Load distributing self-locking mount pin

Patent metadata

Field	Value
Publication number	US-11359656-B2
Application number	US-201816149702-A
Country	US
Kind code	B2
Filing date	Oct 2, 2018
Priority date	Oct 2, 2018
Publication date	Jun 14, 2022
Grant date	Jun 14, 2022

Abstract

A mounting pin assembly includes a first mounting component. The assembly also includes a second mounting component having a first leg located on a first side of the first mounting component and a second leg located on a second side of the first mounting component. The assembly further includes a mount pin extending through an aperture of the first leg, an aperture of the first mounting component, and an aperture of the second leg, the mount pin having a conical shoulder region in contact with a chamfer of the second leg. The assembly yet further includes a self-locking nut plate threaded to the mount pin.

First claim

What is claimed is:

1. A mounting pin assembly comprising:
a first mounting component;
a second mounting component having a first leg located on a first side of the first mounting component and a second leg located on a second side of the first mounting component;
a mount pin extending through an aperture of the first leg, an aperture of the first mounting component, and an aperture of the second leg, the mount pin having a conical shoulder region in contact with a chamfer of the second leg; and
a self-locking nut plate threaded to the mount pin at the second leg.

2. The mounting pin assembly of claim 1 , wherein an angle of the chamfer of the second leg corresponds to an angle of the conical shoulder region.

3. The mounting pin assembly of claim 1 , wherein the conical shoulder region extends between a first outer surface segment of the mount pin and a second outer surface segment of the mount pin, the first outer surface segment having a larger diameter than the second outer surface segment.

4. The mounting pin assembly of claim 3 , further comprising a spherical bearing disposed within the aperture of the first mounting component and adjacent the first outer surface segment of the mount pin.

5. The mounting pin assembly of claim 3 , further comprising a bushing disposed within the aperture of the first leg and adjacent the first outer surface segment of the mount pin.

6. The mounting component of claim 3 , further comprising a bushing disposed within the aperture of the second leg and adjacent the second outer surface segment of the mount pin.

7. The mounting pin assembly of claim 1 , wherein the second mounting component is a clevis coupled to the first mounting component.

8. A method of pin mounting components comprising:
forming a mount pin having a conical shoulder region;
extending the mount pin through a first mounting component and a second mounting component until the conical shoulder region is in contact with a chamfer of the second mounting component; and
locking the pin with a self-locking nut plate threaded to the mount pin;
wherein the chamfer defines a lead-in region of the aperture of the second leg; and
wherein forming the mount pin comprises forming the apertures of the second mounting component and forming the chamfer of the second leg in a single concurrent process with a chamfered drill bit.

9. The method of claim 8 , wherein extending the mount pin through the first mounting component and the second mounting component comprises extending the mount pin through an aperture of a first leg of the second mounting component, through an aperture of the first mounting component, and through an aperture of a second leg of the second mounting component, the first leg located on a first side of the first mounting component and the second leg located on a second side of the first mounting component.

10. The method of claim 8 , further comprising matching an angle of the conical shoulder region with an angle of the chamfer.

11. A gas turbine engine comprising:
a compressor section;
a combustor section;
a turbine section; and
a mounting pin assembly joining components of the gas turbine engine, the mounting pin assembly comprising:
a first mounting component;
a second mounting component having a first leg located on a first side of the first mounting component and a second leg located on a second side of the first mounting component;
a mount pin extending through an aperture of the first leg, an aperture of the first mounting component, and an aperture of the second leg, the mount pin having a conical shoulder region in contact with a chamfer of the second leg, wherein an angle of the chamfer corresponds to an angle of the conical shoulder region; and
a self-locking nut plate threaded to the mount pin.

12. The gas turbine engine of claim 11 , wherein the conical shoulder region extends between a first outer surface segment of the mount pin and a second outer surface segment of the mount pin, the first outer surface segment having a larger diameter than the second outer surface segment.

13. The gas turbine engine of claim 12 , further comprising a spherical bearing disposed within the aperture of the first mounting component and adjacent the first outer surface segment of the mount pin.

14. The gas turbine engine of claim 12 , further comprising a bushing disposed within the aperture of the first leg and adjacent the first outer surface segment of the mount pin.

15. The gas turbine engine of claim 12 , further comprising a bushing disposed within the aperture of the second leg and adjacent the second outer surface segment of the mount pin.

16. The gas turbine engine of claim 11 , wherein the second mounting component is a clevis coupled to the first mounting component.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Cerino Joseph N
• Luo Yong C
• Suarez Juan Pablo

Classifications

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• F16B5/02 Primary

  by means of fastening members using screw-thread ({F16B5/0004 takes precedence}; construction of screw-threaded connections F16B25/00 - F16B39/00) · CPC title

• F16C23/045 Primary

  for radial load mainly, e.g. radial spherical plain bearings · CPC title

• F16C2360/23

  Gas turbine engines · CPC title

• F16C11/02

  Trunnions; Crank-pins (fastening crank-pins to webs, crank-pins integral with cranks F16C3/06, F16C3/22) · CPC title