Aeronautical propulsion system comprising an optimized fan section
AssigneeSafran Aircraft Engines
InventorsMatthieu Pierre Michel DUBOSC, Guillaume Olivier Vartan MARTIN, Didier René André ESCURE
Life of this patent
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Abstract
A fan section of a propulsion system includes a fan rotor including twenty-two blades and having a solidity greater than or equal to 0.9 and less than or equal to 1.3, where the solidity is equal to a ratio between a chord at the tip of a blade and an inter-blade pitch at the tip of the blade. The fan section has a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5, and a peripheral speed at the tip of the blade greater than or equal to 270 m/s and less than or equal to 380 m/s. The pressure ratio and the peripheral speed are measured at cruising power.
Claims20
A fan section of a propulsion system, the fan section comprising:
- a fan rotor comprising exactly twenty-two blades and having a solidity greater than or equal to 0.9 and less than or equal to 1.3, where the solidity is equal to a ratio between a chord at the tip of a blade and an inter-blade pitch at the tip of the blade,
- wherein the fan section has:
- a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5;
- and
- a peripheral speed at the tip of the blade greater than or equal to 270 m/s and less than or equal to 380 m/s, and
- wherein the pressure ratio and the peripheral speed are measured at cruising power.
(canceled)
A operating method for operating a fan section of a propulsion system, the fan section comprising a fan rotor comprising exactly twenty-two blades and having a solidity greater than or equal to 0.9 and less than or equal to 1.3, where the solidity is equal to a ratio between a chord at a tip of a blade and an inter-blade pitch at the tip of the blade,
- wherein the fan section has:
- a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5;
- and
- a peripheral speed at the tip of the blade greater than or equal to 270 m/s and less than or equal to 380 m/s, and
- wherein the pressure ratio and the peripheral speed are measured at cruising power,
- the method comprising operating the fan section of the propulsion system.
A manufacturing method of a fan section of a propulsion system, the manufacturing method comprising:
- dimensioning the fan section, wherein the fan section comprises a fan rotor comprising exactly twenty-two blades and having a solidity greater than or equal to 0.9 and less than or equal to 1.3, where the solidity is equal to a ratio between a chord at a tip of a blade and an inter-blade pitch at the tip of the blade, wherein the fan section has:
- a pressure ratio greater than or equal to 1.05 and less than or equal to 1.5;
- and
- a peripheral speed at the tip of the blade greater than or equal to 270 m/s and less than or equal to 380 m/s, and
- wherein the pressure ratio and the peripheral speed are measured at cruising power;
- and
- manufacturing the fan section that has been dimensioned.
Dependencies are inferred from the claim text.