Turbofan engine including a fan actuation system
A turbofan engine for an aircraft includes a fan and a fan actuation system. The fan has a plurality of fan blades coupled to a fan shaft having one or more fan bearings. The fan blades are rotatable about a pitch axis. The fan actuation system is disposed within a fan hub and includes one or more actuators for rotating the fan blades about the pitch axis and one or more radial thrust bearings. The fan actuation system is characterized by a fan actuation system length envelope in a range of 8.5 to 24 and given by N FB × D FT L AXIAL × ( R TB N FB ) . N FB is a number of the fan blades, D FT is a fan tip diameter of the fan blades, R TB is a thrust bearing radius of the radial thrust bearings, and L AXIAL is an axial length from a fan hub tip to the fan bearings.
1. A turbofan engine for an aircraft, the turbofan engine comprising:
a fan having a plurality of fan blades coupled to a fan shaft having one or more fan bearings, each of the plurality of fan blades being rotatable about a pitch axis and extending from a fan hub; and
a fan actuation system disposed within the fan hub and including one or more actuators for rotating the plurality of fan blades about the pitch axis and one or more radial thrust bearings, wherein the fan actuation system is characterized by a fan actuation system length envelope in a range of 8.5 to 24, the fan actuation system length envelope being given by:
N
FB
×
D
FT
L
AXIAL
×
(
R
TB
N
FB
)
wherein N FB is a number of the plurality of fan blades, D FT is a fan tip diameter of the plurality of fan blades, R TB is a thrust bearing radius of the one or more radial thrust bearings, and L AXIAL is an axial length from a fan hub tip of the fan hub to the one or more fan bearings.
2. The turbofan engine of claim 1 , wherein the fan actuation system includes a pressurized pneumatic chamber that is filled with a pressurized gas that biases the plurality of fan blades to a feather position.
3. The turbofan engine of claim 1 , wherein the fan actuation system includes one or more counterweights for reducing inertial loading associated with rotation of the plurality of fan blades.
4. The turbofan engine of claim 1 , further comprising a turbo-engine, wherein the turbofan engine has a longitudinal centerline axis, and the turbo-engine is annular about the longitudinal centerline axis wherein the turbo-engine includes a core inlet that is annular about the longitudinal centerline axis.
5. The turbofan engine of claim 1 , wherein the fan actuation system includes a hydraulic system that supplies hydraulic fluid for rotating the plurality of fan blades about the pitch axis.
6. The turbofan engine of claim 1 , wherein N FB is in a range of ten to eighteen.
7. The turbofan engine of claim 6 , wherein N FB is in a range of ten to fourteen.
8. The turbofan engine of claim 1 , wherein D FT is in a range of 84.0 inches to 180.0 inches.
9. The turbofan engine of claim 8 , wherein D FT is in a range of 84.0 inches to 120.0 inches.
10. The turbofan engine of claim 8 , wherein D FT is in a range of 120.0 inches to 180.0 inches.
11. The turbofan engine of claim 1 , wherein R TB is in a range of 12 inches to 27 inches.
12. The turbofan engine of claim 11 , wherein R TB is in a range of 12 inches to 19 inches.
13. The turbofan engine of claim 11 , wherein R TB is in a range of 19 inches to 27 inches.
14. The turbofan engine of claim 1 , wherein L AXIAL is given by A FH +A FB , A FH being a fan hub axial length from the fan hub tip to the pitch axis of the plurality of fan blades and A FB being a fan bearing axial length from the pitch axis of the plurality of fan blades to the one or more fan bearings.
15. The turbofan engine of claim 14 , wherein A FH is in a range of 25 inches to 75 inches.
16. The turbofan engine of claim 14 , wherein A FB is in a range of 16 inches to 23 inches.
17. The turbofan engine of claim 14 , wherein the fan actuation system has a fan actuation system axial length (A FAS ) defined from an axially forward-most surface of the fan actuation system to the pitch axis of the plurality of fan blades, A FAS being a maximum of 80% A FH .
18. A turbofan engine for an aircraft, the turbofan engine comprising:
a fan having a plurality of fan blades coupled to a fan shaft having one or more fan bearings, each of the plurality of fan blades being rotatable about a pitch axis and extending from a fan hub;
a nacelle that circumferentially surrounds the fan; and
a fan actuation system disposed within the fan hub and including one or more actuators for rotating the plurality of fan blades about the pitch axis and one or more radial thrust bearings, wherein the fan actuation system is characterized by a fan actuation system length envelope in a range of 8.5 to 13, the fan actuation system length envelope being given by:
N
FB
×
D
FT
L
AXIAL
×
(
R
TB
N
FB
)
wherein N FB is a number of the plurality of fan blades, D FT is a fan tip diameter of the plurality of fan blades, R TB is a thrust bearing radius of the one or more radial thrust bearings, and L AXIAL is an axial length from a fan hub tip of the fan hub to the one or more fan bearings, wherein L AXIAL is given by A FH +A FB , A FH being a fan hub axial length from the fan hub tip to the pitch axis of the plurality of fan blades and A FB being a fan bearing axial length from the pitch axis of the plurality of fan blades to the one or more fan bearings, A FH is in a range of 25 inches to 40 inches, and A FB is in a range of 17 inches to 20 inches.
19. A turbofan engine for an aircraft, the turbofan engine comprising:
a fan having a plurality of fan blades coupled to a fan shaft having one or more fan bearings, the fan being an open fan, and each of the plurality of fan blades being rotatable about a pitch axis and extending from a fan hub; and
a fan actuation system disposed within the fan hub and including one or more actuators for rotating the plurality of fan blades about the pitch axis and one or more radial thrust bearings, wherein the fan actuation system is characterized by a fan actuation system length envelope in a range of 8.5 to 24, the fan actuation system length envelope being given by:
N
FB
×
D
FT
L
AXIAL
×
(
R
TB
N
FB
)
wherein N FB is a number of the plurality of fan blades, D FT is a fan tip diameter of the plurality of fan blades, R TB is a thrust bearing radius of the one or more radial thrust bearings, and L AXIAL is an axial length from a fan hub tip of the fan hub to the one or more fan bearings, and R TB is a thrust bearing radius of the one or more radial thrust bearings, wherein L AXIAL is given by A FH +A FB , A FH being a fan hub axial length from the fan hub tip to the pitch axis of the plurality of fan blades and A FB being a fan bearing axial length from the pitch axis of the plurality of fan blades to the one or more fan bearings, A FH is in a range of 25 inches to 75 inches, and A FB is in a range of 16 inches to 23 inches, and D FT is in a range of 120.0 inches to 180.0 inches.
20. The turbofan engine of claim 19 , wherein R TB is in a range of 12 inches to 27 inches.