MULTI-STAGE CO-ROTATING VARIABLE PITCH FAN

A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk, defining a first stage and a second stage of fan blades. The fan disk is adapted for rotation about a central axis. The blades of both stages have an adjustable pitch angle...

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Bibliographische Detailangaben
1. Verfasser:	FULAYTER, ROY D
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS ENGINE PLANTS IN GENERAL HEATING HELICOPTERS 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 PERFORMING OPERATIONS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk, defining a first stage and a second stage of fan blades. The fan disk is adapted for rotation about a central axis. The blades of both stages have an adjustable pitch angle which can be varied from positive pitch angle, associated to forward thrust, to negative pitch angle, associated to reverse thrust. Each of the first and second stage of blades have preferably a solidity ratio of less than 1.