Turbomachine with a deflector system

A turbomachine front portion comprising an internal support shroud for fan outlet guide vanes of a fan, and a flow splitter fairing from which an annular primary duct and an annular secondary duct of the turbomachine originate, wherein said front portion additionally comprises at least one deflector system configured to prevent or limit the ingress of foreign bodies inside said primary duct of the turbomachine, said deflector system comprising at least one movable deflecting surface together with an actuator configured to move said deflecting surface from a retracted position to a deployed position for deflecting the foreign bodies and to move said deflecting surface from said deployed position back to said retracted position, said deflector system being mounted on said internal support shroud such that, in the deployed position, a downstream end of each deflecting surface is situated upstream of said flow splitter fairing, wherein said actuator and said deflecting surface are formed by one and the same element made of shape memory alloy, said turbomachine front portion comprising a plurality of foreign body deflector systems spaced angularly from one another about a longitudinal axis of the turbomachine.

A turbomachine front portion comprising an internal support shroud for fan outlet guide vanes of a fan, and a flow splitter fairing from which an annular primary duct and an annular secondary duct of the turbomachine originate, wherein said front portion additionally comprises at least one deflector system configured to prevent or limit the ingress of foreign bodies inside said primary duct of the turbomachine, said deflector system comprising at least one movable deflecting surface together with an actuator configured to move said deflecting surface from a retracted position to a deployed position for deflecting the foreign bodies and to move said deflecting surface from said deployed position back to said retracted position, said deflector system being mounted on said internal support shroud such that, in the deployed position, a downstream end of each deflecting surface is situated upstream of said flow splitter fairing, wherein said deflector system comprises elastic return means for returning said deflecting surface into said retracted position, and wherein said elastic return means include an elastic strip coupled mechanically to and superposed on a deflecting strip, said turbomachine front portion comprising a plurality of foreign body deflector systems spaced angularly from one another about a longitudinal axis of the turbomachine.

A deflector system mounted on an internal support shroud of fan outlet guide vanes of a turbomachine front portion, the deflector system situated upstream from a flow splitter fairing from which an annular primary duct and an annular secondary duct of the turbomachine originate, said deflector system comprising at least one movable deflecting surface together with an actuator configured to move said deflecting surface from a retracted position to a deployed position, wherein said actuator is made of shape memory alloy such that when said actuator reaches a given transition temperature, said shape memory alloy adopts its memorized shape and said deflecting surface moves in the deployed position, and wherein said deflector system additionally comprises elastic return for returning said deflecting surface into said retracted position after said actuator has a temperature below said given transition temperature, where said elastic return means include an elastic strip coupled mechanically to and superposed on a deflecting strip, and wherein in the deployed position, said deflecting surface takes the form, in longitudinal section, of a curved line which opens in the upstream direction and radially toward the outside of the turbomachine.