| abstract |
The invention relates to a turbine module, in particular for an aircraft, comprising a turbine nozzle comprising a plurality of sectors (S) with guide vanes extending between an inner platform element and an outer platform element, at least one of the platform elements of each sector carrying, on the one hand, at least one sealing blade (30) configured to ensure a fluid seal between the platform element and an adjacent structural element, and, on the other hand, retaining means for retaining the blade (30) in a sealed position; characterized in that each flat leaf spring (32) comprises an intermediate portion (34) fixed to the platform element of the sector (S) and opposite end portions (33, 35) supported on said blades (30) carried by the platform element. |