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

Patent metadata

Field	Value
Publication number	US-12085016-B2
Application number	US-202217721665-A
Country	US
Kind code	B2
Filing date	Apr 15, 2022
Priority date	May 4, 2021
Publication date	Sep 10, 2024
Grant date	Sep 10, 2024

Abstract

Nacelle inlet structures, engine assemblies and vehicles including the same, and related methods. A nacelle inlet structure of an engine assembly includes an inlet outer barrel and an inlet inner barrel with a tubular portion and an inlet attachment flange. The tubular portion of the inlet inner barrel extends at least partially along a direction parallel to the engine axis, while the inlet attachment flange extends from the tubular portion. The inlet attachment flange is integrally formed with at least a portion of the tubular portion of the inlet inner barrel. The inlet attachment flange is configured to be operatively coupled to an engine case of the engine assembly to operatively couple the nacelle inlet structure to the engine case. In examples, a method of manufacturing an inlet inner barrel includes forming a composite laminate with a composite manufacturing process.

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 at least substantially enclosing the inlet inner barrel and extending circumferentially around the engine axis and at least partially along a 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
an 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 annular load absorber; and wherein the annular load absorber has a U-shaped cross-section, wherein the U-shaped cross-section 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 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 annular load absorber is coupled to the inlet attachment flange; and

wherein the inlet attachment flange is integrally formed with at least a portion of the tubular portion.

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

3. The nacelle inlet structure of claim 2 , wherein the inlet attachment flange and the back skin are formed in a composite manufacturing process as a unitary composite structure.

4. The nacelle inlet structure of claim 2 , wherein the inlet inner barrel includes:
a face sheet that faces toward the engine axis; and
an acoustic structure for mitigating acoustic noise generated by the engine assembly;
wherein the tubular portion includes the acoustic structure; wherein at least a portion of the face sheet is spaced apart from the back skin; and wherein at least a portion of the acoustic structure extends between the back skin and the face sheet.

5. The nacelle inlet structure of claim 1 , wherein the inlet inner barrel includes a flange transition region extending between and interconnecting the tubular portion and the inlet attachment flange; wherein the flange transition region is integrally formed with the inlet attachment flange and at least a portion of the tubular portion; and wherein the flange transition region is smoothly curved between the tubular portion and the inlet attachment flange.

6. The nacelle inlet structure of claim 5 , wherein the inlet inner barrel includes an inlet radius channel defined between the flange transition region and the tubular portion; and wherein the inlet inner barrel further includes an inlet radius filler received within the inlet radius channel.

7. The nacelle inlet structure of claim 6 , wherein the inlet radius filler at least substantially fills the inlet radius channel; and wherein the inlet radius filler is configured to enhance a rigidity of the inlet attachment flange relative to the tubular portion.

8. 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; 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.

9. The nacelle inlet structure of claim 8 , wherein the 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.

10. The nacelle inlet structure of claim 8 , wherein the engine case includes a fan case that at least substantially encloses a fan of the engine assembly; 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.

11. The nacelle inlet structure of claim 8 , 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; wherein the respective deformable spacer is configured to plastically deform upon receiving an applied compressive load that is greater than a threshold compressive load.

12. The nacelle inlet structure of claim 8 , 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.

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

14. A method of manufacturing the inlet inner barrel of the nacelle inlet structure of claim 1 , the method comprising:
forming, with a composite manufacturing process, a composite laminate that includes a back skin and the inlet attachment flange.

15. The method of claim 14 , wherein the forming the composite laminate includes:
molding a plurality of plies of a composite material to define the back skin and the inlet attachment flange; and
curing the plurality of plies of the composite material to solidify the composite laminate.

16. The method of claim 15 , wherein the molding the plurality of plies of the composite material includes forming a flange transition region extending between and interconnecting the tubular portion and the inlet attachment flange and an inlet radius channel defined between the flange transition region and the tubular portion; and wherein the method further comprises, prior to the curing the plurality of plies of the composite material, positioning an inlet radius filler relative to the composite laminate.

17. The method of claim 16 , further comprising, prior to the positioning the inlet radius filler, forming the inlet radius filler; where

Assignees

• Boeing Co

Inventors

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

Classifications

• F01D25/243 Primary

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• 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