AIRCRAFT TURBINE ENGINE

Aircraft turbine engine (10) comprising: - two coaxial annular walls defining between them a main annular duct (16) for the flow of a primary airflow (18); - a rotor blading (30) extending radially through the first duct (16); - an annular separator (24) arranged downstream of the rotor blading (30)...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	SOULAT, Laurent, SCHVALLINGER, Michaël Franck Antoine, SECONDAT DE MONTESQUIEU, Antoine Claude Baudouin, MARTINEZ LUQUE, Raul, GUEGAN, Damien Bernard Emeric
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	Aircraft turbine engine (10) comprising: - two coaxial annular walls defining between them a main annular duct (16) for the flow of a primary airflow (18); - a rotor blading (30) extending radially through the first duct (16); - an annular separator (24) arranged downstream of the rotor blading (30) and configured to divide the primary airflow (18) into two to form the secondary air flows (20, 22); - first variable guide vanes (40) which are distributed around the shaft and each comprise a leading edge (40a) which is located upstream of the separator (24) and trailing edges (40b, 40c) which are located in the secondary airflows (20, 22); - and fixed guide vanes (42) which are distributed around the shaft in the external airflow and downstream of the first variable vanes (40).