Forming a nacelle inlet for a turbine engine propulsion system

Patent metadata

Field	Value
Publication number	US-9845728-B2
Application number	US-201514884206-A
Country	US
Kind code	B2
Filing date	Oct 15, 2015
Priority date	Oct 15, 2015
Publication date	Dec 19, 2017
Grant date	Dec 19, 2017

Abstract

Methods are provided forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis. The nacelle inlet structure includes an inlet lip portion and an outer barrel portion. One of the method may include steps of: forming the inlet lip portion; forming the outer barrel portion; arranging the inlet lip portion axially adjacent the outer barrel portion; and friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion.

First claim

We claim:

1. A method for forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis, the nacelle inlet structure comprising an inlet lip portion and an outer barrel portion, the method comprising:
forming the inlet lip portion;
forming the outer barrel portion;
arranging the inlet lip portion axially adjacent the outer barrel portion; and
friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion;
wherein the inlet lip portion is configured with an inner lip portion and an outer lip portion that axially overlaps and circumscribes the inner lip portion; and
wherein the friction stir welding comprises friction stir welding an axial aft end region of the outer lip portion to an axial forward end region of the outer barrel portion.

2. The method of claim 1 , wherein the nacelle inlet structure has a smooth, seamless outer surface at the weld joint.

3. The method of claim 2 , further comprising performing a finishing process to the weld joint to facilitate in provision of the smooth, seamless outer surface at the weld joint.

4. The method of claim 1 , wherein the friction stir welding is performed using a rotating tool located radially within the inlet lip portion and the outer barrel portion.

5. The method of claim 4 , further comprising disposing a support device radially outside of and abutted against the inlet lip portion and the outer barrel portion during the friction stir welding.

6. The method of claim 1 , wherein the fanning of the inlet lip portion comprises shaping material into an annular or parti-annular body with a cupped sectional geometry.

7. The method of claim 1 , wherein the forming of the outer barrel portion comprises shaping material into a tubular or parti-tubular body.

8. The method of claim 1 , wherein the nacelle inlet structure includes a component and a land which is thicker than another axially adjacent region of the nacelle inlet structure, the land is configured integral with the inlet lip portion or the outer barrel portion, and the component is mechanically fastened to the land.

9. The method of claim 1 , wherein the axial aft end region is thicker than another axially adjacent region of the outer lip portion.

10. The method of claim 1 , further comprising:
disposing a bulkhead radially between the inner lip portion and the outer lip portion; and
bonding the bulkhead to the outer lip portion.

11. The method of claim 1 , further comprising:
perforating the outer lip portion to provide an array of perforations;
disposing a plenum structure radially within the outer lip portion; and
bonding the plenum structure to the outer lip portion;
wherein the plenum structure forms a plenum with at least the outer lip portion, and the plenum is fluidly coupled with the array of perforations.

12. The method of claim 11 , wherein a weld joint between the plenum structure and the outer lip portion are formed by friction stir welding, and the weld joint extends circumferentially between the plenum structure and the outer lip portion.

13. The method of claim 1 , further comprising:
perforating the outer barrel portion to provide an array of perforations;
disposing a plenum structure radially within the outer barrel portion; and
bonding the plenum structure to the outer barrel portion;
wherein the plenum structure forms a plenum with at least the outer barrel portion, and the plenum is fluidly coupled with the array of perforations.

14. A method for forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis, the nacelle inlet structure comprising an inlet lip portion and an outer barrel portion, the method comprising:
forming the inlet lip portion;
forming the outer barrel portion;
arranging the inlet lip portion axially adjacent the outer barrel portion;
friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion;
perforating the outer barrel portion to provide an array of perforations;
disposing a plenum structure radially within the outer barrel portion; and
bonding the plenum structure to the outer barrel portion;
wherein the plenum structure forms a plenum with at least the outer barrel portion, and the plenum is fluidly coupled with the array of perforations; and
wherein a weld joint between the plenum structure and the outer barrel portion is formed by friction stir welding, and the weld joint extends circumferentially between the plenum structure and the outer barrel.

15. A method for forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis, the nacelle inlet structure comprising an inlet lip portion and an outer barrel portion, the method comprising:
forming the inlet lip portion;
forming the outer barrel portion;
arranging the inlet lip portion axially adjacent the outer barrel portion;
friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion;
perforating the outer barrel portion to provide an array of perforations;
disposing a plenum structure radially within the outer barrel portion; and
bonding the plenum structure to the outer barrel portion;
wherein the plenum structure forms a plenum with at least the outer barrel portion, and the plenum is fluidly coupled with the array of perforations; and
wherein a plurality of weld joints between the plenum structure and the outer barrel portion are formed by friction stir spot welding.

16. A method for forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis, the nacelle inlet structure comprising an inlet lip portion and an outer barrel portion, the method comprising:
forming the inlet lip portion;
forming the outer barrel portion;
arranging the inlet lip portion axially adjacent the outer barrel portion;
friction stir welding the inlet lip portion to the outer barrel portion to provide a circumferentially extending weld joint between the inlet lip portion and the outer barrel portion;
perforating the outer barrel portion to provide an array of perforations;
disposing a plenum structure radially within the outer barrel portion; and
bonding the plenum structure to the outer barrel portion;
wherein the plenum structure forms a plenum with at least the outer barrel portion, and the plenum is fluidly coupled with the array of perforations;
wherein the bonding comprises friction stir welding; and
wherein a weld joint between the plenum structure and the outer barrel portion and the weld joint between the inlet lip portion and the outer barrel portion are concurrently formed and part of a common weld joint.

17. The method of claim 1 , wherein the inlet lip portion comprises a first metal and the outer barrel portion comprises a second metal that is different than the first metal.

18. The method of claim 1 , wherein the inlet lip portion and the outer barrel portion comprise a common metal.

19. A method for forming a metallic nacelle inlet structure for a turbine engine aircraft propulsion system with an axis, the nacelle inlet structure comprising an inlet lip portion and an outer barrel portion, the method comprising:
arranging the inlet lip portion axially adjacent th

Assignees

• Rohr Inc

Inventors

• Brown Keith T
• Pujar Vijay V
• Hayes Russell B
• Rose David L

Classifications

• F02C7/04 Primary

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

• F05D2230/60

  Assembly methods · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title

• F05D2230/239

  Inertia or friction welding · CPC title

• F05D2300/10

  Metals, alloys or intermetallic compounds · CPC title