The invention relates to a sealing device between two annular walls (9, 10) of an aircraft engine, the two walls, respectively radially internal (9) and external (10), being engaged coaxially one in the other, one of said walls (9) comprising annular wipers (20, 21) configured to cooperate with the other of said walls to form a labyrinth seal, characterized in that said wipers comprise a first series of wipers (20 ) and a second series of wipers (21), said series of wipers being axially spaced from each other and said walls (9, 10) defining between them an annular cavity (17), the device further comprising means (24, 25) for detecting the pressure in or around said cavity (17) and means (22) for modifying the pressure in the cavity (17).
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