COMPLIANT INTERMEDIATE COMPONENT OF A GAS TURBINE ENGINE

The present application provides an intermediate structure (130) in a gas turbine engine. The intermediate structure is positioned between a first component (120) and another component (110). The first component (120) may be a composite component. The components may be interlocking. The intermediate...

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Bibliographic Details
Main Authors CHAMBERLAIN, ADAM L, USKERT, RICHARD C, THOMAS, DAVID J
Format Patent
LanguageEnglish
French
Published 25.02.2020
Subjects
ARRANGEMENTS OR ADAPTATIONS OF HEATING, COOLING, VENTILATING,OR OTHER AIR-TREATING DEVICES SPECIALLY FOR PASSENGER OR GOODSSPACES OF VEHICLES
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
PERFORMING OPERATIONS
STEAM ENGINES
TRANSPORTING
VEHICLES IN GENERAL
WEAPONS
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Summary:The present application provides an intermediate structure (130) in a gas turbine engine. The intermediate structure is positioned between a first component (120) and another component (110). The first component (120) may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure (130).
Bibliography:Application Number: CA20132897965