Method and device for reversing the thrust of very high bypass ratio turbojet engines
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorAlain Lardellier
Life of this patent
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Abstract
A high bypass ratio turbojet engine comprising a fan rotated by the shaft of a low pressure turbine via a speed reducer is provided with a thrust reverser device by providing the speed reducer with first and second epicyclic gear trains which are mounted in parallel between the low pressure turbine and the fan and which are arranged in such a way as to drive the fan in a first direction of rotation when the engine is operated in a direct thrust mode, and to drive the fan in the opposite direction of rotation when the engine is to be operated in the reverse thrust mode.
Claims8
A thrust reverser device for a high bypass ratio turbojet engine having a fan, a low pressure turbine, and a speed reducer through which said fan is rotated by a shaft of said low pressure turbine, said thrust reverser device being realised by providing said speed reducer with first and second epicyclic gear trains mounted in parallel between said low pressure turbine and said fan in such a way that said fan is driven in a first direction of rotation in a first operating mode, called the direct mode, and said fan is driven in a second direction of rotation opposite to said first direction during a second operating mode, called the reverse mode, so as to reverse the thrust of the engine.
Dependencies are inferred from the claim text.