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US 2026/0226873 A1Published application
Aeronautical propulsion system having a ducted fan and a high bypass ratio
AssigneeSafran Aircraft Engines
InventorCorinne Françoise Michelle THIEBAULT
Life of this patent
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Abstract
An aeronautical propulsion system includes a ducted fan section including a fan, the fan having a fan rotor including blades, and a gas generator including a drive shaft that rotationally drives, directly or indirectly, the fan rotor. The aeronautical propulsion system is dimensioned such as to verify two relationships governing a diameter of the fan rotor, a maximum thrust generated by the fan, and a bypass ratio of a flow through the aeronautical propulsion system.
Claims19
An aeronautical propulsion system;
- comprising:
- a ducted fan section comprising a fan, the fan having a fan rotor comprising blades, and
- a gas generator comprising a drive shaft configured to rotationally drive, directly or indirectly, the fan rotor,
- wherein the aeronautical propulsion system is dimensioned such as to verify the following pair of relationships:
- a
- .
- 0
- ≤
- P
- ·
- D
- ·
- 10
- -
- 4
- ≤
- 160
-
- and
- b
- .
- 2.7
- ·
- (
- P
- ·
- D
- ·
- 10
- -
- 4
- )
- 0
- .
- 6
- ≤
- 100
- ·
- D
- 2
- B
-
- P
-
- R
- +
- 1
- ≤
- 3.9
- ·
- (
- P
- ·
- D
- ·
- 10
- -
- 4
- )
- 0.6
- where:
- D is a diameter of the fan rotor in meters which is measured in a plane normal to an axis of rotation of the fan rotor, at an intersection between an end edge and a leading edge of the blades of the fan rotor;
- P is a maximum thrust generated by the fan in Newtons when the aeronautical propulsion system is static at takeoff regime, in a standard atmosphere and at sea level;
- and
- BPR is a bypass ratio of a flow through the aeronautical propulsion system, defined as a ratio between a mass flow rate of a secondary air stream flowing through the aeronautical propulsion system around the gas generator, and of a primary air stream flowing through the gas generator, measured when the aeronautical propulsion system is static, uninstalled, at a regime corresponding to a takeoff of an aircraft comprising the aircraft propulsion system, in a standard atmosphere and at sea level.
62 more elements
A method for manufacturing an aircraft propulsion system, the aircraft propulsion system comprising:
- a ducted fan section comprising a fan, the fan having a fan rotor comprising blades, and
- a gas generator comprising a drive shaft configured to rotationally drive, directly or indirectly, the fan rotor,
- the manufacturing method comprising:
- dimensioning the fan rotor during which a diameter D of the fan rotor in meters and measured in a plane normal to an axis of rotation of the fan rotor, at an intersection between an end edge and a leading edge of the blades of the fan rotor is chosen such that:
- 0
- ≤
- P
- ·
- D
- ·
- 10
- -
- 4
- ≤
- 160
-
- and
- 2.7
- ·
- (
- P
- ·
- D
- ·
- 10
- -
- 4
- )
- 0
- .
- 6
- ≤
- 100
- ·
- D
- 2
- B
-
- P
-
- R
- +
- 1
- ≤
- 3.9
- ·
- (
- P
- ·
- D
- ·
- 10
- -
- 4
- )
- 0.6
- where:
- P is a maximum thrust generated by the fan in Newtons when the aircraft propulsion system is static in takeoff regime, in a standard atmosphere and at sea level;
- and
- BPR is a bypass ratio of a stream crossing the aircraft propulsion system, defined as a ratio between a mass flow rate of a secondary air stream flowing through the aircraft propulsion system around the gas generator, and of a primary air stream flowing through the gas generator, measured when the aircraft propulsion system is static, uninstalled, at a regime corresponding to takeoff of an aircraft comprising the aircraft propulsion system, in a standard atmosphere and at sea level.
57 more elements
Dependencies are inferred from the claim text.