Nacelle inlet structures, engine assemblies and vehicles including the same, and related methods

Patent metadata

Field	Value
Publication number	US-12338744-B2
Application number	US-202418795021-A
Country	US
Kind code	B2
Filing date	Aug 5, 2024
Priority date	May 4, 2021
Publication date	Jun 24, 2025
Grant date	Jun 24, 2025

Abstract

Nacelle inlet structures comprise an inlet inner barrel, an inlet outer barrel at least substantially enclosing the inlet inner barrel, an aft bulkhead extending between and operatively coupled to each of the inlet inner barrel and the inlet outer barrel, and an annular load absorber that is operatively coupled to each of the aft bulkhead and the inlet inner barrel. The aft bulkhead is operatively coupled to the inlet inner barrel via the annular load absorber, and the annular load absorber has a U-shaped cross-section that is open toward the inlet outer barrel.

First claim

The invention claimed is:

1. A nacelle inlet structure of an engine assembly, the nacelle inlet structure comprising:
an inlet inner barrel extending circumferentially around an engine axis of the engine assembly and extending at least partially along a direction parallel to the engine axis;
an inlet outer barrel extending circumferentially around the engine axis and at least partially along the direction parallel to the engine axis;
an aft bulkhead extending between and operatively coupled to each of the inlet inner barrel and the inlet outer barrel; and
a U-shaped annular load absorber that is operatively coupled to each of the aft bulkhead and the inlet inner barrel; wherein the aft bulkhead is operatively coupled to the inlet inner barrel via the U-shaped annular load absorber; and wherein the U-shaped annular load absorber is open toward the inlet outer barrel;
wherein the inlet inner barrel includes:
a tubular portion that extends at least partially along a direction parallel to the engine axis, wherein the U-shaped annular load absorber is spaced-away from the tubular portion; and
an inlet attachment flange extending from the tubular portion and configured to be operatively coupled to an engine case of the engine assembly to operatively couple the nacelle inlet structure to the engine case, wherein the U-shaped annular load absorber is coupled to the inlet attachment flange.

2. The nacelle inlet structure of claim 1 , further comprising a plurality of flange bolt assemblies; wherein the inlet attachment flange is configured to be operatively coupled to the engine case via the plurality of flange bolt assemblies; wherein each flange bolt assembly of the plurality of flange bolt assemblies includes a respective flange bolt with a respective flange bolt head and a respective flange bolt shank extending away from the respective flange bolt head along a respective flange bolt axis; wherein the inlet attachment flange at least partially defines each of a plurality of inlet flange bolt receivers circumferentially distributed around the engine axis; and wherein each inlet flange bolt receiver of the plurality of inlet flange bolt receivers is configured to receive the respective flange bolt shank of a respective flange bolt assembly of the plurality of flange bolt assemblies.

3. The nacelle inlet structure of claim 2 , wherein the engine case includes a fan case; wherein the inlet attachment flange is configured to be operatively coupled to a fan case attachment flange of the fan case to operatively couple the nacelle inlet structure to the engine case; wherein the fan case attachment flange defines a plurality of fan case flange bolt receivers; and wherein each inlet flange bolt receiver of the plurality of inlet flange bolt receivers is aligned with a corresponding fan case flange bolt receiver of the plurality of fan case flange bolt receivers, such that each respective flange bolt shank extends through a respective inlet flange bolt receiver and the corresponding fan case flange bolt receiver to operatively couple the nacelle inlet structure to the engine case.

4. The nacelle inlet structure of claim 2 , wherein each flange bolt assembly of the plurality of flange bolt assemblies further includes a respective deformable spacer positioned on the respective flange bolt shank, external to the inlet attachment flange; and wherein the respective deformable spacer is configured to plastically deform upon receiving an applied compressive load that is greater than a threshold compressive load.

5. The nacelle inlet structure of claim 2 , wherein each flange bolt assembly of the plurality of flange bolt assemblies includes a respective bushing positioned within a respective inlet flange bolt receiver of the plurality of inlet flange bolt receivers to provide a bearing between the respective flange bolt shank and the respective inlet flange bolt receiver.

6. An engine assembly comprising the nacelle inlet structure of claim 1 .

7. The nacelle inlet structure of claim 1 , wherein the U-shaped annular load absorber is operatively coupled to an aft side of the aft bulkhead.

8. The nacelle inlet structure of claim 2 , wherein the U-shaped annular load absorber comprises a forward flange, an aft flange, and a web interconnecting the forward flange and the aft flange, and wherein the aft flange at least partially defines each of the plurality of inlet flange bolt receivers.

9. The nacelle inlet structure of claim 1 , wherein the inlet attachment flange extends radially away from the engine axis.

10. The nacelle inlet structure of claim 1 , wherein the inlet attachment flange extends fully circumferentially around the engine axis.

11. The nacelle inlet structure of claim 1 , wherein the inlet inner barrel comprises a back skin that faces toward the inlet outer barrel; and wherein the back skin is integrally formed with the inlet attachment flange.

12. The nacelle inlet structure of claim 1 , further comprising a lipskin extending between the inlet outer barrel and the inlet inner barrel at least at a forward end of the nacelle inlet structure.

13. The nacelle inlet structure of claim 12 , wherein the lipskin at least partially defines the inlet outer barrel.

14. The nacelle inlet structure of claim 12 , wherein the inlet outer barrel comprises an outside mold line panel that is operatively coupled to the lipskin.

15. The nacelle inlet structure of claim 12 , wherein the lipskin at least partially defines the inlet inner barrel.

16. The nacelle inlet structure of claim 1 , further comprising a plurality of absorber fasteners that operatively couples the U-shaped annular load absorber to the aft bulkhead.

17. An engine assembly, comprising:
the nacelle inlet structure of claim 1 ;
a fan; and
a fan case operatively coupled to the nacelle inlet structure.

18. An aircraft, comprising:
a fuselage;
a wing extending from the fuselage; and
the engine assembly of claim 17 supported by the wing.

19. An aircraft, comprising:
a fuselage;
two wings extending from the fuselage; and
an engine assembly according to claim 17 supported by each of the two wings.

20. An engine assembly, comprising:
the nacelle inlet structure of claim 16 ;
a fan; and
a fan case operatively coupled to the nacelle inlet structure.

Assignees

• Boeing Co

Inventors

• Labelle Joseph B
• Stokes Jr Richard D
• Advent Kyle C
• Yestrau John
• Stanescu Adrian
• Davis Dan
• Schneider Jr Larry

Classifications

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• F05D2230/23

  by permanently joining parts together · CPC title

• F02C7/04

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title