US 11,988,112 B2
Recovered-cycle aircraft turbomachine
Bernard Claude Pons, Moissy-Cramayel (FR); Alphonse Puerto, Moissy-Cramayel (FR); Laurent Pierre Tarnowski, Moissy-Cramayel (FR); and Loïs Pierre Denis Vive, Moissy-Cramayel (FR)
Assigned to Safran Helicopter Engines, Bordes (FR)
Appl. No. 18/001,677
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Jun. 15, 2021, PCT No. PCT/FR2021/051076
§ 371(c)(1), (2) Date Dec. 13, 2022,
PCT Pub. No. WO2021/255384, PCT Pub. Date Dec. 23, 2021.
Claims priority of application No. 2006310 (FR), filed on Jun. 17, 2020.
Prior Publication US 2023/0220779 A1, Jul. 13, 2023
Int. Cl. F01D 9/02 (2006.01)
CPC F01D 9/026 (2013.01) [F05D 2220/329 (2013.01); F05D 2240/14 (2013.01)] 10 Claims
OG exemplary drawing
 
1. An aircraft turbomachine, comprising:
a centrifugal compressor extending around an axis A;
an annular combustion chamber extending around the axis A;
an annular casing extending around the axis A and the chamber and delimiting an annular space in which the annular combustion chamber is located; and
a heat exchanger comprising:
a first circuit supplied with exhaust gases from the aircraft turbomachine;
and a second circuit having an inlet connected by a first volute to an outlet of the centrifugal compressor, and an outlet connected by a second volute to the annular space,
wherein the first and second volutes are distinct and axially spaced from one another along the axis A on either side of the annular combustion chamber, and
wherein the second volute is connected to the annular space by a rectifier located at least in part outside the annular casing, the rectifier being integrated into an annular connecting pipe connecting the second volute to the annular casing.