Turbine engine such as, for example, an airplane turbojet or turboprop engine

The invention relates to a turbine engine provided with an element (3), comprising a wall (11) and at least one load-bearing member (17) extending substantially perpendicularly relative to the wall (11). Said member (17) is to be attached onto a mounting (18) for attachment onto an aircraft structur...

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Bibliographic Details
Main Authors Laurent Donatien Behaghel, Erwan Pierre Antoine Perse, Stéphane Geyl, Yvan Yoann Guezel, Cécile Thieriet
Format Patent
LanguageEnglish
Published 24.05.2017
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
COSMONAUTICS
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
PARACHUTES
PERFORMING OPERATIONS
TRANSPORTING
WEAPONS
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Summary:The invention relates to a turbine engine provided with an element (3), comprising a wall (11) and at least one load-bearing member (17) extending substantially perpendicularly relative to the wall (11). Said member (17) is to be attached onto a mounting (18) for attachment onto an aircraft structural part, where a thermal protection member (23) surrounds said member (17). Said thermal protection member (23) includes a base flexibly supported on the wall (11) of the element (3). Said base closely fits said wall and at least one covering part that surrounds said load-bearing member.
Bibliography:Application Number: GB20170004532