Patent ID: 6170254
Filing Date: 2001-01-09
Classification: B64C,F02K,F05D,Y02T

Abstract:
In a cascade type thrust reversing system for controlling fan air from a fan gas turbine jet engine for an aircraft, said engine having a core cowl that is provided with bleed port means positioned aft of a fixed fan cowl structure, the combination comprising:a forward fixed structure having inner and outer walls positioned immediately aft of the fixed fan cowl structure;a translatable sleeve structure, having inner and outer walls, that is positioned in an abutting position in a stowed position to said forward fixed structure, the inner wall of said sleeve structure being provided with a plurality of circumferentially arranged deployable blocker doors that are horizontally positioned in said inner wall aft of said bleed port means, andtranslating means for translating said translating sleeve structure rearwardly to deploy said blocker doors into abutting contact with the core cowl and thereby block the fan air and redirect it outwardly through an annular space provided between said forward fixed structure and the translated sleeve structure.