TRANSLATING TURNING VANES FOR A NACELLE INLET

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 (3...

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Bibliographische Detailangaben
Hauptverfasser:	HOISINGTON, Zachary C, SEQUEIRA, Kevin J, HOFFMAN, Drew C, CHAPEL, Steven E, PALACIOS, Francisco D, FRAZIER, Romar C, DORSEY, Andrew M
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	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.