Liner for groove of gas turbine engine and method of manufacturing thereof

A liner 118 for use with a gas turbine engine includes a first 120 and a second 130 liner portion. Each has an upstream surface and a downstream surface. The second upstream surface 132 faces the first downstream surface 124. The second downstream surface 134 and first upstream surface 122 at least...

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Bibliographic Details
Main Author Ewan F Thompson
Format Patent
LanguageEnglish
Published 24.01.2024
Subjects
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
COSMONAUTICS
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
PARACHUTES
PERFORMING OPERATIONS
TRANSPORTING
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Summary:A liner 118 for use with a gas turbine engine includes a first 120 and a second 130 liner portion. Each has an upstream surface and a downstream surface. The second upstream surface 132 faces the first downstream surface 124. The second downstream surface 134 and first upstream surface 122 at least partially engage with a surface of the groove. Each liner portion extends circumferentially and radially with respect to a central axis (X-X'). Each liner portion includes a substrate 140 made of a metallic material and a wear resistant coating 142, made of a polymeric material, disposed on the substrate. The wear resistant coating at least forms the first downstream surface and the second upstream surface. Manufacturing the liner comprises providing a sheet metal blank, cutting two sheets from it, and bending the two sheets to obtain bent portions with two opposing surfaces. One of the surfaces of each bent portion is coated in the wear resistant coating to obtain the liner portions. The liner portions can have a 360-degree circumferential extent and can have a hollow frustoconical shape around the central axis.
Bibliography:Application Number: GB20220010496