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    COOLANT CHANNEL
    1.
    发明申请
    COOLANT CHANNEL 审中-公开

    公开(公告)号：US20200284153A1

    公开(公告)日：2020-09-10

    申请号：US16797011

    申请日：2020-02-21

    申请人： ROLLS-ROYCE plc

    发明人： Adrian L. HARDING

    IPC分类号： F01D5/18

    摘要： A component for a gas turbine engine, comprising: first and second walls; a coolant channel defined by the space between the first and second walls; and a first rib extending between the first and second walls to the end of the coolant channel in a coolant flow direction, such that the coolant channel is bifurcated in the coolant flow direction.

    COOLANT AIRFLOW ASSEMBLY PARTICULATE FILTER WITH PANELS IN SERIES
    2.
    发明申请
    COOLANT AIRFLOW ASSEMBLY PARTICULATE FILTER WITH PANELS IN SERIES 审中-公开

    公开(公告)号：US20190292925A1

    公开(公告)日：2019-09-26

    申请号：US16284107

    申请日：2019-02-25

    申请人： ROLLS-ROYCE plc

    发明人： Salwan D. SADDAWI ,  Adrian L. HARDING

    IPC分类号： F01D9/06 ,  F01D5/18 ,  F01D25/12

    摘要： The present disclosure concerns removal of entrained contaminant particles in a coolant airflow for a gas turbine engine. Example embodiments include a coolant airflow assembly for a gas turbine engine, comprising: a coolant feed passage connected between a supply of coolant air and an inlet of a component to be cooled, the coolant feed passage defining a coolant airflow path and comprising first and second opposing internal faces (305, 306), the inlet of the component connected to the coolant airflow path through one of the first and second internal faces (305, 306) of the coolant feed passage; and a particulate filter for removing entrained particles from the coolant airflow path, comprising: a first filter panel extending from the first face into the coolant airflow path upstream of the inlet of the component; and a second filter panel extending from the second face into the coolant airflow path upstream of the first filter panel.

    VANE ASSEMBLY
    3.
    发明申请
    VANE ASSEMBLY 有权

    公开(公告)号：US20210123353A1

    公开(公告)日：2021-04-29

    申请号：US17061815

    申请日：2020-10-02

    申请人： ROLLS-ROYCE plc

    发明人： Adrian L. HARDING

    IPC分类号： F01D9/04 ,  F01D25/12

    摘要： A vane assembly includes an aerofoil having a leading edge, a trailing edge, and a pressure surface and a suction surface defined between the leading edge and the trailing edge. The aerofoil includes a blade member forming the trailing edge, at least a portion of the pressure surface and at least a portion of the suction surface. The blade member is formed of a first material. The aerofoil further includes a spar at least partly enclosed by the blade member and forming at least a portion of the leading edge. The spar further forms at least one cooling channel and supports at least a portion of an interior surface of the blade member. The spar is formed of a second material different from the first material. The second material has a greater impact resistance than the first material.

    AEROFOIL
    4.
    发明申请
    AEROFOIL 审中-公开

    公开(公告)号：US20190186274A1

    公开(公告)日：2019-06-20

    申请号：US16191663

    申请日：2018-11-15

    申请人： ROLLS-ROYCE plc

    发明人： Adrian L. HARDING

    IPC分类号： F01D5/18 ,  B23P15/04

    CPC分类号： F01D5/187 ,  B23P15/04 ,  F01D5/147 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2230/237 ,  F05D2240/301 ,  F05D2260/20 ,  F05D2260/204

    摘要： Aerofoil including: a body comprising first body portion and second body portion bonded to first body portion, first and second body portions having outer faces forming an outer surface of the aerofoil, and inner faces opposing the outer faces; a channel formed within the aerofoil by the inner faces of the first body portion and the second body portion; and a dividing sheet provided within the channel, such that a cooling passage is formed between the dividing sheet and the inner face of at least one of the first body portion and second body portion, cooling passage arranged to conduct cooling fluid adjacent the body, for cooling the body; wherein the body has a rear face and an opposing front face; and the dividing sheet extends parallel to at least a portion of a rear face of the body, such that the cooling passage formed parallel to the rear face.

    CHANNEL CLOSURE
    5.
    发明申请
    CHANNEL CLOSURE 审中-公开

    公开(公告)号：US20190070660A1

    公开(公告)日：2019-03-07

    申请号：US16112910

    申请日：2018-08-27

    申请人： ROLLS-ROYCE plc

    发明人： Adrian L. HARDING ,  David J. HUNT

    IPC分类号： B22D19/00 ,  F01D5/18 ,  B23P21/00

    摘要： A method of bi-casting a first component (10) to a second component (11), wherein the first component comprises a channel (13) having an opening at a surface of the component, the method comprising inserting a pin (12) into the channel (13) to a closure position to block a cross-section of said channel, positioning the first and second components to be adjacent such that at least one space is defined between the first and second components, pouring liquid bi-cast metal (15) into the at least one space between the first component and the second component such that the first component is joined to the second component by the bi-cast metal and the pin is secured in the closure position.

    GAS TURBINE ENGINE
    6.
    发明申请
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20180087395A1

    公开(公告)日：2018-03-29

    申请号：US15714082

    申请日：2017-09-25

    申请人： ROLLS-ROYCE plc

    发明人： Adrian L. HARDING

    IPC分类号： F01D11/22 ,  F01D9/04 ,  F01D17/16 ,  F01D25/24

    CPC分类号： F01D11/22 ,  F01D9/041 ,  F01D9/042 ,  F01D11/16 ,  F01D17/16 ,  F01D25/24 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/50

    摘要： A gas turbine engine comprising a rotor blade, an inner casing and an outer casing, a guide vane, located upstream of the rotor blade and between the inner and outer casing, the guide vane comprising a vane contact member, wherein the guide vane is configured to pivot upon axial displacement of the inner casing relative to either or both of the outer casing and the rotor blade; and, a seal segment located radially outwardly of the rotor blade and mounted for radial displacement relative to the rotor blade; wherein at least a portion of the seal segment axially overlaps, and slidably engages a downstream end of the guide vane so that a pivoting of the guide vane causes the vane contact member to undergo a radially outward displacement which causes a radially outward displacement of at least a portion of the seal segment.

    METHODS, APPARATUS, COMPUTER PROGRAMS, AND NON-TRANSITORY COMPUTER READABLE STORAGE MEDIUMS FOR REPAIRING AEROFOILS OF GAS TURBINE ENGINES
    7.
    发明申请
    METHODS, APPARATUS, COMPUTER PROGRAMS, AND NON-TRANSITORY COMPUTER READABLE STORAGE MEDIUMS FOR REPAIRING AEROFOILS OF GAS TURBINE ENGINES 审中-公开
    方法，装置，计算机程序，以及用于修理气体涡轮发动机的空气的非离子计算机可读存储介质

    公开(公告)号：US20170051615A1

    公开(公告)日：2017-02-23

    申请号：US15219904

    申请日：2016-07-26

    申请人： ROLLS-ROYCE plc

    发明人： Mark FOULKES ,  Adrian L. HARDING ,  David L. TUCKER ,  Gary J. WRIGHT

    IPC分类号： F01D5/28 ,  F01D25/00 ,  F01D9/04

    摘要： Methods, apparatus, computer programs, and non-transitory computer readable storage mediums for repairing an aerofoil of a gas turbine engineA method of repairing an aerofoil of a gas turbine engine, the method comprising: controlling machining of at least one of: a first aerofoil and a second aerofoil; the machining causing an increase in a throat area defined by the first aerofoil, the second aerofoil, a first platform and a second platform, the first aerofoil and the second aerofoil being arranged to couple to the first platform and to the second platform; and controlling provision of a coating to at least one of the first platform and the second platform subsequent to controlling machining to reduce the throat area.

    摘要翻译： 一种修复燃气涡轮发动机的机翼的方法，所述方法包括：控制第一机翼和第二机翼中的至少一个的机械加工; 所述加工导致由所述第一机翼，所述第二机翼，第一平台和第二平台限定的喉部区域的增加，所述第一机翼和所述第二机翼被布置成联接到所述第一平台和所述第二平台; 以及在控制加工以减少所述喉部区域之后，控制向所述第一平台和所述第二平台中的至少一个提供涂层。