公开(公告)号：US10648349B2

公开(公告)日：2020-05-12

申请号：US15915200

申请日：2018-03-08

Applicant: ROLLS-ROYCE plc

Inventor： Andrew Hewitt ,  Ian W R Harrogate

IPC: F01D5/28 ,  F01D9/04 ,  C23C28/00 ,  B22F5/04 ,  C23C4/11 ,  C23C4/02 ,  B33Y80/00 ,  B22F3/105

Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).

公开(公告)号：US20180258776A1

公开(公告)日：2018-09-13

申请号：US15915200

申请日：2018-03-08

Applicant: ROLLS-ROYCE plc

Inventor： Andrew Hewitt ,  Ian W. R. Harrogate

IPC: F01D5/28 ,  F01D9/04 ,  C23C28/00

CPC classification number: F01D5/288 ,  B22F3/1055 ,  B22F5/04 ,  B33Y80/00 ,  C23C4/02 ,  C23C4/11 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  F01D9/041 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2240/12 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/80 ,  F05D2250/294 ,  F05D2300/173 ,  F05D2300/182 ,  F05D2300/2118 ,  F05D2300/611

Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).

公开(公告)号：US10465536B2

公开(公告)日：2019-11-05

申请号：US15136308

申请日：2016-04-22

Applicant: ROLLS-ROYCE plc

Inventor： Andrew Hewitt ,  Matthew Hancock

IPC: F01D5/28 ,  F01D5/20 ,  F01D11/12 ,  F01D5/14

Abstract: A gas turbine engine component includes a rotor blade having a squealer tip comprising a projecting lip, the rotor blade further having a raised rim running along both edges of each projecting kip of the squealer tip, and an abrasive coating formed of hard particles embedded in a retaining matrix covering a tip region of the rotor blade within an area bounded by the raised rim. The raised rim has a height of between 50% and 75% of a mean diameter of the hard particles.

公开(公告)号：US10019808B2

公开(公告)日：2018-07-10

申请号：US15332349

申请日：2016-10-24

Applicant: ROLLS-ROYCE PLC

Inventor： Andrew Hewitt ,  Matthew Hancock

IPC: G06T7/40 ,  G01B11/30 ,  G06T7/00

CPC classification number: G06T7/40 ,  G01B11/30 ,  G06T7/0004 ,  G06T2207/10016 ,  G06T2207/30164

Abstract: A method of inspecting an object, the method comprising: receiving a first image of a first part of a first surface of the object from a camera arrangement; controlling relative movement between the camera arrangement and the object through a predetermined distance; receiving a second image of a second part of the first surface of the object from the camera arrangement, the second part being different to the first part; generating a third image using at least the first image and the second image; and determining a parameter associated with an abrasive surface coating on the object using the third image.