Unducted turbine engine comprising stator blades having different chords

An aircraft comprising:

• at least one unducted turbine engine for propulsion of the aircraft, the turbine engine extending along a longitudinal axis and being configured to accelerate an air flow circulating from upstream to downstream, the turbine engine comprising a rotor and a stator mounted downstream of the rotor, the stator comprising a plurality of stator vanes for straightening the air flow coming from the rotor extending radially with respect to the longitudinal axis and distributed angularly about the longitudinal axis, each of the stator vanes comprising a leading edge and a trailing edge defining between them a chord in a plane of revolution defined with respect to the longitudinal axis, each of the stator vanes being defined, in a plane transverse to the longitudinal axis, by an angular position, and
• at least one aerodynamic obstacle, positioned close to the turbine engine, the aerodynamic obstacle causing a change in the circulation of the air flow downstream of the stator vanes,
• wherein the plurality of stator vanes includes conventional vanes each defining a first cord and at least one elongated vane defining a second cord, and wherein the second chord is larger than the first chord, said at least one elongated vane being positioned in an interference angular range defined in relation with the aerodynamic obstacle, so as to increase the straightening of the air flow from the rotor in the interference angular range.