Patent ID: 8133010

Claim:
A turbine stator for an aircraft turbine engine, comprising: a stator wall supporting a high pressure air injector fixed on the downstream side; an annular abradable element support designed to be contacted by a sealing labyrinth, the lower radial end of said support arranged on the downstream side of said stator wall being fixed to said high pressure air injector and its upper radial end being fixed to said stator wall, such that said annular support, said stator wall and said high pressure air injector jointly delimit a cavity under pressure, at least one vibration damping device located in said cavity under pressure, said vibration damping device being in contact with each of the two elements taken among said stator wall and said abradable annular element support, wherein said vibration damping device is in the form of a plate located in said cavity under pressure and with a first end fixed onto one of the two elements among said stator wall and said annular abradable element support, and a second free end, held in contact with the other of said two elements.