GAS TURBINE ENGINE COMPRISING A COMPOSITE COMPONENT AND A METAL COMPONENT WHICH ARE CONNECTED BY A FLEXIBLE FIXING DEVICE

A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connec...

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Bibliographic Details
Main Authors BART JACQUES RENE, BEAUJARD ANTOINE JEAN-PHILIPPE
Format Patent
LanguageEnglish
Published 18.06.2015
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
ENGINE PLANTS IN GENERAL
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
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:A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.
Bibliography:Application Number: US201314410180