Torque tube bearing assembly

• US 6,821,084 B2
• Filed: 12/11/2002
• Issued: 11/23/2004
• Est. Priority Date: 12/11/2002
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Park, Sang Yeng, Bathori, Julius, Headley, Mitchell Jay
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): MCALEENAN, JAMES M
• Application Number:
  US10/316,778
• Publication Number:
  US 20040115040A1
• Time in Patent Office: 713 Days
• Field of Search: 415/160, 415/173.1, 415/173.2, 415/173.3, 415/123, 415/149, 415/150, 415/174.2, 415/126
• US Class Current: 415/160
• CPC Class Codes: F01D 25/16 Arrangement of bearings; Supporting or mounting bearings in casings bearings per se F16C
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F16C 23/045 for radial load mainly, e.g. radial spherical plain bearings
• CPC Class Codes: F16C 2360/23 Gas turbine engines
• CPC Class Codes: F16C 35/02 in the case of sliding-contact bearings

Abstract

A bearing assembly for use in a gas turbine engine to rotatably mount a torque tube in an access hole extending through a fan duct. The torque tube connects a variable stator vane bell crank positioned inside the fan duct to an actuator positioned outside the fan duct. The bearing assembly includes a bearing having a spherical external engagement surface and a housing having a flange and an annular interior surface having an inner edge and an outer edge. The interior surface is sized and shaped for rotatably receiving the spherical external engagement surface of the bearing so the spherical engagement surface and the annular interior surface make contact along an annular contact area centered on a contact plane lying between the inner and outer edges. The contact plane is tilted with respect to the flange at an angle greater than five degrees.

Claims

1. A bearing assembly for use in a gas turbine engine to rotatably mount a torque tube in an access hole extending through a fan duct of the engine, said torque tube connecting a variable stator vane bell crank positioned inside the fan duct to an actuator positioned outside the fan duct, said bearing assembly comprising:

a bearing adapted for mounting on the torque tube having a spherical external engagement surface; and

a housing having a flange adapted for mounting on the fan duct adjacent the access hole and an annular interior surface having an inner edge and an outer edge, said interior surface being sized and shaped for rotatably receiving the spherical external engagement surface of the bearing so the spherical engagement surface and the annular interior surface make contact along an annular contact area centered on a contact plane lying between said inner edge and said outer edge of the interior surface, said contact plane being tilted with respect to the flange at an angle greater than five degrees.

2. A bearing assembly as set forth in claim 1 wherein the angle at which the contact plane tilts is greater than about ten degrees.

3. A bearing assembly as set forth in claim 2 wherein the angle at which the contact plane tilts is about thirteen degrees.

4. A bearing assembly as set forth in claim 3 wherein the angle at which the contact plane tilts is about 13.08 degrees.

5. A bearing assembly as set forth in claim 1 wherein the annular interior surface of the housing includes a relieved portion for loading the bearing into the housing.

6. A bearing assembly as set forth in claim 5 wherein the relieved portion faces inward when the flange of the housing is mounted on the fan duct.

7. A bearing assembly as set forth in claim 1 wherein the housing includes a rabbet surface for engaging the access hole when the flange is mounted on the fan duct.

8. A bearing assembly as set forth in claim 1 wherein a portion of the housing flange is positioned outside the interior surface of the housing when the flange is mounted on the fan duct and a portion of the housing flange is positioned inside the interior surface of the housing when the flange is mounted on the fan duct.

9. A bearing assembly as set forth in claim 8 wherein the portion of the housing flange positioned outside the interior surface of the housing includes a rearward side of the housing flange and the portion of the housing flange positioned inside the interior surface of the housing includes a forward side of the housing flange.

10. A torque tube assembly for use in a gas turbine engine to connect a variable stator vane bell crank positioned inside a fan duct of the engine to of a variable stator vane actuator positioned outside the fan duct, said torque tube assembly comprising:

an elongate torque tube having an inner end adapted for connection to the variable stator vane bell crank, an outer end adapted for connection to the variable stator vane actuator, and a longitudinal axis extending between said inner end and said outer end;

a bearing mounted on the torque tube having a spherical external engagement surface; and

a housing having a flange adapted for mounting to the fan duct and an annular interior surface having an inner edge and an outer edge, said interior surface being sized and shaped for rotatably receiving the spherical external engagement surface of the bearing so that when the spherical engagement surface and the annular interior surface make contact along an annular contact area centered on a contact plane extending parallel to the outside edge of the interior surface of the housing, the torque tube axis extends at an angle measured from the flange of less than 85 degrees.

11. A torque tube assembly as set forth in claim 10 wherein the angle at which the torque tube axis extends is less than about eighty degrees.

12. A torque tube assembly as set forth in claim 11 wherein the angle at which the torque tube axis extends is about 77 degrees.

13. A torque tube assembly as set forth in claim 10 wherein the torque tube axis extends perpendicular to the outside edge of the interior surface of the housing during at least one steady state power setting of the engine.

14. A torque tube assembly as set forth in claim 13 wherein the torque tube assembly is adapted for use in an aircraft engine and the torque tube axis extends perpendicular to the outside edge of the interior surface of the housing during steady state cruise operation of the engine.

15. A torque tube assembly as set forth in claim 13 wherein the outer end of the torque tube is positioned behind the inner end of the torque tube during said steady state power setting of the engine.

16. A torque tube assembly as set forth in claim 10 wherein the annular interior surface of the housing includes a relieved portion for loading the bearing into the housing.

17. A torque tube assembly as set forth in claim 10 wherein the relieved portion faces inward when the flange of the housing is mounted on the fan duct.

18. A torque tube assembly as set forth in claim 10 wherein the housing includes an annular rabbet surface adjacent the flange for positioning housing assembly on the fan duct.

19. A torque tube assembly as set forth in claim 10 in combination with the gas turbine engine.