Guide pulley blade assembly blade box of axial turbine engine compressor

The present invention relates to an angle section of the blade rotor of a low-pressure compressor of an axial turbine engine compressor. The section comprises an arc external lantern ring (30) installed at the external housing of the turbine engine compressor in a concentric mode and an internal lantern ring. The section also comprises a row of rotor blades (42) extending in a radial direction and pitched in the lantern ring (30), and a blade box is form in such manner. The blades (42) of the box comprise the pitching legs (50) at the external end portion, wherein the pitching legs (50) are arranged in the thickness of the external lantern ring (30). The internal lantern ring comprises a pile used for pitching the blades (42).