Patent ID: 11873729
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A turbofan engine with a longitudinal axis (X-X′) comprising a primary duct in which there flows a primary flow at a primary pressure (P3) and a secondary duct which radially surrounds said primary duct and in which there flows a secondary flow (F2) at a secondary pressure (PS), said primary duct including at least one compressor configured to compress the primary flow, a turbine driving said compressor in rotation and a combustion chamber designed to receive, at an inlet, the primary air flow compressed by the compressor, said turbomachine further comprising a cooling circuit extending between the compressor and the turbine and in which flows a flow (F1) of cooling air taken from an outlet of the compressor and having as pressure the primary pressure (P3), wherein the cooling circuit comprises a device configured to regulate a cooling air flow rate arranged upstream of the turbine and comprising at least one valve that is configured to move between an open position and a closed position depending on a pressure difference (ΔP) between the pressure (P3) in the primary duct located between the compressor and the combustion chamber and the pressure (PS) in the secondary duct.