Aircraft engine mounting system

Patent metadata

Field	Value
Publication number	US-9533768-B2
Application number	US-201414457287-A
Country	US
Kind code	B2
Filing date	Aug 12, 2014
Priority date	Aug 12, 2014
Publication date	Jan 3, 2017
Grant date	Jan 3, 2017

Abstract

An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves.

First claim

What is claimed is:

1. An aircraft comprising:
a fuselage;
a wing structure fixedly secured to and extending from the fuselage, the wing structure substantially defining a flat plane;
an engine configured for mounting to the wing structure, the engine having a substantially fixed thrust orientation relative to the wing structure;
a first support directly fixed to the wing structure; the first support adapted to secure the engine to the wing structure in a position above the wing structure;
wherein the first support extends substantially orthogonally with respect to the flat plane;
a second support extending above the wing structure, and defining a single elongate member having two ends, the first end secured to the engine, and the second end directly secured to the fuselage;
wherein the second support extends substantially parallel to the flat plane; and
wherein the first and second supports are load-bearing structures.

2. The aircraft of claim 1 , wherein the first support is an upwardly extending strut, and the second support is a laterally extending bridge.

3. The aircraft of claim 1 , wherein the bridge comprises a load carrying member between the engine and the fuselage.

4. The aircraft of claim 3 , further comprising at least two passenger floors, a carry through beam secured to the fuselage, the beam extending between the floors, and having laterally spaced ends joined to an end of each bridge.

5. The aircraft of claim 3 , further including a crown support fixed to the top of the aircraft fuselage, wherein each bridge is connected to the crown support.

6. The aircraft of claim 3 , wherein each bridge comprises a truss system.

7. The aircraft of claim 3 , wherein the bridge defines a concave curvature along a fore-aft axis.

8. An aircraft propulsor mounting system, comprising:
an aircraft fuselage;
a wing structure fixedly secured to and extending from the fuselage, the wing structure substantially defining a flat plane;
an aircraft propulsor configured for mounting to the wing structure, the propulsor having a substantially fixed thrust orientation relative to the wing structure;
a first support directly fixed to the wing structure; the first support adapted to secure the aircraft propulsor to the wing structure in a position above the wing structure;
wherein the first support extends substantially orthogonally with respect to the flat plane;
a second support extending above the wing structure, and defining a single elongate member having two ends, the first end secured to the aircraft propulsor, and the second end directly secured to the fuselage;
wherein the second support extends substantially parallel to the flat plane; and
wherein the first and second supports are load-bearing structures.

9. The aircraft propulsor mounting system of claim 8 , wherein the first support is an upwardly extending strut, and the second support is a laterally extending bridge.

10. The aircraft propulsor mounting system of claim 8 , wherein the bridge comprises a load carrying member between the engine and the fuselage.

11. The aircraft propulsor mounting system of claim 10 , further comprising at least two passenger floors, a carry through beam secured to the fuselage, the beam extending between the floors, and having laterally spaced ends joined to an end of each bridge.

12. The aircraft propulsor mounting system of claim 10 , further including a crown support fixed to the top of the aircraft fuselage, wherein each bridge is connected to the crown support.

13. The aircraft propulsor mounting system of claim 10 , wherein each bridge comprises a truss system.

14. The aircraft propulsor mounting system of claim 10 , wherein the bridge defines a concave curvature along a fore-aft axis.

15. A method of enhancing aircraft performance using an above wing propulsion engine, the method comprising the steps of:
providing an aircraft fuselage having a wing fixedly joined thereto, the wing extending from the fuselage, the wing substantially defining a flat plane;
providing a first engine support on the wing, the first engine support configured to secure a propulsion engine directly to the wing in position above the wing, the propulsion engine having a substantially fixed thrust orientation relative to the wing;
wherein the first support extends substantially orthogonally with respect to the flat plane; and
providing a second engine support, the second engine support configured to extend from the vehicle fuselage above the wing to secure the propulsion engine to the vehicle fuselage separately from first engine support;
forming the second engine support as a single elongate member having two ends, and securing the first end to the aircraft propulsor, and the second end directly to the fuselage; wherein the second support extends substantially parallel to the flat plane; and
forming the first and second supports as load-bearing structures.

16. The method of claim 15 , wherein the first engine support is an upwardly extending wing strut, and wherein the second engine support is a laterally extending bridge.

17. The method of claim 16 , wherein the bridge defines an upwardly extending bowed curvature.

18. The method of claim 16 , wherein the bridge is formed of metal.

19. The method of claim 16 , wherein the bridge is formed of a composite structure.

20. The method of claim 19 , in which the bridge is formed of one of a woven, braided, sandwiched, or isogrid composite structure.

Assignees

• Boeing Co

Inventors

• Barmichev Sergey D
• Kirkbride David W
• Sankrithi Mithra M K V

Classifications

• B64D27/402

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

• B64D27/18 Primary

  within, or attached to, wings · CPC title

• B64D2027/262

  Operations & Transport · mapped topic

• B64D2027/005

  Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR] · CPC title

• B64D29/04

  associated with fuselages · CPC title