Rotor blade with reduced acoustic response

1. A turbine engine rotor comprising:

a plurality of rotor blades, wherein a wake of the rotor blades impacts against structural elements mounted downstream from the rotor blades,

wherein each of said rotor blades includes a determined zone between a trailing edge and at most 50% of the chord of the respective rotor blade, wherein the determined zone of each rotor blade includes a modified surface state acting on a flow approaching said trailing edge, and

wherein determined zones of two circumferentially consecutive rotor blades are of different lengths, such that a speed of the flow over said rotor blades is altered to modify the acoustic interaction of the flow against structural elements downstream from said rotor blades.

2. The rotor according to claim 1 , wherein said determined zone is present over the entire height of the blade.

3. The rotor according to claim 1 , wherein said modified surface state is present on the suction side of the blade.

4. The rotor according to claim 3 , wherein said modified surface state comprises applying a textured paint or adhesively bonding a material acting as a rough skin, thereby slowing down the flow approaching said trailing edge.

5. The rotor according to claim 1 , wherein said modified surface state is present on the pressure side of the blade.

6. The rotor according to claim 5 , wherein said modified surface state comprises applying a textured paint or adhesively bonding a material providing a surface that is more effective from an aerodynamic point of view, so as to accelerate the flow approaching said trailing edge.

7. The rotor according to claim 6 , wherein said modified surface state presents a “shark's skin” type surface state.