Turbine blade for an aircraft turbomachine, provided with a channel for ejecting a primary flow towards an inter-lip cavity

An assembly for a turbine of a turbomachine extending around a longitudinal axis, comprising:

• a blade;
• a sealing element, said sealing element forming an abradable, the blade comprising a platform and an airfoil extending from the platform, the platform forming a first surface from which the airfoil extends and intended to delimit a primary duct wherein the airfoil extends in order to receive a fluid flowing in a direction going from a leading edge towards a trailing edge of the airfoil and going from an upstream part towards a downstream part of the platform, the sealing element being connected to the platform and forming a second surface intended to delimit an inter-lip cavity;
• an internal channel passing through the platform and having a suction opening which opens onto the first surface of the upstream part of the platform and an ejection opening which opens onto the second surface, the blade including a root between the platform and the sealing element, and the internal channel including an angled portion passing through the platform, and a radially extending portion passing through the root and the sealing element;
• and
• a rotor element carrying lips of a dynamic sealing joint, the inter-lip cavity extending longitudinally between two of said lips and radially between the abradable and the rotor element carrying the lips,
• wherein the suction opening is positioned upstream of the leading edge of the airfoil relative to a direction of flow of the fluid in the primary duct.