公开(公告)号：US09771807B2

公开(公告)日：2017-09-26

申请号：US14473425

申请日：2014-08-29

Applicant: ROLLS-ROYCE PLC

Inventor： Steven Aleksy Radomski

IPC: F01D5/18 ,  B23P15/04 ,  B23K13/01 ,  B23K20/00 ,  B23K20/02 ,  B23K20/16 ,  F01D5/14 ,  B23K101/00

CPC classification number: F01D5/18 ,  B23K13/01 ,  B23K20/002 ,  B23K20/02 ,  B23K20/16 ,  B23K2101/001 ,  B23P15/04 ,  F01D5/147 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/236 ,  F05D2230/51 ,  F05D2230/60 ,  F05D2230/90 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49337

Abstract: A method of manufacturing a hollow aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a mandrel (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. Remotely detectable elements (700) may be provided to the mandrel (400) to enable the location of the pocket (310) to be accurately determined from outside the aerofoil (100).

公开(公告)号：US09879545B2

公开(公告)日：2018-01-30

申请号：US14158014

申请日：2014-01-17

Applicant: ROLLS-ROYCE PLC

Inventor： Steven Aleksy Radomski ,  Clive Grafton-Reed ,  Ian Crowston ,  Andrea Lelio Maurizio

IPC: F01D5/18 ,  B23P15/04 ,  F01D5/14

CPC classification number: F01D5/18 ,  B23P15/04 ,  F01D5/147 ,  Y02T50/672 ,  Y10T29/49339

Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body. This ensures that the outer surface of the capping panel is located as accurately as possible. This means that the capping panel can be made to be as thin as possible, which in turn reduces weight and material wastage. Once the capping panel has been located in position, it may be welded to the aerofoil body in order to produce the hollow aerofoil component.

公开(公告)号：US09855628B2

公开(公告)日：2018-01-02

申请号：US14474944

申请日：2014-09-02

Applicant: ROLLS-ROYCE PLC

Inventor： Steven Aleksy Radomski

IPC: B23P15/04 ,  F01D5/14 ,  F01D5/18

CPC classification number: B23P15/04 ,  F01D5/147 ,  F01D5/18 ,  F05D2230/232 ,  F05D2230/60 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49336

Abstract: A method of manufacturing a filled aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a pre-formed filler insert (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. The pre-formed filler insert (400) provides a lightweight core for the finished aerofoil component in use.

公开(公告)号：US09777599B2

公开(公告)日：2017-10-03

申请号：US14505956

申请日：2014-10-03

Applicant: ROLLS-ROYCE PLC

Inventor： Steven Aleksy Radomski ,  Simon Read

IPC: F01D25/24 ,  F01D21/04 ,  F01D11/12 ,  F02C7/04 ,  F04D19/00 ,  F04D29/02

CPC classification number: F01D25/24 ,  F01D11/122 ,  F01D21/045 ,  F02C7/04 ,  F04D19/002 ,  F04D29/023 ,  F05D2220/36 ,  F05D2250/25 ,  F05D2300/522 ,  F05D2300/615 ,  Y10T29/49245

Abstract: A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.