Integration of generators in an air flow of an aircraft engine

A turbomachine comprising:

• a fan arranged along a longitudinal axis of the turbomachine,
• a primary duct able to channel a flow of primary air from the fan through a compressor, a combustion chamber and a turbine of the turbomachine,
• an annular nacelle surrounding the fan so as to delimit a secondary duct able to channel a flow of secondary air from the fan, a temperature of which is less than that of the primary air from the fan, the secondary air flow of the fan extending around the primary air flow of the fan, and
• at least one support arm arranged around the longitudinal axis (X) between the annular nacelle and a hub which delimits the primary and secondary ducts, wherein the turbomachine also comprises at least one electrical energy generation device mounted on a support arranged around the longitudinal axis of the turbomachine between the at least one support arm and the at least one electrical energy generation device driven by the secondary air flow.

A turbomachine comprising:

• a fan arranged along a longitudinal axis of the turbomachine,
• a primary duct able to channel a flow of primary air from the fan through a compressor, a combustion chamber and a turbine of the turbomachine,
• an annular nacelle surrounding the fan so as to delimit a secondary duct able to channel a flow of secondary air from the fan, a temperature of which is less than that of the primary air from the fan, the secondary air flow of the fan extending around the primary air flow of the fan, and
• at least one support arm arranged around the longitudinal axis (X) between the annular nacelle and a hub which delimits the primary and secondary ducts, wherein the turbomachine also comprises at least one electrical energy generation device mounted retractably on the nacelle radially relative to the longitudinal axis of the turbomachine, and the at least one electrical energy generation device is driven by the secondary air flow.