Compressive stress system and method for a gas turbine engine

The present application provides a compressive stress system (100) for a gas turbine engine (10). The compressive stress system (100) may include a first bucket (120) attached to a rotor (180), a second bucket (130) attached to the rotor (180), the first and the second buckets (120, 130) defining a...

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Bibliographic Details
Main Author HOGBERG, NICHOLAS ALVIN
Format Patent
LanguageEnglish
French
German
Published 20.03.2013
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:The present application provides a compressive stress system (100) for a gas turbine engine (10). The compressive stress system (100) may include a first bucket (120) attached to a rotor (180), a second bucket (130) attached to the rotor (180), the first and the second buckets (120, 130) defining a shank pocket (205) therebetween, and a compressive stress spring (210) positioned within the shank pocket (205). A corresponding method of reducing interlaminar stresses in a composite bucket is also provided.
Bibliography:Application Number: EP20120176536