US 6,438,942 B2Granted

Cascade-type reversers for jet engines

AssigneeSociete de Construction des Avions Hurel-Dubois (Societe Anonyme)

InventorsAlain Fournier, Bernard Laboure, Robert R. Standish

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Abstract

The cascade-type thrust reverser comprises a cowling in which there is formed an opening which, when in a direct thrust mode, is closed by a sliding cowl and which, in a thrust-reversal mode, is uncovered by the translation of the said sliding cowl, a fan duct being defined between an interior skin and an exterior skin, said exterior skin having a radius Re in the plane transversal to the longitudinal axis of the reverser and passing through the upstream end of the sliding cowl in the direct thrust mode, and said interior skin having, downstream of this upstream plane, a maximum radius Ri in a plane parallel to the upstream plane, the upstream end of the said sliding cowl substantially blocking the fan duct upstream of the said downstream plane in a thrust-reversal mode, the said radius Re being less than the radius Ri.

Claims7

Dependent claims

A thrust reverser for a jet engine, comprising:

a cowling (27) having a fan duct (10) that is defined between an interior skin (21) and an exterior skin (9);
a sliding cowl (3′) that moves downstream in translation, relative to a direction of flow of gases through the jet engine, to uncover an opening in said cowling in a thrust-reversal mode and that has an interior surface (5i) that is a part of said exterior skin of said fan duct in a direct thrust mode;
said sliding cowl having an upstream end (23′) that has a minimum radius (Re) relative to a longitudinal axis of the jet engine at a first plane (P′1) transverse to the longitudinal axis of the jet engine;
said interior skin of said fan duct having a maximum radius (Ri) relative to the longitudinal axis of the jet engine at a second plane (P2) that is downstream of said first plane and parallel thereto;
said upstream end of said sliding cowl substantially blocking said fan duct upstream of said second plane when said sliding cowl has been moved downstream in the thrust-reversal mode;
said minimum radius being less than said maximum radius;
said cowling comprising two roughly symmetrical cowling parts relative to a longitudinal section plane, each of said cowling parts having a first track (28) approximately in said longitudinal section plane and that extends upstream and downstream of said second plane, each of said cowling parts also having a pair of second tracks (29, 30) opposite said first track and that extend upstream of said second plane;
and
said sliding cowl comprising two roughly symmetrical halves relative to the longitudinal section plane that are each movably mounted on a respective one of said cowling parts, each said sliding cowl half having a first rail (32) that is rotatable in and movable longitudinally along said first track, each said sliding cowl half also having a pair of second rails (33, 34) that are movable longitudinally along respective ones of said second tracks, wherein each said sliding cowl half is movable downstream on said first track to a location where said second rails are free of said second tracks and is then rotatable about said first track.

6 more elements

A thrust reverser for a jet engine, comprising:

a fan duct (10) that is defined between an interior skin (21) and an exterior skin (9);
a sliding cowl (3′) that moves downstream in translation, relative to a direction of flow of gases through the jet engine, to uncover an opening in a thrust-reversal mode and that has an interior surface (5i) that is a part of said exterior skin of said fan duct in a direct thrust mode;
said sliding cowl having an upstream end (23′b) to which is removably attached a base plate (11′) that extends upstream and that is incorporated into said exterior skin, said base plate having an upstream extension (23′a) that has a first minimum radius (Re1) relative to a longitudinal axis of the jet engine at a first plane (P′1) transverse to the longitudinal axis of the jet engine, said upstream end having a second minimum radius (Re2) relative to a longitudinal axis of the jet engine;
said interior skin of said fan duct having a maximum radius (Ri) relative to the longitudinal axis of the jet engine at a second plane (P2) that is downstream of said first plane and parallel thereto;
said upstream end of said sliding cowl substantially blocking said fan duct upstream of said second plane when said sliding cowl has been moved downstream in the thrust-reversal mode;
and
said first minimum radius being less than said maximum radius and said second minimum radius being greater than said maximum radius.

4 more elements

Dependencies are inferred from the claim text.