Translating sleeve for cascade type thrust reversing system for fan gas turbine engine for an aircraft

A translating sleeve structure for a cascade type thrust reverser for controlling fan air from an aircraft fan gas turbine jet engine, said engine having a bypass fan air duct and a core cowl provided with circumferentially arranged bleed port means for relieving excessive temperature and pressure fluid associated with the engine, which sleeve structure comprises:

• a translating sleeve structure having outer and inner skins that are spaced apart a predetermined distance at their leading edges and which are joined together at a trailing edge of such sleeve structure, said inner skin having circumferentially arranged spaced receptacles provided entirely within said skin for hingedly receiving a blocker door within each such receptacle, said blocker door receptacles being spaced rearwardly from the leading edge of said sleeve structure and aft of said bleed port means provided in the core cowl of the gas turbine engine,
• and a blocker door hingedly positioned within each such receptacle and hingedly connected through a link connection to the core cowl of a gas turbine engine whereby translation of said sleeve structure rotates said blocker doors to a fan air blocking position without possible exposure to excessive temperature and pressure of fluid which may be expelled through said bleed port means.