PROCESS FOR USING AN AIR INPUT OF A TURBOREACTOR NACELLE COMPRISING AN AIR INPUT LIP WHICH COMPRISES A PORTION WHICH CAN BE MOVED TO PROMOTE A THRUST INVERSION PHASE

PROCESS FOR USING AN AIR INPUT OF A TURBOREACTOR NACELLE COMPRISING AN AIR INPUT LIP WHICH COMPRISES A PORTION WHICH CAN BE MOVED TO PROMOTE A THRUST INVERSION PHASE

A process for using an air input of a turboreactor nacelle of an aircraft, comprising an air input lip which comprises at least one fixed portion and at least one portion which can be moved between a first position, in which the air input lip has an aerodynamic profile so as to guide the internal ai...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: SIRVIN, NICOLAS JOSEPH, Mincu, Daniel-Ciprian, WOROTYNSKA, JAGODA ALINA, BINDER, ANTHONY, LALLIA, MATHIEU PATRICK JEAN-LOUIS, DAUTREPPE, FREDERIC, LEBEAULT, EVA JULIE
Format: Patent
Sprache:eng
Schlagworte:
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Beschreibung
Zusammenfassung:A process for using an air input of a turboreactor nacelle of an aircraft, comprising an air input lip which comprises at least one fixed portion and at least one portion which can be moved between a first position, in which the air input lip has an aerodynamic profile so as to guide the internal air flow over the internal wall in order to promote a thrust phase, and a second position, in which the portion is displaced in relation to the fixed portion so that the air input lip has a second radial thickness in the second position which is less than the first radial thickness in the first position so as to promote a reverse thrust phase.