公开(公告)号：US20170175571A1

公开(公告)日：2017-06-22

申请号：US15380134

申请日：2016-12-15

Applicant: ROLLS-ROYCE plc

Inventor： Phillip J. DOORBAR ,  Gareth FRIEND ,  Kenneth F. UDALL

IPC: F01D25/00 ,  B21D11/20 ,  F01D9/02 ,  F01D25/28 ,  B23K20/02 ,  B23K20/22

CPC classification number: F01D25/005 ,  B21D11/203 ,  B22F3/15 ,  B22F5/008 ,  B22F5/106 ,  B22F7/06 ,  B22F7/062 ,  B22F2998/10 ,  B22F2999/00 ,  B23K20/023 ,  B23K20/22 ,  B23K2101/001 ,  B23K2103/166 ,  C22C32/00 ,  C22C32/0031 ,  C22C47/20 ,  C22C49/11 ,  F01D9/02 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/42 ,  F05D2300/6032 ,  F16C7/02

Abstract: Method of manufacturing a metal matrix composite component includes the steps of providing a first tubular member having a first end and an opposite second end, the first tubular member's first end being formed as a first end block; positioning a metal matrix composite tubular member concentrically the first tubular member; positioning a second tubular member concentrically over metal matrix composite tubular member, second tubular member having a first end and an opposite second end, the second tubular member's second end being formed as a second end block; welding first tubular member's first end to the second tubular member's first end, and the first tubular member's second end to second tubular member's second end, to join the first and second tubular member and thereby to form a metal matrix composite preform; and consolidating metal matrix composite preform by a hot isostatic pressing process to form the metal matrix composite component.

公开(公告)号：US20170175763A1

公开(公告)日：2017-06-22

申请号：US15371700

申请日：2016-12-07

Applicant: ROLLS-ROYCE plc

Inventor： Phillip J. DOORBAR

IPC: F04D29/34 ,  F04D29/38 ,  F04D29/32

CPC classification number: F04D29/34 ,  F01D5/147 ,  F01D5/3007 ,  F02K3/06 ,  F04D29/023 ,  F04D29/322 ,  F04D29/329 ,  F04D29/388 ,  F05D2220/36 ,  F05D2230/232 ,  F05D2230/236 ,  F05D2300/174

Abstract: A fan blade root block assembly includes a fan blade, and a cheek piece. The fan blade includes a first root portion having a first root portion end, and a second root portion having a second root portion end. The first root portion is aligned side by side with the second root portion, and the cheek piece is attached to each of the first root portion end and the second root portion end.

公开(公告)号：US20180016938A1

公开(公告)日：2018-01-18

申请号：US15625523

申请日：2017-06-16

Applicant: ROLLS-ROYCE plc

Inventor： Phillip J. DOORBAR ,  Jason J. MADGE

IPC: F01D25/00 ,  F01D15/12 ,  F01D5/06 ,  F16H1/28 ,  F16H57/08 ,  F01D15/08 ,  F01D25/16

CPC classification number: F01D25/005 ,  F01D5/06 ,  F01D15/08 ,  F01D15/12 ,  F01D25/16 ,  F02C7/36 ,  F05D2220/32 ,  F05D2260/40311 ,  F05D2300/171 ,  F05D2300/174 ,  F05D2300/2261 ,  F05D2300/2282 ,  F05D2300/2283 ,  F05D2300/6032 ,  F16H1/28 ,  F16H57/08 ,  F16H57/082 ,  Y02T50/672

Abstract: A gas turbine engine comprises a gearbox comprises a sun gear, an annulus gear, a plurality of planet gears and a carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. The planet gear carrier comprising a first ring, a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring. Each planet gear is rotatably mounted on a respective one of the axles and the axles are arranged at a first radius. At least one of the first ring and the second ring comprises a metal matrix composite material ring and the metal matrix composite ring comprises a ring of reinforcing fibres and the ring of reinforcing fibres having a second radius greater than the first radius.

公开(公告)号：US20180003063A1

公开(公告)日：2018-01-04

申请号：US15635869

申请日：2017-06-28

Applicant: ROLLS-ROYCE plc

Inventor： Phillip J. DOORBAR

IPC: F01D5/26 ,  B22F7/08 ,  F01D5/28 ,  F04D29/66 ,  B22F3/10 ,  F04D29/38 ,  B23K20/10

CPC classification number: F01D5/26 ,  B22F3/10 ,  B22F5/04 ,  B22F7/08 ,  B23K20/10 ,  B23P6/002 ,  F01D5/005 ,  F01D5/16 ,  F01D5/28 ,  F04D29/083 ,  F04D29/324 ,  F04D29/388 ,  F04D29/668 ,  F05D2220/32 ,  F05D2230/233 ,  F05D2230/234 ,  F05D2230/31

Abstract: A method of sealing one or more openings provided in a wall of an aerofoil for a gas turbine engine, the aerofoil comprising at least one cavity which is at least partly filled with a vibration damping material, the method comprising steps to provide a metallic material onto the wall of the aerofoil in order to cover the opening and bond the metallic material to the wall of the aerofoil to seal the opening.