GAS TURBINE ENGINE

GAS TURBINE ENGINE

A gas turbine engine for an aircraft is provided comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core and driven by the turbine, the fan comprising a circumferential row of tandem fan b...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: Baralon, Stephane, Phelps, Benedict
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
COMBUSTION ENGINES
ENGINE PLANTS IN GENERAL
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
NON-POSITIVE DISPLACEMENT PUMPS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
STEAM ENGINES
WEAPONS
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Beschreibung
Zusammenfassung:A gas turbine engine for an aircraft is provided comprising: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; and a fan located upstream of the engine core and driven by the turbine, the fan comprising a circumferential row of tandem fan blades. Each of the tandem fan blades comprises a main fan blade and an auxiliary fan blade positioned at the rear of the main fan blade, such that, over substantially all of the auxiliary fan blade's radial span, the leading edge of the auxiliary fan blade is rearwards of the closest point on the trailing edge of the main fan blade, and on a given aerofoil chordal section of the main fan blade, the leading edge position of an aerofoil chordal section of the auxiliary fan blade lies on a rearwards extension of the camber line of the aerofoil chordal section of the main fan blade, and the main fan blade and the auxiliary fan blade are arranged to rotate in tandem. The auxiliary fan blade is movable within a range of pitch angles relative to the main fan blade.