Translating independently mounted air inlet system for aircraft turbofan jet engine

• US 6,340,135 B1
• Filed: 05/30/2000
• Issued: 01/22/2002
• Est. Priority Date: 05/30/2000
• Status: Expired due to Term

• Current Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: ROHR Incorporated (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Barton, Brian E.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/580,900
• Time in Patent Office: 602 Days
• Field of Search: 244/53.R, 244/54, 244/110.B, 244/129.4, 137/15.1, 137/15.2, 60/393.1, 602/261
• US Class Current: 244/53.00B
• CPC Class Codes: B64D 29/00 Power-plant nacelles, fairings, or cowlings nacelles not otherwise provided for B64C

Abstract

An arrangement for an aircraft propulsion system to determinably reduce or eliminate inlet cowl induced bending of a turbofan aircraft jet engine case during certain flight conditions. The arrangement includes a turbofan aircraft jet engine having an engine case with a fan case portion, a nacelle structure housing the engine and having a forward nacelle portion and a rearward nacelle portion, and a pylon structure to support the engine and the nacelle structure while permitting the forward nacelle structure to be translated forwardly from an operational position to a servicing position to permit access to the engine and its components. The forward nacelle portion is independently supported from the pylon and has an inner skin portion that sealingly engages the fan case portion of the engine case and an outer skin portion that is determinably locked to the rearward nacelle portion. The sealing arrangement of the forward nacelle portion and the fan case portion is designed to determinably tailor the load transfer between the forward nacelle portion and the fan case portion to completely eliminate or to reduce such load transfer according to the particular propulsion system arrangement.

Claims

1. An aircraft propulsion system arrangement to determinably reduce or eliminate inlet cowl induced bending of an aircraft jet engine case during certain flight conditions, which arrangement comprises a turbofan aircraft jet engine having an engine case with a fan case portion, a nacelle structure housing the engine and having a forward generally cylindrical nacelle portion and a rearward nacelle portion, and a pylon structure to support the engine and the nacelle structure while permitting relative movement between the forward and rearward nacelle portions, wherein the pylon structure supports the forward nacelle portion independently of its support of the engine while permitting translational movement of the forward nacelle portion forwardly on the pylon structure from a locked operational position during operation of the engine to a forward servicing position during non-operation of the engine, wherein the forward nacelle portion provides an air inlet cowl portion directly coupled to said fan case portion of the engine for the supply of air to the engine and to an integral fan housing portion which surrounds the fan case portion of the engine, wherein the forward nacelle portion includes a noselip portion having an inner main skin which extends rearwardly to sealingly engage said fan case portion of the engine, and an outer generally concentric main skin which extends rearwardly to lockingly engage the rearward nacelle portion, and in the forward servicing position of the forward nacelle portion, it may be spaced forwardly from said fan case portion of the engine to uncover the outer fan case portion of the engine to give access thereto and to components mounted thereon which are inaccessible when the forward nacelle portion is secured in the operational position.

2. A nacelle arrangement according to claim 1 wherein the forward portion of the nacelle structure includes bulkhead means positioned between the inner and outer main skins to provide reinforcement.

3. A nacelle arrangement according to claim 2 wherein the bulkhead means includes at least two spaced bulkhead members fixedly positioned between said inner and outer main skins.

4. A nacelle arrangement according to claim 1 which further includes track means to provide support for the nacelle structure and to permit determinable translation of the forward nacelle structure portion from a locked operational position during operation of the engine to a forward servicing position.

5. A nacelle arrangement according to claim 4 wherein said track means is an extensible track arrangement cooperating with the supporting pylon structure and the supported nacelle structure to provide determinable translation of said forward nacelle structure portion.

6. A nacelle arrangement according to claim 5 which further includes screw jack means that is determinably actuable to extend and retract said track means to determinably translate said forward nacelle structure portion.

7. A nacelle arrangement according to claim 1 which further includes actuable locking means to provide locking of the aft end of said outer main skin to a forward flange means of said rearward nacelle portion.

8. A nacelle arrangement according to claim 7 wherein said locking means further includes latching means to provide determinable locking of said locking means, said latching means being accessible from a position external to the external main skin of the forward nacelle portion.

9. A nacelle arrangement according to claim 1 which further includes a seal means to provide a non-locking sealing and limited load transfer engagement between an aft end of the inner main skin of the forward nacelle portion and an annular flange provided on a forward portion of said fan case portion of said jet engine, said seal means comprising a V-groove arrangement that provides a generally concentrically shaped longitudinally extending V-shaped portion provided in the inner main skin that cooperates with a complementarily V-shaped portion of said flange of the fan case portion of said engine case.

10. A nacelle arrangement for a turbofan aircraft jet engine having an engine case and supported by a pylon structure secured to an aircraft to determinably reduce or eliminate inlet cowl induced engine case bending during certain flight conditions, which arrangement comprises a nacelle structure housing the engine and having a forward generally cylindrical nacelle portion supported on the pylon structure supporting the engine and a rearward nacelle portion supported on the engine case while permitting relative movement between the forward and rearward nacelle portions, wherein the forward nacelle portion is supported by the pylon structure in a manner to permit translational movement of the forward nacelle portion forwardly on the pylon structure from an operational position during operation of the engine to a forward servicing position during non-operation of the engine in which the forward nacelle portion is supported by the pylon structure forwardly of the operational position, wherein the forward nacelle portion provides an air inlet cowl portion directly coupled to a fan case portion of the engine case for the supply of air to the engine and a fan cowl housing portion which surrounds said fan case portion of the engine, wherein the forward nacelle portion includes a noselip portion having an inner main skin which extends rearwardly to engage the fan case portion of the engine case and an outer generally concentric main skin which extends rearwardly to lockingly engage the rearward nacelle portion, and in the forward servicing position of the forward nacelle portion it may be spaced forwardly of the air intake of the engine to uncover the outer fan case portion of the engine to give access thereto and to components mounted thereon which are inaccessible when the forward nacelle portion is secured in the operational position.

11. An aircraft propulsion system according to claim 10, wherein the forward nacelle portion has a substantially uninterrupted low drag exterior surface.

12. An aircraft propulsion system according to claim 10, wherein the support means provides for translational movement of the forward nacelle portion from its operational position to its forward servicing position.

13. An aircraft propulsion system according to claim 10 wherein the aft end of the forward nacelle portion terminates at a position downstream of the fan case of the jet engine.

14. An aircraft propulsion system according to claim 10 which also includes an extensible track means which provides support for the forward nacelle portion from the pylon structure and that permits determinable translational movement of the forward nacelle portion between an operational position and a servicing position.

15. An aircraft propulsion system according to claim 14 which further includes screw jack means to determinably translate the forward nacelle portion on said track means between an operational position and a servicing position.

16. An aircraft propulsion system for an aircraft to determinably reduce or eliminate inlet cowl induced engine case bending during certain flight conditions, which system comprises a nacelle structure housing a turbofan jet engine having an engine case and having a forward nacelle portion and a rearward nacelle portion, and a pylon structure to support independently the engine and the forward nacelle portion while permitting relative movement between the forward and rearward nacelle portions, wherein the pylon structure supports the forward nacelle portion while permitting translational movement of the forward nacelle portion forwardly on the pylon structure from an operational position during operation of the engine to a forward servicing position during non-operation of the engine in which the forward nacelle portion is supported by the pylon structure forwardly of the operational position, wherein the forward nacelle portion provides an air inlet portion directly coupled to a leading edge portion of a fan case portion of the engine case for the supply of air to the engine and a fan housing portion which surrounds said fan case portion of the engine case, wherein the forward nacelle portion includes a noselip portion having an inner main skin which extends rearwardly to engage the leading edge portion of a fan case portion of the engine case and an outer generally concentric main skin which extends rearwardly to lockingly engage the rearward nacelle portion, and in the forward servicing position of the forward nacelle portion it may be spaced forwardly of said fan case portion of the engine case to uncover the outer fan portion of the engine to give access thereto and to components mounted thereon which are inaccessible when the forward nacelle portion is secured in the operational position.

17. An aircraft propulsion system for an aircraft according to claim 16 which further includes an extensible track means which cooperates with the supporting pylon and the forward nacelle portion to provide fore and aft longitudinal translational movement of the forward nacelle portion between an operational positional and a servicing position, and screw jack means coupled to said track means to drive said extensible track means in a desired longitudinal direction.

18. An aircraft propulsion system for an aircraft according to claim 17 which further includes a locking ring means that is actuable by latch means accessible from the exterior of the forward nacelle portion to permit determinable locking of said aft end portion of the main skin portion of the forward nacelle portion to a forward flange of the rearward nacelle portion.

19. An aircraft propulsion system for an aircraft according to claim 18 wherein the rearward nacelle portion further comprises thrust reverser means for such system.

20. An aircraft propulsion system for an aircraft according to claim 16 which further includes seal means interposed between the aft end of the inner main skin of the forward nacelle portion and an annular flange of the leading edge portion of the fan case portion of the engine case to preclude the leakage of air flowing through said forward nacelle portion during operation of the engine between the non-locking engagement of the aft end said inner skin portion of the forward section of the nacelle portion and the fan case portion of the engine case.

21. An aircraft propulsion system for an aircraft according to claim 20 wherein said seal means provides a non-locking engagement of the aft end of said inner skin portion of the forward section of the nacelle portion and the fan case portion of the engine case, which non-locking engagement determinably falls within a range of complete elimination of bending load transfer from the forward nacelle portion to the fan case portion to a partial reduction in such bending load transfer.

22. An aircraft propulsion system for an aircraft according to claim 21 wherein the attachment of the forward nacelle portion to the rearward nacelle portion and the aircraft pylon is arranged to provide additional structural load paths for retention of said forward nacelle portion in said nacelle structure following a blade-out occurrence of the fan portion of the engine.