MOBILE TURBINE AUB WITH IMPROVED DESIGN FOR AN AIRCRAFT TURBOMACHINE

摘要

The invention relates to a turbine blade (20) for an aircraft turbine engine comprising a foot (24), a blade (30) and a platform (28) interposed between the blade and the foot and delimiting a flow of gas flow. (14a), the platform (28) having two axial ends respectively forming two spoilers (44, 46) of which at least one of them has an internal cavity (46a) intended to be supplied with air from the foot (24) of dawn. According to the invention, at least one of the two spoilers is pierced with at least one purge hole (82) for the passage of a purge flow (84) coming from the internal cavity (46a) and intended to limit / prevent recirculation of gases outside the vein (14a).