US 12,286,887 B2
Integration of generators in an air flow of an aircraft engine
Boris Pierre Marcel Morelli, Moissy-Cramayel (FR); Matthieu Bruno François Foglia, Moissy-Cramayel (FR); Clément Raucoules, Moissy-Cramayel (FR); and Jean-Pierre Serey, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN TRANSMISSION SYSTEMS, Colombes (FR)
Appl. No. 18/705,309
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN TRANSMISSION SYSTEMS, Colombes (FR)
PCT Filed Oct. 18, 2022, PCT No. PCT/FR2022/051969
§ 371(c)(1), (2) Date Apr. 26, 2024,
PCT Pub. No. WO2023/073305, PCT Pub. Date May 4, 2023.
Claims priority of application No. 2111502 (FR), filed on Oct. 28, 2021.
Prior Publication US 2025/0003350 A1, Jan. 2, 2025
Int. Cl. F01D 15/10 (2006.01)
CPC F01D 15/10 (2013.01) [F05D 2220/323 (2013.01); F05D 2220/76 (2013.01)] 20 Claims
OG exemplary drawing
 
17. 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.