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AssigneeSafran Nacelles
InventorsNicolas Pierre Denis MARIE, Laurent Georges VALLEROY, Vincent Jean-François PEYRON, Pierre Charles CARUEL
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The invention relates to a thrust reverser (30) for an aircraft propulsion assembly, comprising a stationary structure (31) equipped with a radially inner wall (18) delimiting a secondary flow path (21B) through which a secondary flow (20B) passes, and a movable structure (29) comprising at least one movable reverser cowl (33) having a cavity (54) delimited between a radially outer wall (50) and a radially inner wall (52) of the movable reverser cowl (33), the movable structure being translatable relative to the stationary structure along a longitudinal central axis (Al) of the reverser, between a forward direct thrust position and a retracted thrust reversal position. The reverser also comprises a controlled system (72) for moving the movable cowl (33) towards the rear, by injecting air from the secondary flow (20B) through the radially inner wall (52) of the movable reverser cowl into the cavity (54).
Thrust reverser (30) for an aircraft propulsion system, the reverser comprising a fixed structure (31) equipped with a radially inner delimiting wall (18) of a secondary flow path (21B) of the propulsion system intended to be traversed by a secondary flow (20B), the reverser also comprising a movable structure (29) comprising at least one movable reverser cover (33) having a cavity (54) delimited between a radially outer wall (50) and a radially inner wall (52) of the movable reverser cover (33), the radially inner wall (52) forming a radially outer delimiting wall of the secondary flow path (21B), the movable structure being movable in translation with respect to the fixed structure along a central longitudinal axis (A1) of the reverser, between an forward direct thrust position a reverse thrust position,
Thrust reverser according to any one of the preceding claims, characterized in that in the retracted reverse thrust position of the movable structure (29), the fixed structure (31) of the reverser and an upstream end (52a) of the radially retracted inner wall (52) of the movable reverser cover allow a passage opening (56) for air to appear between them through the secondary flow path (21B), the thrust reverser also comprising sealing means (84) of the secondary flow path, designed to divert at least a portion of the secondary flow (20B) toward the passage opening (56), and in that the closing part is a closing flap (84) of the secondary flow path (21B), belonging to said closing means, or in that the closing part is an interflap part (86) for reconstituting the secondary flow path (21B), arranged circumferentially between two closing flaps (84) of said closing means.
Thrust reverser according to any one of the preceding claims, characterized in that the fixed structure (31) of the reverser comprises at least one deflection grid (32) arranged, in the advanced position of direct thrust of the movable structure, in the cavity (54) of the movable cover, being isolated from the secondary flow path by the radially inner wall (52) of the reverser cover (33).
Thrust reverser according to any one of the preceding claims, characterized in that it also includes a device (92) for damping the opening travel limit of the movable cover (33), in its movement from the forward direct thrust position to the rearward reverse thrust position.
Aircraft propulsion system (1), comprising a turbomachine (2) and a nacelle (3) comprising at least one fan cowling (14), as well as a thrust reverser (30) according to any one of the preceding claims.
Dependencies are inferred from the claim text.