Thrust reverser configuration

In a door thrust reverser for an aircraft turbojet, in which, in the forward thrust mode, a cavity (3) exists between the fan duct line profile (6) and the inner surface (14a) of each door, the invention provides a fixed arched device (4) located in said door cavity (3), roughly concentrically to th...

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Bibliographic Details
Main Authors MEYER, PASCAL JEROME, FRANK, JOEL HUDSON
Format Patent
LanguageEnglish
French
German
Published 30.06.1999
Edition6
Subjects
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS
INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:In a door thrust reverser for an aircraft turbojet, in which, in the forward thrust mode, a cavity (3) exists between the fan duct line profile (6) and the inner surface (14a) of each door, the invention provides a fixed arched device (4) located in said door cavity (3), roughly concentrically to the annular channel (C) for the flow of the gas flux F1, which channel is defined between the outer casing and the engine structure. The arched device (4) is rigidly attached at each end to the structural beams of the casing in such a fashion as to not protrude past the fan duct line (6). In reverse thrust mode the arched device (4) entrains the flow (F1) by virtue of a flow depressurization on its aft side, thereby enhancing the flow discharge and velocity characteristics.
Bibliography:Application Number: EP19970403164