Aircraft propulsion assembly

An aircraft propulsion assembly, comprising:

• a triple-flow turbomachine;
• and
• a nacelle surrounding the turbomachine,
• wherein the turbomachine comprises:
• a gas generator comprising at least one compressor, one combustion chamber, and one turbine, the gas generator being arranged along a longitudinal axis;
• a first propeller mounted inside the nacelle and around the longitudinal axis and configured to accelerate an air inlet flow entering the nacelle;
• at least one annular element arranged radially between the gas generator and the nacelle and defining a first internal annular duct for supplying the gas generator, and a second external annular duct with the nacelle, the annular element comprising upstream a first annular splitter nose which is configured to split the air inlet flow into a first air flow flowing in the first duct and into a second air flow flowing in the second external annular duct;
• a second propeller mounted upstream of the nacelle and around the longitudinal axis and configured to accelerate a main air flow, the nacelle comprising upstream a second annular splitter nose which is configured to separate the main air flow into the inlet air flow flowing into the nacelle and into a third air flow flowing around the nacelle;
• a first stator vane extending radially between a casing of the gas generator and the nacelle upstream of the first annular splitter nose and downstream of the first propeller;
• and
• a second stator vane extending radially between a casing of the gas generator and the annular element, downstream of the first splitter nose and upstream of a first rotor vane of the at least one compressor of the gas generator, and/or between the annular element and the nacelle, downstream of the first annular splitter nose,
• wherein at least one of the first and second stator vanes is a variable pitch vane or comprises at least one variable pitch portion.