Intermediate casing extension of improved design

The invention relates to an extension (30) of an intermediate frame for an aircraft turbine engine, that will project downstream from an outer ring of the intermediate frame, this extension comprising a downstream annular connecting part (64) preferably forming an annular groove (66) open radially o...

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Bibliographische Detailangaben
Hauptverfasser:	Demoulin Alexandre Christophe Adrien, Dubois Margaux Justine Emma
Format:	Patent
Sprache:	eng
Schlagworte:	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 ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to an extension (30) of an intermediate frame for an aircraft turbine engine, that will project downstream from an outer ring of the intermediate frame, this extension comprising a downstream annular connecting part (64) preferably forming an annular groove (66) open radially outwards, into which the nacelle cowls will fit (38), the end (64) comprising at least one first angular sector (76b). According to the invention, the extension comprises a body (77) made from a single piece comprising a junction ring (74) and at least one second angular sector (76a) of said downstream annular connecting part (64), the first angular sector being added onto the extension body (77).