US 12,286,926 B2
Recovered-cycle aircraft turbomachine
Bernard Claude Pons, Moissy-Cramayel (FR); Alphonse Puerto, Moissy-Cramayel (FR); Laurent Pierre Tarnowski, Moissy-Cramayel (FR); and Lois Pierre Denis Vive, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 18/001,441
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Jun. 15, 2021, PCT No. PCT/FR2021/051075
§ 371(c)(1), (2) Date Dec. 9, 2022,
PCT Pub. No. WO2021/255383, PCT Pub. Date Dec. 23, 2021.
Claims priority of application No. 2006309 (FR), filed on Jun. 17, 2020.
Prior Publication US 2023/0220800 A1, Jul. 13, 2023
Int. Cl. F02C 7/08 (2006.01); F02C 3/08 (2006.01); F02C 3/10 (2006.01); B64C 27/12 (2006.01); F04D 29/42 (2006.01)
CPC F02C 3/103 (2013.01) [F02C 3/08 (2013.01); F02C 7/08 (2013.01); B64C 27/12 (2013.01); F04D 29/4233 (2013.01); F05D 2220/329 (2013.01)] 21 Claims
OG exemplary drawing
 
14. A turbomachine comprising:
a combustion chamber; and
a volute assembly, said volute assembly comprising first and second volutes which are axially joined together, each including an annular conduit wound around an axis A, the first and second volutes each comprising a first port located at the external periphery of the conduit and oriented in the tangential direction, and a second port located at the internal periphery of the conduit and oriented in the radial direction, the second ports of the volutes opening onto an outside of the volute assembly, the conduit of each of the volutes having an evolving passage cross-section which is maximum at the level of the first port and minimum at a circumferential end of the conduit opposite the first port, the volutes having reversed winding directions so that their first ports are formed by conduit portions spaced apart from each other and the minimum cross-section of each conduit is located at the level of a larger cross-section of the other conduit,
wherein at least one of the second ports of the volutes extends from an annular rectifier of the combustion chamber.