Emergency ventilation device for a turbine of a turbine engine, triggered by the melting of a locking means

An aircraft turbomachine turbine comprising a ventilation device configured to have a cooling air flow circulate in the turbine, the turbine comprising a annular vein of hot airflow, a sub-vein cavity coaxial to the hot airflow vein, the ventilation device comprising:

• an injection device configured to inject cooling air into the sub-vein cavity,
• at least one tube extending into the sub-vein cavity, a first end of the tube being fixed to a wall of the sub-vein cavity, a second end of the tube being an air outlet,
• blocking means fixed to the second end and mobile between a blocking position of the air outlet and an opening position of the air outlet, and
• locking means configured to maintain the blocking means in the blocking position when the temperature within the sub-vein cavity is less than a predetermined threshold value, the locking means comprising a fusible material configured to melt so as to let the blocking means adopt the opening position when the temperature within the module is greater than said predetermined threshold value
• wherein the blocking means are a flap mobile between the blocking position and opening position by means of a hinge fixed to the second end of the tube.