Turbine stator for aircraft turbomachine including a vibration damper device

The stator has an abradable element (35) with an annular support (54) arranged at downstream of a wall (46), where the stator includes a lower radial end fixedly connected to a high pressure air injector, and upper radial end of the stator is fixedly connected to the wall. A vibration damping device...

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Bibliographische Detailangaben
Hauptverfasser:	DAKOWSKI, MATHIEU, GANDELOT, SANDRINE, LEFEBVRE, ERIC, JACQUES
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The stator has an abradable element (35) with an annular support (54) arranged at downstream of a wall (46), where the stator includes a lower radial end fixedly connected to a high pressure air injector, and upper radial end of the stator is fixedly connected to the wall. A vibration damping device (74) i.e. vibrating damping annular sheet, is placed in a pressurized cavity (58) and is centered on a longitudinal axis of the stator, where the device contacts with the support and the wall. The device (74) has an end (74a) fixedly mounted on the support and the wall.