A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.
ARRANGEMENT D'ETANCHEITE ENTRE DEUX PAROIS ANNULAIRES D'UN MOTEUR D'AERONEF
SEALING ARRANGEMENT BETWEEN TWO RING-SHAPED WALLS OF AN AIRCRAFT ENGINE
DICHTUNGSANORDNUNG ZWISCHEN ZWEI RINGFÖRMIGEN WÄNDEN EINES FLUGZEUGTRIEBWERKS
2021-04-14
Patent
Elektronische Ressource
Französisch
IPC: | F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F16J Kolben , PISTONS |
ARRANGEMENT D'ETANCHEITE ENTRE DEUX PAROIS ANNULAIRES D'UN MOTEUR D'AERONEF
Europäisches Patentamt | 2019
|Europäisches Patentamt | 2021
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