Inlet section of an aircraft engine nacelle

• US 8,197,191 B2
• Filed: 04/14/2009
• Issued: 06/12/2012
• Est. Priority Date: 04/14/2009
• Status: Active Grant

• Current Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Binks, Alan, James, Norman John, Layland, Michael John
• Primary Examiner(s): Luu, Chuong A.
• Application Number:
  US12/423,550
• Publication Number:
  US 20100260602A1
• Time in Patent Office: 1,155 Days
• Field of Search: 415/119, 415/213.1, 415/214.1, 415/220, 415/182.1
• US Class Current: 415/119
• CPC Class Codes: B64D 2033/0206 comprising noise reduction means, e.g. acoustic liners
• CPC Class Codes: B64D 29/06 Attaching of nacelles, fairings or cowlings
• CPC Class Codes: B64D 29/08 Inspection panels for power plants
• CPC Class Codes: B64D 33/02 of combustion air intakes air intakes for gas-turbine plants or jet-propulsion plants per se F02C7/04; air intakes for combustion engines in general F02M35/00
• CPC Class Codes: Y02B 10/30 Wind power
• CPC Class Codes: Y02E 10/72 Wind turbines with rotation axis in wind direction
• CPC Class Codes: Y10T 137/0536 Highspeed fluid intake means [e.g., jet engine intake]

Abstract

A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange.

Claims

1. A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange, the nacelle inlet comprising:

an acoustic inner barrel having a forward portion and an aft portion;

an outer shell comprising a nose lip portion having a trailing inner edge and an outer barrel portion having an aft portion;

an aft mounting flange configured for attaching the inlet to the forward flange of the engine fan case; and

an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft mounting flange;

wherein the forward portion of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft mounting flange; and

wherein the aft bulkhead connects the outer barrel portion to the aft mounting flange such that a load can be transferred from the outer barrel portion to the aft mounting flange, via the aft bulkhead, with no substantial portion of the load path passing through the acoustic inner barrel.

2. A nacelle inlet according to claim 1 wherein the aft bulkhead, the nose lip portion and the outer barrel portion are constructed of a single piece of material that continuously extends from the trailing inner edge of the nose lip portion to the aft end of the aft bulkhead.

3. A nacelle inlet according to claim 1 wherein a portion of the aft mounting flange, the aft end of the aft bulkhead and the aft portion of the inner barrel are secured together by a first plurality of fasteners, each fastener securing all three of the mounting flange, the aft end of the aft bulkhead and the aft portion of the inner barrel.

4. A nacelle inlet according to claim 1 wherein the aft bulkhead has a substantially conical shape.

5. A nacelle inlet according to claim 1 wherein the aft end of the aft bulkhead has a substantially cylindrical shape.

6. A nacelle inlet according to claim 1, further comprising a forward bulkhead extending between the trailing inner edge of the nose lip portion and a forward portion of the inner barrel.

7. A nacelle inlet according to claim 1 wherein the acoustic inner barrel includes no longitudinal joints.

8. A nacelle inlet according to claim 1 wherein the acoustic inner barrel comprises a plurality of separably connected circumferential segments.

9. A nacelle inlet according to claim 8 wherein any longitudinal gaps between the circumferential segments are not greater than about 5 mm.

10. A nacelle inlet according to claim 9 wherein the circumferential segments are connected by opposing flanges along longitudinal edges of the segments.

11. A nacelle inlet according to claim 9 wherein the circumferential segments are connected by one or more splice plates.

12. A nacelle inlet according to claim 1 wherein the aft portion of the inner barrel extends aft of the aft mounting flange.

13. A nacelle inlet according to claim 1 further comprising at least one circumferential stiffener on an inner surface of the outer barrel portion.

24. An aircraft engine nacelle according to claim 1 wherein the nose lip portion, the outer barrel portion and the aft bulkhead are formed from a continuous piece of material.

14. A nacelle for an aircraft engine of a type having a fan case, the nacelle having an inlet portion comprising:

an acoustic inner barrel;

an outer shell comprising a nose lip portion and an outer barrel portion; and

mounting means for mounting the inlet portion to the fan case;

wherein the mounting means provides a load path from an aft portion of the outer shell to the fan case through the mounting means, and wherein no substantial portion of the load path passes through the acoustic inner barrel.

15. A nacelle according to claim 14 wherein the mounting means comprises a bulkhead disposed between the fan case and the outer shell when the inlet portion is mounted to the fan case.

16. A nacelle according to claim 15 wherein the aft bulkhead and the outer shell are formed from a continuous piece of material.

17. A nacelle according to claim 15 further comprising an aft mounting flange connected to the bulkhead.

18. A nacelle according to claim 14 wherein the acoustic inner barrel comprises a plurality of separably connected circumferential segments.

20. An aircraft engine nacelle according to claim 18 wherein the outer shell and the aft bulkhead are formed from a continuous piece of material.

19. An aircraft engine nacelle having an inlet portion comprising:

an outer shell having a nose lip portion and an outer barrel portion;

an inner barrel;

an aft bulkhead; and

an aft mounting flange;

wherein the outer barrel is connected to the aft bulkhead by a first connection, the aft bulkhead is connected to the aft mounting flange by a second connection, the inner barrel is connected to the aft mounting flange by a third connection, and the second connection is separate from the third connection; and

wherein the second connection provides a load path from the outer barrel portion to the aft mounting flange via the aft bulkhead, such that a load can be transferred from the outer barrel portion to the aft mounting flange, via the aft bulkhead, with no substantial portion of the load path passing through the inner barrel.

21. An aircraft engine nacelle according to claim 19 wherein the nose lip portion and the outer barrel portion are formed from a continuous piece of material.

22. An aircraft engine nacelle according to claim 19 wherein the nose lip portion, the outer barrel portion and the aft bulkhead are formed from a continuous piece of material.

23. An aircraft engine nacelle according to claim 19 wherein the aft bulkhead has a substantially conical shape.

25. An aircraft engine nacelle having an inlet portion comprising:

an outer shell having a nose lip portion and an outer barrel portion;

an inner barrel having an outer skin;

an aft bulkhead; and

an aft mounting flange integrally formed as part of the outer skin of the inner barrel;

wherein the aft bulkhead is connected to the aft mounting flange by a connection which provides a load path from the outer barrel portion to the aft mounting flange.

26. An aircraft engine nacelle according to claim 25 wherein the outer barrel portion is connected to the aft bulkhead by a first connection and the aft bulkhead is connected to the aft mounting flange by a second connection.

27. An aircraft engine nacelle according to claim 25 wherein the outer shell and the aft bulkhead are formed from a continuous piece of material.

28. An aircraft engine nacelle according to claim 25 wherein the nose lip portion and the outer barrel portion are formed from a continuous piece of material.

29. An aircraft engine nacelle according to claim 25 wherein the nose lip portion, the outer barrel portion and the aft bulkhead are formed from a continuous piece of material.

30. An aircraft engine nacelle according to claim 25, wherein the aft bulkhead has a substantially conical shape.

31. A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange, the nacelle inlet comprising:

an acoustic inner barrel having a forward portion and an aft portion;

an outer shell comprising a nose lip portion having a trailing inner edge and an outer barrel portion having an aft portion;

an aft mounting flange configured for attaching the inlet to the forward flange of the engine fan case; and

an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft mounting flange;

wherein the forward portion of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft mounting flange; and

wherein the nose lip portion, the outer barrel portion and the aft bulkhead are constructed as a single piece of material that continuously extends from the trailing inner edge of the nose lip portion to the aft end of the aft bulkhead.

32. A nacelle inlet according to claim 31 wherein the aft bulkhead has a substantially conical shape.

33. A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange, the nacelle inlet comprising:

an acoustic inner barrel having a forward portion and an aft portion;

an outer shell comprising a nose lip portion having a trailing inner edge and an outer barrel portion having an aft portion;

an aft mounting flange configured for attaching the inlet to the forward flange of the engine fan case; and

an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft mounting flange;

wherein the forward portion of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft mounting flange; and

wherein a portion of the aft mounting flange, the aft end of the aft bulkhead and the aft portion of the inner barrel are secured together by a first plurality of fasteners, each fastener securing all three of the mounting flange, the aft end of the aft bulkhead and the aft portion of the inner barrel.

34. A nacelle inlet according to claim 33 wherein the aft bulkhead is further directly fastened to the aft mounting flange via an additional plurality of fasteners.

35. A nacelle inlet according to claim 33 wherein the aft bulkhead has a substantially conical shape.

36. A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange, the nacelle inlet comprising:

an acoustic inner barrel having a forward portion and an aft portion;

an outer shell comprising a nose lip portion having a trailing inner edge and an outer barrel portion having an aft portion;

an aft mounting flange configured for attaching the inlet to the forward flange of the engine fan case; and

an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft mounting flange;

wherein the forward portion of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft mounting flange; and

wherein the aft portion of the inner barrel extends aft of the aft mounting flange.

37. A nacelle inlet according to claim 36 wherein the aft bulkhead has a substantially conical shape.

38. A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange, the nacelle inlet comprising:

an acoustic inner barrel having a forward portion and an aft portion;

an outer shell comprising a nose lip portion having a trailing inner edge and an outer barrel portion having an aft portion;

an aft mounting flange configured for attaching the inlet to the forward flange of the engine fan case; and

an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft mounting flange;

wherein the forward portion of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft mounting flange; and

wherein the aft bulkhead has a substantially conical shape.