Triple-flow aircraft turbine engine

A triple-flow aircraft turbine engine including a gas generator having along a longitudinal axis, at least one compressor, a combustion chamber, and at least one turbine, the turbine engine comprising:

• two coaxial annular walls, respectively internal and external, extending around each other and defining therebetween a main annular duct for a main air flow;
• a rotor blading extending radially across the main annular duct and forming a ducted propeller;
• an annular separator disposed downstream of the rotor blading and between the two coaxial annular walls, the annular separator defining, with the internal and external coaxial annular walls, respectively, two secondary flow annular ducts, respectively internal and external, for the secondary air flow, respectively internal and external, the separator comprising at an upstream end an annular nose configured to split the main air flow into two and to form the secondary air flows;
• stator elements extending radially on the one hand through the main duct and on the other hand through the secondary flow annular ducts the stator elements being connected to the annular nose;
• and
• a non-ducted propeller disposed upstream of the external wall,
• wherein the stator elements comprise:
• stationary guide vanes which are distributed around the longitudinal axis and which each comprise a leading edge located upstream of the nose, and trailing edges, respectively internal and external, located respectively in the internal and external secondary ducts, these stationary guide vanes being connected to the nose;
• variable-pitch guide vanes which are distributed about the longitudinal axis and which extend radially through at least one of the secondary flow annular ducts, each of the variable-pitch guide vanes comprising a leading edge and a trailing edge,
• and wherein:
• the leading edges of the variable pitch guide vanes are located upstream of the internal and/or external trailing edges of the stationary guide vanes;
• or
• the leading edges of the variable pitch guide vanes are located directly downstream of the internal and/or external trailing edges of the stationary guide vanes, and are separated by predetermined axial clearances from the trailing edges.