SEALING RING ELEMENT FOR A TURBINE COMPRISING AN INCLINED CAVITY IN AN ABRADABLE MATERIAL

The main object of the invention is a sealing ring element (6s) of a turbomachine, comprising a sealing portion (6p) with a first area (6p1) and a second area (6p2), with the inner surface (6i) of a first area (6p1) being at the same radial distance from the axis (X) of the turbomachine, characteris...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	RICOU, Laurent Pierre Joseph, LAMBERT, Olivier Arnaud Fabien, TELMAN, Cyrille
Format:	Patent
Sprache:	eng
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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	The main object of the invention is a sealing ring element (6s) of a turbomachine, comprising a sealing portion (6p) with a first area (6p1) and a second area (6p2), with the inner surface (6i) of a first area (6p1) being at the same radial distance from the axis (X) of the turbomachine, characterised in that the sealing portion (6p) comprises an annular cavity (6c) which opens into an inner surface of the second area (6p2) and extends into the first area (6p1), the annular cavity (6c) defining an upstream lateral wall (6m) and/or a downstream lateral wall (6v) forming an angle (α) which is strictly between 0 and 90°.