One piece inlet lip skin design

Patent metadata

Field	Value
Publication number	US-9664113-B2
Application number	US-201414214723-A
Country	US
Kind code	B2
Filing date	Mar 15, 2014
Priority date	Mar 15, 2014
Publication date	May 30, 2017
Grant date	May 30, 2017

Abstract

An aircraft engine inlet incorporates a lip skin having a skin web with a plurality of stiffeners integrally extending from the skin web. An aft edge land integrally extends from the skin web at an outer rim and an inner edge land integrally extends from the skin web at an inner rim. A central land integrally extends from the skin web with the plurality of stiffeners extending between said aft edge land and the central land.

First claim

What is claimed is:

1. An aircraft engine net comprising:
a lip skin having
a skin web;
a plurality of stiffeners integral to and extending from the skin web;
an aft edge land integral to and extending from the skin web at an outer rim;
an inner edge land integral to and extending from the skin web at an inner rim;
a central land integral to and extending from the skin web, said plurality of stiffeners extending longitudinally fore and aft between said aft edge land and said central land; and
a forward bulkhead engaged between the central land and the inner edge land.

2. The aircraft engine inlet as defined in claim 1 wherein the plurality of integral stiffeners comprises two stiffeners and the stiffeners extend substantially fore and aft on the skin web.

3. The aircraft engine inlet as defined in claim 1 wherein the stiffeners are asymmetrically located about an inlet axis.

4. The aircraft engine inlet as defined in claim 3 wherein the stiffeners are located at an offset angle of about 11 degrees from vertical.

5. The aircraft engine inlet as defined in claim 4 where in the stiffeners are separated by a clocking angle of about 25 degrees.

6. The aircraft engine inlet as defined in claim 1 further comprising an inner barrel, said inner barrel abutting the inner rim and said forward bulkhead having an inner flange spanning and connecting the inner edge land and a mating surface on the inner barrel.

7. The aircraft engine inlet as defined in claim 6 further comprising an outer barrel abutting the outer rim and a first stringer engaging the aft edge land and outer barrel.

8. The aircraft engine inlet as defined in claim 7 further comprising an aft bulkhead inter connected to a second stringer and an aft edge of the outer barrel.

9. The aircraft engine inlet as defined in claim 8 further comprising a bracket attaching the inner barrel to internal nacelle structure and an inner attach angle engaging the aft bulkhead and the bracket.

10. A method for fabricating an engine inlet comprising:
forming a lip skin by spin forming with a thickness at least as thick as a thickest land or stiffener;
determining a pattern of lands and stiffeners to meet structural requirements for aerodynamic, sonic, and step loads;
forming an aft edge land, an inner edge land, a central land and a plurality of stiffeners integrally in the lip skin extending from a skin web pursuant to the determined pattern, said plurality of stiffeners extending longitudinally fore and aft between the aft edge land and the central land;
wherein the aft edge land extends from an outer rim of the skin web and the inner edge land extends from an inner rim of the skin web; and
attaching a forward bulkhead between the central land and the inner edge land.

11. The method as defined in claim 10 wherein the step of forming further comprises machining the plurality of lands and stiffeners integrally in the lip skin.

12. The method as defined in claim 10 wherein the step of forming further comprises chemical milling the plurality of lands and stiffeners integrally in the lip skin.

13. The method as defined in claim 11 wherein the plurality of lands and stiffeners are machined to a common thickness.

14. The method as defined in claim 11 wherein the plurality of lands and stiffeners are machined to differing thicknesses.

15. The method as defined in claim 10 further comprising:
abutting the lip skin at an outer rim to an outer barrel and an inner rim at an inner barrel.

16. The method as defined in claim 15 further comprising engaging a first stringer to the aft edge land on the lip skin and the outer barrel.

17. The method as defined in claim 16 further comprising engaging an outer periphery of the forward bulkhead to a mating surface on the inner barrel.

18. The method as defined in claim 17 further comprising attaching an aft bulkhead to the outer barrel using a second stringer and to an L bracket on the inner barrel using an inner attach angle.

19. The method as defined in claim 18 further comprising attaching the L bracket to internal nacelle structure and the second stringer to an external skin of the nacelle.

Assignees

• Boeing Co

Inventors

• Wilson Ronnie
• Stemple Alan D

Classifications

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F02C7/20 Primary

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• Y10T29/49229

  Prime mover or fluid pump making · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• B64D33/02 Primary

  of combustion air intakes · CPC title