Method and apparatus for reducing high transient mount load in aircraft engine mounting systems

Patent metadata

Field	Value
Publication number	US-9783312-B2
Application number	US-201414327627-A
Country	US
Kind code	B2
Filing date	Jul 10, 2014
Priority date	Jul 10, 2014
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

Exemplary embodiments are provided to reduce the high transient mount load in an aircraft engine mounting system under extreme loading condition. The exemplary embodiments reduce the impact of the snubbing phenomenon without adding to the weight or space claim of the engine mounting system.

First claim

What is claimed is:

1. An apparatus for reducing the high transient mount load from an aircraft engine, the apparatus of the type including a housing with a sleeve for receiving a yoke bolt, the apparatus comprising:
a first wall having a first ovalized opening; and
a second wall opposite the first wall, having a second ovalized opening;

wherein (i) the first ovalized opening and the second ovalized opening are for receiving the yoke bolt therethrough, (ii) the first ovalized opening and second ovalized opening each have a cross section that is continuous and substantially semi-circular according to a minor axis on a first half and substantially oval shaped having a major axis on a second half, (iii) the major axes of the first ovalized opening and the second ovalized opening are sized and oriented based on a distance that the yoke bolt travels responsive to the high transient mount load, and (iv) the major axes are oriented to align substantially tangentially with a circular engine mount frame, in a direction opposite to a direction of rotation of engine fan blades.

2. The apparatus of claim 1 , wherein the major axis of the first ovalized opening and the major axis of the second ovalized opening are aligned and have a predetermined length.

3. The apparatus of claim 2 , wherein the predetermined length is within a range of about 1.1 to about 1.4 times the minor axis.

4. The apparatus of claim 3 , wherein the predetermined length is substantially equal to 1.3 times the minor axis.

5. The apparatus of claim 1 wherein the apparatus further comprises flexible packing material inside the housing.

6. The apparatus of claim 1 wherein the apparatus further comprises elastomer packing inside the housing.

7. The apparatus of claim 1 , wherein the second half of the first ovalized opening comprises an ovalized area of a first predetermined thinness and the second half of the second ovalized opening comprises an ovalized area of a second predetermined thinness.

8. The apparatus of claim 7 wherein the first wall has a first wall thickness, and wherein the first predetermined thinness is within the range of 0.2 to 0.4 times the first wall thickness.

9. The apparatus of claim 7 wherein the second wall has a second wall thickness, and wherein the second predetermined thinness is within the range of 0.2 to 0.4 times the second wall thickness.

Assignees

• Honeywell Int Inc

Inventors

• Kumar Avinash
• Brockett Theodore
• Chinthapally Srinivas
• Kumbham Krishna Mohan
• Khare Milind
• Ganji Venkatarao
• Kandula Rama Sateesh Venkata

Classifications

• B64D27/402

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

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• B64D2027/266

  Operations & Transport · mapped topic

• B64D2027/268

  Operations & Transport · mapped topic