Patent ID: 11965433
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A turbomachine turbine nozzle extending around a central axis, comprising:
a radially outer shroud,
a radially inner shroud comprising a radial positioning flange,
a blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between said radially inner shroud and said radially outer shroud, the blade being hollow and comprising a cavity opening at a radially inner end and at a radially outer end of the blade, and
a tubular mast arranged in the cavity of the blade and allowing routing of ventilation air passing through said cavity of the blade, the tubular mast comprising a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with the radial positioning flange of the radially inner shroud, the radially inner end of the tubular mast comprising an engagement portion which cooperates by interlocking with a notch of said radial positioning flange so as to limit relative movement of the tubular mast with respect to the radial positioning flange.