Self-contained hybrid turbine engine

A twin-spool turbofan type of turbine engine for an aircraft, the turbine engine having a main axis and comprising a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine, said low-pressure turbine being connected to said low-pressure compressor by a rotating low-pressure shaft centered on the main axis and said high-pressure turbine being connected to said high-pressure compressor by a rotating high-pressure shaft centered on the main axis,

• the turbine engine also comprising a mechanical power feed device on at least one of the rotating high-pressure shaft and the rotating low-pressure shaft,
• wherein the turbine engine comprises capacitive components adapted to supply the turbine engine with electrical energy through said mechanical power feed device, said capacitive components being arranged in at least one pair of concentric circles on a support structure of the turbine engine, said at least one pair of concentric circles being centered on the main axis of the turbine engine, each circle of the at least one pair of concentric circles being radially adjacent,
• wherein, for the at least one pair of concentric circles, the capacitive components of a radially inner circle of the at least one pair of concentric circles are arranged so as to be circumferentially offset by half the circumferential width of the capacitive components, relative to the capacitive components of a radially outer circle of the at least one pair of concentric circles.