Turbine casing cooling device for a turbomachine

A method for managing a cooling device for a turbine casing of an aircraft engine extending along an axis (X), the aircraft engine having a fan downstream of which extends a compressor, a combustion chamber and a turbine comprising a turbine casing, the aircraft engine further having:

• a primary vein in which a primary flow (F1) circulates, said primary vein passing through in a direction of circulation of the primary flow (F1), the compressor, the combustion chamber and the turbine comprising the turbine casing,
• a secondary vein into which flows a secondary flow from the fan, wherein the secondary flow is distinct from the primary flow, the secondary vein extending around the primary vein,
• wherein the aircraft engine further includes a device for cooling the turbine casing, said cooling device having air-distribution means configured to take in air and convey it to the turbine casing, the air-distribution means having at least a first ramp and a second ramp extending circumferentially about the axis (X) respectively on a first circumferential portion and on a second circumferential portion different from each other, each of the first ramp and second ramp comprising air ejection orifices configured to be directed towards the turbine casing in order to cool it, the cooling device further having adjustment means capable of adjusting an air flow rate of air ejected at the first ramp with respect to an air flow rate of air ejected at the second ramp,
• each of the first ramp and second ramp extending circumferentially about the axis (X) and being located radially outside the turbine casing, the air ejection orifices of the ramps first ramp and second ramp being turned towards the said turbine casing,
• the method comprising:
• logging along two different axes accelerations experienced by at least one of an airframe or a propulsion system of an aircraft;
• determining an eccentricity of a rotor from the logged accelerations;
• and
• adjusting the adjustment means so as to adapt the air flow rate ejected at the first ramp to the air flow rate ejected at the second ramp.