FIELD: engines and pumps.
SUBSTANCE: proposed stator comprises wall and circular support for wearing element intended for contact with labyrinth seal. High-pressure injector is fixed on stator wall and directed in the line of gas flow. Circular support is located downstream of said stator wall and fixed by its radial bottom end on high-pressure injector and, by its top radial end, on stator wall. It is fixed so that circular support stator wall and high-pressure air injector confine pressurised chamber. Turbine stator comprises additionally, at least, one vibration damper located in said pressurised chamber. Said damper stays in contact with each of two elements of the group consisting of stator wall and circular support of wearing element. Invention covers also aircraft gas turbine engine with above described stator and gas turbine engine with said turbine.
EFFECT: ruled out vibrations caused by interaction between turbine rotor and stator.
13 cl, 5 dwg
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