THRUST RECOVERY OUTFLOW VALVES FOR USE WITH AIRCRAFT

Thrust recovery outflow valves (200) for aircraft are disclosed. An example thrust recovery outflow valve (200) includes a flow control member (216) having a first aerodynamic surface (230) and a second aerodynamic surface (246) to define at least a portion of a fluid flow passageway between an inle...

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Bibliographic Details
Main Authors FERRAIOLO, Nicholas R, TRETOW, Paul R, WILLIE, Robert H
Format Patent
LanguageEnglish
French
German
Published 17.11.2021
Subjects
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
COSMONAUTICS
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
PARACHUTES
PERFORMING OPERATIONS
TRANSPORTING
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Summary:Thrust recovery outflow valves (200) for aircraft are disclosed. An example thrust recovery outflow valve (200) includes a flow control member (216) having a first aerodynamic surface (230) and a second aerodynamic surface (246) to define at least a portion of a fluid flow passageway between an inlet (204) and an outlet (208) of the thrust recovery outflow valve (200). A first portion (422) of the first aerodynamic surface (230) and a first portion (434) of the second aerodynamic surface (246) provides a converging profile between the inlet (204) and a throat (408) of the fluid flow passageway. A second portion of the first aerodynamic surface (230) and a second portion of the second aerodynamic surface (246) provides a diverging profile between the throat (408) and the outlet (208) of the fluid flow passageway. The fluid flow passageway is positioned at a small angle relative to an outer surface (412) of an aircraft to enable fluid exiting the fluid flow passageway to provide a thrust recovery vector (416) oriented substantially parallel to the outer surface (412) of the aircraft and opposite a direction of drag.
Bibliography:Application Number: EP20170151054