Deflector edge for a thrust reverser
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United States of America Patent
Stats
-
Mar 29, 1994
Grant Date -
N/A
app pub date -
Aug 18, 1992
filing date -
Aug 21, 1991
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A thrust reverser for a turbofan-type turbojet engine assembly is disclosed having a deflector defining an upstream edge of a reverse thrust opening formed in the turbofan housing so as to control the direction and shape of the gases passing through the reverse thrust opening. The deflector has a deflector edge portion defining a deflector edge wherein the curvature of the deflector edge portion, as measured in a longitudinal radial plane passing radially through a longitudinal axis of the engine, varies in a direction from one side of the reverse thrust opening to the opposite side of the opening. The curvature of the deflector edge portion is defined as being positive when the center of curvature of the deflector edge portion lies radially outwardly of the deflector and is defined as being negative when the center of curvature of the deflector edge portion lies radially inwardly of the deflector. The deflector edge portion may have a positive curvature adjacent to one side of the reverse thrust opening and a negative curvature adjacent to an opposite side of the reverse thrust opening such that the deflector edge defines a continuous smooth curve from one side of the reverse thrust opening to the other side. The direction and the shape of the gases passing through the reverse thrust opening is controlled by varying the curvature of the deflector edge portion across the reverse thrust opening. The portion of the deflector edge having a positive curve of the smallest radius forms a maximum flow area, while the deflector edge portion having a negative curvature of the smallest radius forms a minimum flow area. Thus, by tailoring the curvature of the deflector edge portion to meet the requirements of a particular engine/aircraft application, the direction and shape of the gases passing through the reverse thrust opening can be controlled so as to minimize contact with the adjacent aircraft structure and to prevent reingestion of the thrust reverse gases into the turbofan engine.
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