An auxiliary tank for an aircraft turbine engine, has a curved general shape, and includes a cylindrical or frustoconical radially outer wall and three cylindrical or frustoconical radially inner walls arranged facing the radially outer wall, the three radially inner walls having a middle wall and two side walls arranged to either side of the middle wall. The inner volume of the tank forms a U-shape, the branches of which are formed by lateral volume portions between the side walls and the radially outer wall, and the base of which is formed by a middle volume portion between the middle wall and the radially outer wall.
AUXILIARY OIL TANK FOR AN AIRCRAFT TURBINE ENGINE
2021-11-18
Patent
Electronic Resource
English
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F16H Getriebe , GEARING |
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