US 12,305,570 B2
Recovered-cycle turboshaft engine
Bernard Claude Pons, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 18/726,349
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Jan. 2, 2023, PCT No. PCT/FR2023/050001
§ 371(c)(1), (2) Date Jul. 2, 2024,
PCT Pub. No. WO2023/135378, PCT Pub. Date Jul. 20, 2023.
Claims priority of application No. 2200229 (FR), filed on Jan. 12, 2022.
Prior Publication US 2025/0067211 A1, Feb. 27, 2025
Int. Cl. F02C 3/107 (2006.01); F02C 7/10 (2006.01); F02C 7/32 (2006.01); F02C 7/36 (2006.01)
CPC F02C 3/107 (2013.01) [F02C 7/10 (2013.01); F02C 7/32 (2013.01); F02C 7/36 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A turboshaft engine for an aircraft, the turboshaft engine comprising:
a gas generator comprising a compressor, a combustion chamber and an expansion turbine, the compressor and the expansion turbine extending along a common longitudinal axis and being mechanically connected to one another, the combustion chamber being arranged axially at a rear end of the turboshaft engine;
a power turbine arranged axially between the compressor and the expansion turbine, the power turbine driving a power take-off in rotation via a reduction gear;
a heat exchanger comprising:
a first circuit comprising an inlet connected to an outlet of the compressor, and an outlet connected to an inlet of the combustion chamber, and
a second circuit comprising an inlet connected to an outlet of the power turbine,
wherein the compressor comprises a first shaft driven in rotation by a second shaft of the expansion turbine via a transmission mechanism, said transmission mechanism and said reduction gear forming part of a transmission casing which is arranged axially at a front end of the turboshaft engine, so that the compressor is arranged axially between the transmission casing and the power turbine.