LINER FOR GROOVE OF GAS TURBINE ENGINE AND METHOD OF MANUFACTURING THEREOF

A liner for use with a gas turbine engine includes a first liner portion including a first upstream surface and a first downstream surface. The liner further includes a second liner portion spaced apart from the first liner portion. The second liner portion includes a second upstream surface and a s...

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Bibliographische Detailangaben
1. Verfasser:	THOMPSON, Ewan F
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVINGMATERIAL PERFORMING OPERATIONS PUNCHING METAL TRANSPORTING WEAPONS WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS ORPROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL
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Beschreibung
Zusammenfassung:	A liner for use with a gas turbine engine includes a first liner portion including a first upstream surface and a first downstream surface. The liner further includes a second liner portion spaced apart from the first liner portion. The second liner portion includes a second upstream surface and a second downstream surface. The second upstream surface faces the first downstream surface. Each of the first liner portion and the second liner portion at least circumferentially and radially extends with respect to a central axis. Each of the first liner portion and the second liner portion includes a substrate made of a metallic material and a wear resistant coating disposed on at least a portion of the substrate. The wear resistant coating is made of a polymeric material. The wear resistant coating at least forms the first downstream surface and the second upstream surface.