A flow control system on an aircraft engine nacelle (14) incorporates a plurality of translating turning vanes (17a-17e) each having a body. An equal plurality of actuators (30) is coupled to a trailing edge of the body of an associated one of the translating turning vanes (17a-17e). The actuator (30) translates the body from a retracted position to an extended position.
TRANSLATING TURNING VANES FOR A NACELLE INLET
TRANSLATORISCHE UMLENKBLECHE FÜR EINEN GONDELEINLASS
TRANSLATION D'AUBES DIRECTRICES POUR UNE ENTRÉE DE NACELLE
2019-01-02
Patent
Electronic Resource
English