Aircraft turbine engine with a hybrid compressor

An aircraft turbine engine comprising at least one combustion chamber, a high-pressure compressor and a low-pressure body, said high-pressure compressor upstream of said at least one combustion chamber, said low-pressure body comprising an axial low-pressure compressor;

• upstream of said high-pressure compressor, said high-pressure compressor configured to deliver air to said at least one combustion chamber and, downstream of said at least one combustion chamber, a turbine receiving hot gases from said at least one combustion chamber and configured to drive a rotor of said axial low-pressure compressor, said axial low-pressure compressor comprising a plurality of compression stages each having a ring of rotor blades extending radially at a periphery of said rotor of the axial low-pressure compressor and a respective ring of stator vanes secured to a casing,
• wherein a first compression stage of the plurality of compression stages is a fan stage comprising a ring of fan rotor blades and a respective first ring of stator vanes, and downstream of the fan stage are booster stages of the plurality of compression stages, each of the booster stages comprising a respective ring of booster rotor blades and a respective ring of booster stator vanes,
• wherein said aircraft turbine engine further, comprises at least one electric machine located downstream of the last of the booster stages of said axial low-pressure compressor and upstream of said high-pressure compressor, the at least one electric machine is coaxial or parallel to said low-pressure body, a stator of the at least one electric machine is secured to said casing and a rotor of the at least one electric machine drives in rotation an additional ring of rotor blades downstream of the last of the booster stages and upstream of the high-pressure compressor, the additional ring of rotor blades configured to generate a flow of air when the additional ring of rotor blades is rotated, a respective additional ring of stator vanes secured to the casing being located downstream of and adjacent to the additional ring of rotor blades, and said rotor of the at least one electric machine being furthermore guided in rotation by at least one bearing secured to said casing so that a speed of rotation of said rotor of the at least one electric machine is independent of a speed of rotation of the rotor of the axial low-pressure compressor and independent of a speed of rotation of the high-pressure compressor, and
• wherein the rotor of the at least one electric machine rotates in the same direction of rotation as the rotor of said axial low-pressure compressor.