COMPOSITE AEROFOIL STRUCTURE WITH A CUTTING EDGE TIP PORTION

An aerofoil structure (26) for a gas turbine engine (10), the aerofoil structure comprising a carbon composite aerofoil portion (38) and a tip portion (48), wherein the tip portion comprises a tip surface (60) configured to face a corresponding casing structure (30), the tip portion further comprisi...

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Bibliographic Details
Main Author MERRIMAN, Nicholas Michael
Format Patent
LanguageEnglish
French
German
Published 01.05.2019
Subjects
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Summary:An aerofoil structure (26) for a gas turbine engine (10), the aerofoil structure comprising a carbon composite aerofoil portion (38) and a tip portion (48), wherein the tip portion comprises a tip surface (60) configured to face a corresponding casing structure (30), the tip portion further comprising a ridge line (62) extending along at least a portion of the tip surface, wherein the tip surface comprises a first surface (64) and a second surface (66) provided either side of the ridge line, the ridge line being defined by the intersection of the first and second surfaces, wherein the ridge line is configured to cut into the casing structure during an interaction between the aerofoil structure and casing structure.
Bibliography:Application Number: EP20130812035