The invention relates to a secondary flow stator vane (1) for a turbomachine, comprising skins (2, 3) having end portions (21, 31) delimiting an opening (5) and a cavity (4) therebetween, which skins diverge from one another in a direction (Y). A filler material (41) is located in the cavity (4) at a distance from the opening (5). A reinforcement (6), the density of which is higher than the density of the material (41), comprises a first reinforcement portion (61) located in the cavity (4) against the material (41) and a second reinforcement portion (62) for closing the opening (5) between the portions (21, 31) to form a single piece.
Secondary flow guide vane of a turbomachine and turbomachine provided therewith
29.07.2025
Patent
Elektronische Ressource
Englisch
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 / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS / F03B MACHINES OR ENGINES FOR LIQUIDS , Kraft- und Arbeitsmaschinen oder Kraftmaschinen für Flüssigkeiten |
Secondary flow guide vane of turbomachine and turbomachine provided with secondary flow guide vane
Europäisches Patentamt | 2024
|Europäisches Patentamt | 2020
|Europäisches Patentamt | 2019
|UNDUCTED RECTIFIER FOR A TURBOMACHINE, TURBOMACHINE MODULE AND AIRCRAFT TURBOMACHINE
Europäisches Patentamt | 2024
|Unducted rectifier for a turbomachine, turbomachine module and aircraft turbomachine
Europäisches Patentamt | 2025
|