Assembly for a turbomachine

The invention relates to an assembly for a turbomachine, comprising: -a nacelle comprising an inlet lip which defines an air inlet, and-a device for modifying the geometry of the air inlet, comprising: -a first spout, and-a second spout, the first spout and the second spout being translatably movabl...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	Carbonneau, Xavier, Martin Pleguezuelo, Alejandro, Sirvin, Nicolas Joseph, Chanez, Philippe Gérard, Garcia Rosa, Nicolas, Tantot, Nicolas Jérôme Jean
Format:	Patent
Sprache:	eng
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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	The invention relates to an assembly for a turbomachine, comprising: -a nacelle comprising an inlet lip which defines an air inlet, and-a device for modifying the geometry of the air inlet, comprising: -a first spout, and-a second spout, the first spout and the second spout being translatably movable in relation the nacelle between: -a first configuration, in which the first spout forms the inlet lip and the second spout extends inside the nacelle, and-a second configuration, in which the first spout extends away from the inlet lip, and the second spout forms the inlet lip so as to define an air flow channel between a downstream surface of the first spout and an upstream surface of the second spout.