Aircraft engine nacelle bulkheads and methods of assembling the same

Patent metadata

Field	Value
Publication number	US-9708072-B2
Application number	US-201414266404-A
Country	US
Kind code	B2
Filing date	Apr 30, 2014
Priority date	Apr 30, 2014
Publication date	Jul 18, 2017
Grant date	Jul 18, 2017

Abstract

An engine nacelle includes an exterior wall and an interior wall. A forward bulkhead is coupled between the interior wall and the exterior wall, wherein the forward bulkhead comprises a curvilinear body portion that extends between the interior wall and the exterior wall. The engine nacelle also includes an aft bulkhead coupled between the interior wall and the exterior wall, wherein the aft bulkhead comprises a curvilinear body portion that extends between the interior wall and the exterior wall.

First claim

What is claimed is:

1. An engine nacelle comprising:
an exterior wall;
an interior wall;
a forward bulkhead coupled between said interior wall and said exterior wall wherein said forward bulkhead comprises a curvilinear body portion that extends between said interior wall and said exterior wall; and
an aft bulkhead comprising a first end coupled to said interior wall and a second end coupled to said exterior wall, wherein said aft bulkhead comprises a curvilinear body portion that extends between said interior wall and said exterior wall from said first end to said second end.

2. The engine nacelle in accordance with claim 1 further comprising:
a lipskin assembly comprising a first segment and a second segment wherein said first segment is operable as a first portion of said interior wall and said second segment is operable as said exterior wall; and
a structural inner barrel operable as a second portion of said interior wall.

3. The engine nacelle in accordance with claim 2 , wherein said forward bulkhead is coupled between said second segment and one of said first segment or said inner barrel.

4. The engine nacelle in accordance with claim 2 , wherein said aft bulkhead is coupled between said second segment and said inner barrel.

5. The engine nacelle in accordance with claim 1 , wherein said forward bulkhead body portion and said aft bulkhead body portion each protrude in an upstream direction opposite a direction of airflow through said engine nacelle.

6. The engine nacelle in accordance with claim 1 , wherein said forward bulkhead further comprises an inner flange coupled between said body portion and said interior wall and an outer flange coupled between said body portion and said exterior wall, and wherein said aft bulkhead further comprises an inner flange coupled between said body portion and said interior wall and an outer flange coupled between said body portion and said exterior wall.

7. The engine nacelle in accordance with claim 1 , wherein said aft bulkhead body portion comprises a forward wall, an aft wall, and strengthening structure extending therebetween.

8. The engine nacelle in accordance with claim 1 , wherein said forward bulkhead is formed from a ceramic matric composite.

9. The engine nacelle in accordance with claim 1 , wherein said aft bulkhead is formed from a super-plastic formed diffusion-bonded titanium.

10. An aircraft comprising:
an engine nacelle comprising:
a lipskin comprising a first segment and a second segment;
a structural inner barrel;
a forward bulkhead comprising a curvilinear body portion that extends between one of said first segment or said inner barrel and said second segment; and
an aft bulkhead axially-spaced from said forward bulkhead, said aft bulkhead comprising a first end coupled to said inner barrel and a second end coupled to said lipskin, wherein said aft bulkhead comprises a curvilinear body portion that extends between said structural inner barrel and said second segment from said first end to said second end.

11. The aircraft in accordance with claim 10 , wherein said forward bulkhead body portion and said aft bulkhead body portion each protrude in an upstream direction opposite a direction of airflow through said engine nacelle.

12. The aircraft in accordance with claim 10 , wherein said forward bulkhead further comprises an inner flange coupled between said body portion and one of said first segment or said structural inner barrel and an outer flange coupled between said body portion and said second segment, and wherein said aft bulkhead further comprises an inner flange coupled between said body portion and said structural inner barrel and an outer flange coupled between said body portion and said second segment.

13. The aircraft in accordance with claim 12 , wherein said forward bulkhead further comprises a reinforcing wall coupled between said inner and said outer flanges.

14. The aircraft in accordance with claim 10 , wherein said aft bulkhead body portion comprises a forward wall, an aft wall, and strengthening structure extending therebetween.

15. A method of assembling an engine nacelle having an interior wall and an exterior wall, said method comprising:
coupling a forward bulkhead between the interior wall and the exterior wall, wherein the forward bulkhead includes a curvilinear body portion that extends between the interior wall and the exterior wall; and
coupling an aft bulkhead between the interior wall and the exterior wall, wherein the aft bulkhead includes a first end coupled to the interior wall and a second end coupled to the exterior wall, and a curvilinear body portion that extends between the interior wall and the exterior wall from the first end to the second end.

16. The method in accordance with claim 15 , wherein coupling a forward bulkhead between the interior wall and the exterior wall further comprises coupling the forward bulkhead between one of a first segment of a lipskin assembly or a structural inner barrel and a second segment of the lipskin assembly.

17. The method in accordance with claim 15 , wherein coupling an aft bulkhead between the interior wall and the exterior wall further comprises coupling the aft bulkhead between a structural inner barrel and a lipskin assembly.

18. The method in accordance with claim 15 , wherein coupling a forward bulkhead between the interior wall and the exterior wall further comprises coupling the forward bulkhead between the interior wall and the exterior wall such that the body portion protrudes in an upstream direction opposite a direction of airflow through the engine nacelle.

19. The method in accordance with claim 15 , wherein coupling an aft bulkhead between the interior wall and the exterior wall further comprises coupling the aft bulkhead between the interior wall and the exterior wall such that the body portion protrudes in an upstream direction opposite a direction of airflow through the engine nacelle.

20. The method in accordance with claim 15 further comprising:
coupling a forward reinforcement wall between the interior and exterior walls aft of the forward bulkhead body portion; and
coupling an aft reinforcement wall between the interior and exterior walls aft of the aft bulkhead body portion.

Assignees

• Boeing Co

Inventors

• Lumbab Alex C
• Leisten Bradley Scott

Classifications

• B64D29/02

  associated with wings · CPC title

• F01D25/02

  De-icing means for engines having icing phenomena · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• B64D29/00 Primary

  Power-plant nacelles, fairings or cowlings · CPC title

• F01D25/005

  Selecting particular materials · CPC title