Turbomachine turbine blade comprising a cooling circuit with improved homogeneity

A blade for an aircraft turbomachine turbine, comprising:

• a blade root defining a radially internal end of the blade;
• and
• an airfoil part extending radially outward from the blade root and having a pressure-side wall and a suction-side wall connected to the pressure-side wall at a leading edge and at a trailing edge of the airfoil part, the airfoil part comprising at least one internal cooling circuit,
• wherein said internal cooling circuit includes a plurality of cavities interconnected in series and distributed into:
• at least one cavity radially extending along the suction-side wall, hereinafter referred to as the “suction-side cavity”, and
• cavities radially extending along the pressure-side wall, hereinafter referred to as the “pressure-side cavities”, in an equal number to the number of suction-side cavity or cavities increased by one,
• and wherein:
• the at least one suction-side cavity is separated from at least one of the pressure-side cavities by a first internal wall of the airfoil part extending between the pressure-side and the suction-side walls,
• each pressure-side cavity has an air inlet section and an air outlet section, said air outlet section of each pressure-side cavity being arranged radially outward with respect to said air inlet section of each pressure-side cavity,
• the at least one suction-side cavity includes an air inlet section connected to the air outlet section of one of the pressure-side cavities and an air outlet section connected to the air inlet section of another of the pressure-side cavities, said air outlet section of the at least one suction-side cavity being radially arranged toward the inside with respect to said air inlet section of the at least one suction-side cavity,
• said air inlet section of one of the pressure-side cavities is connected to cooling air supply means,
• said at least one suction-side cavity is arranged facing two of said pressure-side cavities, from which the at least one suction-side cavity is separated by said first internal wall of the airfoil part, and
• said at least one suction-side cavity includes at least one first deflector extending protruding from the suction-side wall in a direction of the first internal wall of the airfoil part,
• wherein said first deflector has a concavity oriented radially outward and towards a side wall of the at least one suction-side cavity disposed on a same side as the pressure-side cavity to which the air outlet section of said at least one suction-side cavity is connected, wherein the first deflector includes a radially external end extending in the air inlet section of said at least one suction-side cavity, said first deflector being provided with air through-ports.