Loading patent…
AssigneeSafran Aircraft Engines
InventorsMatthieu Pierre Michel DUBOSC, Guillaume Olivier Vartan MARTIN, Didier René André ESCURE
Estimating the term…
A fan section of an aeronautical propulsion system includes a fan rotor including seventeen blades to twenty blades and having a solidity strictly less than 1.0. The solidity is equal to a ratio between a chord at the blade tip and an inter-blade pitch at the blade tip. The fan section has a hub-tip ratio greater than or equal to 0.22 and less than or equal to 0.32, a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5, and a peripheral speed at the blade tip greater than or equal to 260 m/s and less than or equal to 400 m/s. The pressure ratio and the peripheral speed are measured at cruising speed.
A fan section of an aeronautical propulsion system, the fan section comprising a fan rotor comprising at least seventeen blades and at most twenty blades and having a solidity strictly less than 1.0, where the solidity is equal to a ratio between a chord at the blade tip and an inter-blade pitch at the blade tip, the fan section having a hub-tip ratio greater than or equal to 0.22 and less than or equal to 0.32, a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5 and a peripheral speed at the blade tip greater than or equal to 260 m/s and less than or equal to 400 m/s, the pressure ratio and the peripheral speed being measured at cruising speed.
A method for dimensioning a fan section of an aeronautical propulsion system, the fan section comprising a fan rotor comprising at least seventeen blades and at most twenty blades and having a solidity strictly less than 1.0 and optionally strictly greater than 0.6, where the solidity is equal to a ratio between a chord at the blade tip and an inter-blade pitch at the blade tip, the fan section having a hub-tip ratio greater than or equal to 0.22 and less than or equal to 0.32, a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5, and a peripheral speed at the blade tip greater than or equal to 260 m/s and less than or equal to 400 m/s, the pressure ratio and the peripheral speed being measured at cruising speed.
Dependencies are inferred from the claim text.