CASCADE FOR A THRUST REVERSER COMPRISING BLADED STAGES CONNECTED BY THEIR CELLULAR STRUCTURES

A cascade (22) of vanes for a cascade thrust reverser (19) for an aircraft propulsion assembly nacelle comprises: a first bladed stage (22A) and a second bladed stage (22B), which are superimposed, each comprising rows of vanes (50A, 50B) and of spars (52A, 52B) which cross over one another so as to...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	PAGANO, Fabrizio, ROGNANT, Michel, PIGEON, Julien, MARIE, Nicolas
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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