Aerodynamic arm for an aircraft turbine engine casing

A double flow aircraft turbine engine, comprising a casing having:

• two coaxial annular rows of blading constituting an inner blading located in a primary flow duct of the double flow aircraft turbine engine and an outer blading located in a secondary flow duct of the double flow aircraft turbine engine and
• at least ten aerodynamic arms, each aerodynamic arm being part of a flow rectifier blading that passes through one of the secondary flow duct and the primary flow duct, each aerodynamic arm comprising:
• an outer tubular shell having a generally elongated shape extending substantially along an axis (A-A), the outer tubular shell comprising axial ends configured to connect to a casing of the turbine engine;
• an electrically conductive core extending inside the outer tubular shell and having electrical connection ends at each of the ends of the outer tubular shell;
• and
• an insulating material configured to occupy a space provided between the electrically conductive core and the outer tubular shell, wherein for any cross-section of the aerodynamic arm in a plane perpendicular to the axis (A-A) of the outer tubular shell, a maximum thickness (Ep) of the aerodynamic arm is between 2 mm and 10 mm, and a chord length (L) of the aerodynamic arm is between 30 mm and 150 mm,
• wherein each aerodynamic arm is located in the secondary flow duct with the outer blading.