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.
ВЫПУСКНЫЕ КЛАПАНЫ ВОССТАНОВЛЕНИЯ ТЯГИ ДЛЯ ИСПОЛЬЗОВАНИЯ С ЛЕТАТЕЛЬНЫМ АППАРАТОМ
2018-07-17
Patent
Electronic Resource
Russian
IPC: | B64C AEROPLANES , Flugzeuge |
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