Hub assembly with grease lubricated roller bearing and tension-torsion strap

Patent metadata

Field	Value
Publication number	US-10059438-B2
Application number	US-201113337215-A
Country	US
Kind code	B2
Filing date	Dec 26, 2011
Priority date	Dec 26, 2011
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A rotary system and method to control feathering and centrifugal forces of a rotor blade during flight. The rotary system having a hub assembly, which includes a hollow yoke arm to receive a spindle section of the rotor blade. A tension-torsion strap extends through the hollow yoke arm and couples the rotor blade and the hub assembly. The method includes allowing the spindle section of the rotor blade to pivot within the hollow yoke arm and controlling rotational and centrifugal movement of the rotor blade with the tension-torsion strap.

First claim

What is claimed is:

1. A rotary system for a rotary aircraft, comprising:
a rotor mast;
a constant velocity joint;
a rotor blade having a hollow spindle section; and
a hub assembly rotatably attached to the rotor mast and operably associated with the rotor blade, the hub assembly having:
a housing attached to the rotor mast and attached to the constant velocity joint;
a spinner configured to divert air to the rotor blade during flight, the spinner being positioned above the housing and having an inlet extending through a thickness of the spinner, the inlet being configured to allow air to pass therethrough to the housing;
a hollow yoke arm having a flange and forming a hollow cavity, the hollow yoke arm being configured to receive the hollow spindle section of the rotor blade;
a bearing assembly disposed within the hollow cavity of the hollow yoke arm and positioned between the hollow spindle section and the hollow yoke arm, the bearing assembly having:
a first bearing; and
a second bearing spaced at a distance relative to the first bearing;

a coning element bonded to an outer surface of the housing, the coning element being configured to receive and sandwich the flange of the hollow yoke arm between an elastomeric material and configured to reduce a coning force exerted on the hollow yoke arm during flight; and
a tension-torsion strap coupled to the constant velocity joint and coupled to the rotor blade, the tension-torsion strap being configured to extend through the hollow yoke arm and to extend through the hollow spindle section of the rotor blade;

wherein the constant velocity joint is disposed within the housing;
wherein the tension-torsion strap is fastened to the constant velocity joint;
wherein the coning element peripherally extends around at least a portion of an outer perimeter of the hollow yoke arm;
wherein the coning element enables the hollow yoke arm to pivot;
wherein the spindle section pivots within the hollow yoke arm as a blade feathering force is exerted on the hub assembly via the rotor blade during flight; and
wherein the tension-torsion strap restricts the pivoting movement of the rotor blade as the blade feathers during flight.

2. The rotary system of claim 1 , wherein the tension-torsion strap is composed of an elastic material.

3. The rotary system of claim 2 , wherein the tension-torsion strap is composed of fiberglass material.

4. The rotary system of claim 1 , the tension-torsion strap comprising:
a base portion coupled to the constant velocity joint via a fastening means; and
a strap arm extending from the base and passes through the spindle section of the rotor blade.

5. The rotary system of claim 1 , the tension-torsion strap comprising:
a first longitudinal member; and
a second longitudinal member extending alongside the first longitudinal member at a spaced relation therefrom.

6. The rotary system of claim 1 , wherein the bearing assembly allows rotation of the spindle section relative to the hollow yoke arm.

7. The rotary system of claim 6 , the bearing assembly comprising:
a first roller bearing; and
a second roller bearing;
wherein the first roller bearing and the second roller bearing are positioned at a spaced distance relative to each other.

8. The rotary system of claim 7 , wherein the first roller bearing peripherally extends the entire circumferential length of an outer surface of the spindle section; and
wherein the second roller bearing peripherally extends the entire circumferential length of the outer surface of the spindle section.

9. A method to control centrifugal and feathering movement of a rotor blade relative to a hub assembly coupled thereto, the method comprising:
providing the rotary system of claim 1 ;
elastically attaching the hollow yoke arm to the coning element bonded to an outer surface of the housing rotatably coupled to the rotor mast;
reducing the coning force exerted on the hollow yoke arm during flight via the coning element;
receiving the spindle section of the rotor blade in the hollow yoke arm;
securing a first end of the tension-torsion strap to the housing;
extending the tension-torsion strap through the hollow yoke arm; and
coupling a second end of the tension-torsion strap to the spindle section of the rotor blade;
wherein the coning element peripherally extends around at least a portion of an outer perimeter of the hollow yoke arm;
wherein the coning element enables the hollow yoke arm to pivot;
wherein the rotor blade pivots within the hollow yoke arm; and
wherein the tension-torsion strap controls the pivoting movement of the rotor blade during flight.

10. The method of claim 9 , further comprising:
controlling a rotor blade coning force with an elastomeric element operably associated with the yoke arm.

11. The method of claim 9 , further comprising:
attaching the rotor blade to the hollow yoke arm with a bearing assembly;
wherein the bearing assembly allows pivoting movement of the rotor blade relative to the hollow yoke arm.

12. A rotary system for a rotary aircraft, comprising:
a rotor blade having:
a hollow spindle section;

a hub assembly having:
a housing;
a hollow yoke arm having a flange and forming a hollow cavity and configured to receive the hollow spindle section therein;
a bearing assembly disposed within the hollow cavity of the hollow yoke arm and positioned between the hollow spindle section and the hollow yoke arm, the bearing assembly having:
a first bearing; and
a second bearing spaced at a distance relative to the first bearing;

a coning element bonded to an outer surface of the housing, the coning element being configured to sandwich the flange of the hollow yoke arm between an elastomeric material and configured to reduce a coning force exerted on the hollow yoke arm during flight; and
a tension-torsion strap, comprising;
a first longitudinal member;
a second longitudinal member extending alongside the first longitudinal member; and
a gap located between the first longitudinal member and the second longitudinal member, the tension-torsion strap coupled to both the rotor blade and the hub assembly;

wherein the coning element peripherally extends around at least a portion of an outer perimeter of the hollow yoke arm;
wherein the coning element enables the hollow yoke arm to pivot;
wherein the spindle section pivots within the hollow yoke arm; and
wherein the tension-torsion strap controls the pivoting movement of the spindle caused by feathering movement of the rotor blade during flight.

13. The rotary system of claim 12 , wherein the bearing assembly allows the spindle section to pivot relative to the hollow yoke arm.

14. The rotary system of claim 13 , the bearing assembly comprising:
a first roller bearing; and
a second roller bearing;
wherein the first roller bearing and the second roller bearing are positioned at a spaced distance relative to each other.

15. The rotary system of claim 12 , the tension-torsion strap comprising:
a base; and
an arm attached to and extending from the base;
wherein the arm extends through the spindle section and attaches the rotor to the hub assembly.

16. The rotary system of claim 12 , the spindle section having:
a hollow cavity;
wherein the tension-torsion strap passes through the hollow cavity.

Assignees

• Rauber Richard
• Stamps Frank B
• Popelka David
• Tisdale Patrick
• Donovan Tom
• Textron Innovations Inc

Inventors

• Rauber Richard
• Stamps Frank B
• Popelka David
• Tisdale Patrick
• Donovan Tom

Classifications

• B64C11/04

  Blade mountings · CPC title

• B64C27/33 Primary

  having flexing arms · CPC title

• B64C27/35

  having elastomeric joints · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title