow across the blade tip platform and are spaced to effect overlap of adjacent sealing members in the direction of the air flow.
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公开(公告)号：US20200271060A1
公开(公告)日：2020-08-27
申请号：US16281995
申请日：2019-02-21
Inventor： Christopher Hall , William Barry Bryan
Abstract: A system and method for meeting take off noise requirements in a gas turbine engine with a multi-stage fan, comprising an inlet passage, a core passage, a bypass passage and a mid-stage offtake passage; the core passage comprising a core inlet, high pressure compressor, combustor, high pressure turbine, low pressure turbine and a core exhaust; the bypass passage comprising a primary bypass inlet and a primary bypass exit; the mid-stage offtake passage comprising an offtake inlet and offtake exit; a first stage comprising a first rotor, and a second stage comprising a second rotor; and a variable guide vane located axially between the first rotor and the second rotor; an actuator coupled to and selectively varying the variable guide vane between two or more orientations; a variable offtake exit thrust nozzle; and, wherein a gas stream exiting the inlet passage enters one of the core, bypass or mid-stage off take passages as a function of the two or more orientations.
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Patent Agency Ranking
公开(公告)号：US10508660B2
公开(公告)日：2019-12-17
申请号：US15789456
申请日：2017-10-20
Inventor： Christopher Hall , Russell White , Jonathan Acker , Lyle Helvie
Abstract: An apparatus and method of controlling the position of a variable vane in a compressor and a kit for adding such apparatus to the compressor are disclosed. The vane is coupled to a unison ring, a cam is secured to a torque tube, a cam follower is secured to the unison ring. The cam follower is secured such that a wall of the cam follower is in contact with the cam. Rotation of the torque tube causes movement of the cam, and movement of the cam moves the cam follower, thereby moving the unison ring and the variable vane coupled thereto.
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公开(公告)号：US20180016934A1
公开(公告)日：2018-01-18
申请号：US15211964
申请日：2016-07-15
Applicant: Rolls-Royce Corporation
Inventor： Christopher Hall , Graham Burkholder , Xuekun Sun , Jeff Crutchfield , Ben Hodgson , Dennes Kyle Burney
CPC classification number: F01D21/003 , F01D5/34 , F01D21/045 , F04D29/322 , F04D29/644 , F42B3/006
Abstract: According to one aspect, a method of releasing a fan blade for testing a turbofan engine includes providing an internal passage with a constant arc through an airfoil arranged about a blisk such that the constant arc of the internal passage aligns with a contour of the blisk. The method further includes packing the internal passage with a charge, modifying the airfoil such that the airfoil is released from the blisk evenly along a chordwise length of the airfoil, and detonating the charge such that the airfoil is released from the blisk at a selected time.
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8.发明授权公开(公告)号：US11879480B1
公开(公告)日：2024-01-23
申请号：US18132177
申请日：2023-04-07
Inventor： Eric Engebretsen , Christopher Hall , Erick Meyer
CPC classification number: F04D29/563 , F04D29/542 , F04D19/002 , F04D29/023 , F05D2230/20 , F05D2240/12
Abstract: A compressor assembly for a gas turbine engine includes an outer band, a plurality of variable pitch vanes, and an inner band. The plurality of variable pitch vanes extend radially between the outer band and the inner band. The inner band extends circumferentially partway about an axis and includes a first ring segment and a second ring segment that cooperate to receive the plurality of variable pitch vanes.
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9.发明授权公开(公告)号：US10113442B2
公开(公告)日：2018-10-30
申请号：US15211964
申请日：2016-07-15
Applicant: Rolls-Royce Corporation
Inventor： Christopher Hall , Graham Burkholder , Xuekun Sun , Jeff Crutchfield , Ben Hodgson , Dennes Kyle Burney
Abstract: According to one aspect, a method of releasing a fan blade for testing a turbofan engine includes providing an internal passage with a constant arc through an airfoil arranged about a blisk such that the constant arc of the internal passage aligns with a contour of the blisk. The method further includes packing the internal passage with a charge, modifying the airfoil such that the airfoil is released from the blisk evenly along a chordwise length of the airfoil, and detonating the charge such that the airfoil is released from the blisk at a selected time.
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公开(公告)号：US20180017065A1
公开(公告)日：2018-01-18
申请号：US15212027
申请日：2016-07-15
Applicant: Rolls-Royce Corporation
Inventor： Christopher Hall , Graham Burkholder , Xuekun Sun , Jeff Crutchfield , Ben Hodgson
CPC classification number: F04D27/001 , F01D5/34 , F01D21/003 , F01D21/045 , F02K3/06 , F04D29/322 , F05D2220/36 , F05D2260/83 , G01M15/14 , Y02T50/671
Abstract: According to one aspect, a method of releasing a fan blade for testing a turbofan engine includes arranging an external shaped charge about an airfoil and modifying the airfoil by extricating one or more portions of material from one or more sides of the airfoil. The method further includes detonating the external shaped charge such that the airfoil is released at a selected time.
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