Pitch change mechanism for open rotor framework

The invention relates to a mechansim for enabling independent pitch control of airfoil blades of contra-rotating rotor assemblies. The mechanism is of particular benefit when applied to 'open rotor' gas turbine engines. The disclosed pitch change mechanism (40) for an open rotor gas turbin...

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Bibliographic Details
Main Author ALEKSANDER KRZYSZTOF SZYMANDERA
Format Patent
LanguageChinese
English
Published 06.03.2013
Subjects
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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Summary:The invention relates to a mechansim for enabling independent pitch control of airfoil blades of contra-rotating rotor assemblies. The mechanism is of particular benefit when applied to 'open rotor' gas turbine engines. The disclosed pitch change mechanism (40) for an open rotor gas turbine engine (10) comprises an engine having a first rotor assembly (20) and a second rotor assembly (30), with a plurality of airfoil blades (21, 31) circumferentially mounted on each rotor assembly and arranged in contra-rotational relationship to each other. The pitch change mechanism includes an actuator assembly (50) adapted to be secured to a non-rotating frame (12) of the engine. The actuator assembly has a first actuator (51) and a second actuator (52) with the actuator assembly being rotationally isolatable from and couplable to the first and second rotor assemblies. An actuation signal from the first or second actuator induces a corresponding desired change in pitch of the airfoil blades of the respective first or seco
Bibliography:Application Number: CN201210304564