Aero-propulsion system with improved propulsion efficiency
AssigneeSafran Aircraft Engines
InventorDidier René André ESCURE
Life of this patent
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Abstract
A propulsion system includes a drive shaft movable in rotation about an axis of rotation, a fan shaft, a fan section comprising a ducted fan rotor driven in rotation by the fan shaft, the fan rotor including plural blades, and a reduction mechanism that couples the drive shaft and the fan shaft in order to drive the fan shaft at a rotation speed lower than the rotation speed of the drive shaft. A thrust density per blade of the fan rotor of the propulsion system being greater than or equal to 1.40×105 and less than or equal to 1.70×105 N/m2 where the thrust density per blade is defined based on a thrust generated by the fan rotor measured when the propulsion system is stationary in take-off rating and a diameter of the fan rotor.
Claims19
A propulsion system comprising:
- a drive shaft movable in rotation about an axis of rotation;
- a fan shaft;
- a fan section comprising a ducted fan rotor driven in rotation by the fan shaft, the fan rotor comprising a plurality of blades;
- and
- a reduction mechanism coupling the drive shaft and the fan shaft in order to drive the fan shaft at a rotation speed lower than the rotation speed of the drive shaft;
- a thrust density per blade of the fan rotor of the propulsion system being greater than or equal to 1.40×105 and less than or equal to 1.70×105 N/m2 where the thrust density per blade is defined by the following formula:
- Thrust
-
- density
- =
- FN
- n
- *
- D
- 2
- *
- 100
- and where:
- FN is a thrust generated by the fan rotor and is measured when the propulsion system is stationary in take-off rating in a standard atmosphere and at sea level and is expressed in Newton;
- n is a number of blades in the fan rotor;
- and
- D is a diameter of the fan rotor, measured in a plane normal to the axis of rotation at an intersection between a tip and a leading edge of the blades of the fan rotor, and is expressed in meters.
A method for dimensioning a propulsion system comprising a reduction mechanism coupling a drive shaft and a ducted fan rotor to drive the fan rotor at a speed lower than a speed of the drive shaft, wherein the fan rotor is dimensioned such that a thrust density per blade of the fan rotor of the propulsion system is greater than or equal to 1.40×105 and less than or equal to 1.70×105 N/m2 where the thrust density per blade of the fan rotor is defined by the following formula:
- Thrust
-
- density
- =
- FN
- n
- *
- D
- 2
- *
- 100
- and where:
- FN is a thrust of the fan rotor and is measured when the propulsion system is stationary in take-off rating in a standard atmosphere and at sea level and is expressed in Newton;
- n is a number of blades in the fan rotor;
- and
- D is a fan diameter, measured in a plane normal to the axis of rotation at an intersection between a tip and a leading edge of the blades of the fan rotor, and is expressed in meters.
Dependencies are inferred from the claim text.