Flexured standpipes for aircraft propulsion assemblies
A propulsion assembly includes a rotor assembly, a mast coupled to the rotor assembly and a bull gear coupled to the mast. The bull gear is subject to radial and axial loads. The propulsion assembly includes a flexured standpipe extending through the bull gear and a ball bearing including inner and outer races interposed between the bull gear and the flexured standpipe. The ball bearing is configured to absorb axial loads from the bull gear. The bull gear is rotatably coupled to the flexured standpipe via the ball bearing. The flexured standpipe flexes in response to radial loads from the bull gear.
1. A propulsion assembly comprising:
a rotor assembly;
a mast coupled to the rotor assembly;
a bull gear coupled to the mast, the bull gear subject to radial and axial loads;
a flexured standpipe extending through the bull gear; and
a ball bearing including inner and outer races interposed between the bull gear and the flexured standpipe, the ball bearing configured to absorb axial loads from the bull gear;
wherein, the bull gear is rotatably coupled to the flexured standpipe via the ball bearing; and
wherein, the flexured standpipe flexes in response to radial loads from the bull gear.
2. The propulsion assembly as recited in claim 1 wherein the bull gear further comprises a forward collar and an aft collar; and
wherein, the ball bearing is interposed between the flexured standpipe and the aft collar of the bull gear.
3. The propulsion assembly as recited in claim 2 wherein the inner surface of the aft collar forms a circumferential bearing retention lip.
4. The propulsion assembly as recited in claim 2 further comprising forward and aft roller bearings coupled to the forward and aft collars of the bull gear, the roller bearings configured to absorb the radial loads from the bull gear.
5. The propulsion assembly as recited in claim 4 wherein the ball bearing is aft of the aft roller bearing.
6. The propulsion assembly as recited in claim 2 wherein the outer race of the ball bearing is integral with the aft collar of the bull gear.
7. The propulsion assembly as recited in claim 1 wherein the mast, the bull gear, the flexured standpipe and the ball bearing are substantially coaxial.
8. The propulsion assembly as recited in claim 1 wherein the flexured standpipe extends through the mast.
9. The propulsion assembly as recited in claim 1 wherein the flexured standpipe does not rotate with the bull gear and the mast.
10. The propulsion assembly as recited in claim 1 wherein the ball bearing is clamped to the flexured standpipe and the bull gear.
11. The propulsion assembly as recited in claim 1 wherein the inner race of the ball bearing is clamped to the flexured standpipe and the outer race of the ball bearing is clamped to the bull gear.
12. The propulsion assembly as recited in claim 1 wherein the inner race abuts the outer surface of the flexured standpipe.
13. The propulsion assembly as recited in claim 1 wherein the inner race of the ball bearing is integral with the flexured standpipe.
14. The propulsion assembly as recited in claim 1 wherein the radial loads are transmitted from the bull gear to the flexured standpipe via the ball bearing.
15. The propulsion assembly as recited in claim 1 wherein the ball bearing is nonflexibly coupled to the bull gear.
16. A rotorcraft comprising:
a fuselage; and
a propulsion assembly coupled to the fuselage, the propulsion assembly comprising:
a rotor assembly;
a mast coupled to the rotor assembly;
a bull gear coupled to the mast, the bull gear subject to radial and axial loads;
a flexured standpipe extending through the bull gear; and
a ball bearing including inner and outer races interposed between the bull gear and the flexured standpipe, the ball bearing configured to absorb axial loads from the bull gear;
wherein the bull gear is rotatably coupled to the flexured standpipe via the ball bearing; and
wherein the flexured standpipe flexes in response to radial loads from the bull gear.
17. The rotorcraft as recited in claim 16 wherein the rotorcraft further comprises a tiltrotor aircraft and the rotor assembly further comprises a proprotor assembly.
18. The rotorcraft as recited in claim 16 wherein the rotorcraft further comprises a helicopter and the propulsion assembly further comprises a main rotor assembly.
19. The rotorcraft as recited in claim 16 wherein the propulsion assembly further comprises a pinion gear configured to mesh with the bull gear via helical gear teeth.
20. The rotorcraft as recited in claim 16 wherein the propulsion assembly further comprises a planetary gear system interposed between the mast and the bull gear.