Granted Patent B2

US 12,286,887 · App. 18/705,309 · Granted Apr 29, 2025

Inventors: Boris Pierre Marcel Morelli (Moissy-Cramayel, FR); Matthieu Bruno François Foglia (Moissy-Cramayel, FR); Clément Raucoules (Moissy-Cramayel, FR); Jean-Pierre Serey (Moissy-Cramayel, FR)

Assignees: SAFRAN AIRCRAFT ENGINES; SAFRAN TRANSMISSION SYSTEMS

F01D15/10F05D2220/323F05D2220/76

Abstract

Claims (32)

1. 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 the at least one support arm and the at least one electrical energy generation device driven by the secondary air flow.

2. The turbomachine according to claim 1 , wherein the at least one of the electrical energy generation devices is mounted on a support arranged around the longitudinal axis of the turbomachine between the at least one support arm.

3. The turbomachine according to claim 1 , wherein the at least one electrical energy generation device is mounted on the at least one support arm or on a support arranged around the longitudinal axis of the turbomachine between two support arms of the at least one support arm.

4. The turbomachine according to claim 1 , wherein at least one of the electrical energy generation devices is mounted retractably on the nacelle radially relative to the longitudinal axis of the turbomachine.

5. The turbomachine according to claim 4 , wherein the electrical energy generation devices mounted radially on the nacelle are placed between the support arms or upstream of the support arms relative the secondary air flow.

6. The turbomachine according to claim 1 , wherein the nacelle comprises at least one cavity wherein is mounted one of the electrical energy generation devices.

7. The turbomachine according to claim 6 , wherein a cavity of the nacelle comprises a retractable hatch.

8. The turbomachine according to claim 6 , wherein the cavities of the nacelle are NACA air inlets.

9. An aircraft comprising at least one turbomachine according to claim 1 .

10. 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.

11. The turbomachine according to claim 10 , wherein at least one of the electrical energy generation devices is mounted retractably on the nacelle radially relative to the longitudinal axis of the turbomachine.

12. The turbomachine according to claim 11 , wherein the electrical energy generation devices mounted radially on the nacelle are placed between the support arms or upstream of the support arms relative the secondary air flow.

13. The turbomachine according to claim 12 , wherein the nacelle comprises at least one cavity wherein is mounted one of the electrical energy generation devices.

14. The turbomachine according to claim 13 , wherein a cavity of the nacelle comprises a retractable hatch.

15. The turbomachine according to claim 13 , wherein the cavities of the nacelle are NACA air inlets.

16. An aircraft comprising at least one turbomachine according to claim 10 .

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.

18. The turbomachine according to claim 17 , wherein the electrical energy generation devices mounted radially on the nacelle are placed between the support arms or upstream of the support arms relative the secondary air flow.

19. The turbomachine according to claim 17 , wherein the nacelle comprises at least one cavity wherein is mounted one of the electrical energy generation devices.

20. An aircraft comprising at least one turbomachine according to claim 17 .

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (21)