公开(公告)号：US20170051615A1

公开(公告)日：2017-02-23

申请号：US15219904

申请日：2016-07-26

Applicant: ROLLS-ROYCE plc

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

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

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20180230843A1

公开(公告)日：2018-08-16

申请号：US15874058

申请日：2018-01-18

Applicant: ROLLS-ROYCE plc

Inventor： Gary J. WRIGHT ,  Simon DONOVAN

IPC: F01D11/12 ,  F01D25/12

CPC classification number: F01D11/125 ,  B22F3/1055 ,  B22F5/009 ,  B22F2005/005 ,  B22F2999/00 ,  B23K26/342 ,  B33Y10/00 ,  B33Y30/00 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/234 ,  F05D2230/31 ,  F05D2240/11 ,  F05D2250/711 ,  F05D2260/201 ,  B22F5/10

Abstract: An abradable sealing element is positioned radially outwardly of a plurality of aerofoil blades of a gas turbine engine. The abradable sealing element comprises a radially inwardly facing surface region and a plurality of cooling holes.The radially inwardly facing surface region comprises a wall structure, with the wall structure having one or more radially inwardly projecting walls formed by additive layer, powder fed, laser weld deposition.Each of the inwardly projecting walls is continuous and defines a plurality of repeating units arranged circumferentially around the radially inwardly facing surface region, each repeating unit is open at a radially inwardly facing side of the sealing element, and each repeating unit comprises a plurality of curved portions forming a multi-lobed profile shape. Each cooling hole is provided in the radially inwardly facing surface region at a position within the multi-lobed profile shape.