NACELLE ASSEMBLY HAVING INTEGRATED AFTERBODY MOUNT CASE

• US 20130052005A1
• Filed: 08/24/2011
• Published: 02/28/2013
• Est. Priority Date: 08/24/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Cloft, Thomas G.
• Granted Patent: US 9,828,105 B2
• Time in Patent Office: Days
• US Class Current: 415/213.1
• CPC Class Codes: B64D 27/40 Arrangements for mounting power plants in aircraft
• CPC Class Codes: B64D 27/406 Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links
• CPC Class Codes: B64D 29/06 Attaching of nacelles, fairings or cowlings
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A nacelle assembly for a gas turbine engine includes an integrated afterbody mount case. The integrated afterbody mount case includes an outer ring and a plurality of spokes that extend radially inwardly from the outer ring. The outer ring includes a radially outer surface and a radially inner surface. The plurality of spokes are circumferentially disposed about the radially inner surface and extend radially inwardly from the radially inner surface.

Claims

1. A nacelle assembly for a gas turbine engine, comprising:

an integrated afterbody mount case including an outer ring having a radially outer surface and a radially inner surface;

a plurality of spokes that extend radially inwardly from said radially inner surface, wherein said plurality of spokes are circumferentially disposed about said outer ring.

2. The assembly as recited in claim 1, wherein said plurality of spokes are disposed in a diamond-shaped arrangement.

3. The assembly as recited in claim 1, wherein said plurality of spokes extend between said outer ring and a core engine casing.

4. The assembly as recited in claim 1, comprising a plurality of lugs disposed circumferentially about said radially inner surface of said outer ring.

5. The assembly as recited in claim 4, wherein at least one of said plurality of spokes is connected to at least one of said plurality of lugs.

6. The assembly as recited in claim 1, wherein said integrated afterbody mount case is connected to an afterbody section of the gas turbine engine.

7. A gas turbine engine, comprising:

a pylon;

a mount assembly connected to said pylon;

a nacelle assembly having an integrated afterbody mount case that includes an outer ring and a plurality of spokes, wherein said outer ring includes a radially outer surface connected to said mount assembly and a radially inner surface; and

a core engine casing, wherein each of said plurality of spokes extend between said radially inner surface of said outer ring and said core engine casing.

8. The gas turbine engine as recited in claim 7, wherein said core engine casing includes a turbine exhaust case.

9. The gas turbine engine as recited in claim 8, wherein each of said plurality of spokes extend between said radially inner surface and said turbine exhaust case.

10. The gas turbine engine as recited in claim 7, wherein said mount assembly includes a front mount and a rear mount.

11. The gas turbine engine as recited in claim 10, wherein said rear mount is attached between said integrated afterbody mount case and said pylon.

12. The gas turbine engine as recited in claim 7, comprising a fitting that attaches between said radially outer surface of said outer ring and said mount assembly.

13. The gas turbine engine as recited in claim 12, wherein said fitting includes a cone bolt fitting.

14. The gas turbine engine as recited in claim 7, comprising a mount beam that attaches between said radially outer surface of said outer ring and said mount assembly.

15. A method of isolating gas turbine engine loads, comprising the steps of:

positioning an integrated afterbody mount case of a nacelle assembly about a portion of a core engine casing; and

reacting the gas turbine engine loads through the integrated afterbody mount case to isolate the core engine casing from the gas turbine engine load.

16. The method as recited in claim 15, wherein the step of positioning the integrated afterbody mount case includes disposing the integrated afterbody mount case annularly about a turbine exhaust case of the core engine casing.

17. The method as recited in claim 15, wherein the step of positioning the integrated afterbody mount case includes the steps of:

positioning an outer ring about the core engine casing; and

extending a plurality of spokes between a radially inner surface of the outer ring and a radially outer surface of the core engine casing.

18. The method as recited in claim 15, wherein the step of reacting the gas turbine engine loads includes reacting the gas turbine engine loads through a mount assembly and a pylon of the gas turbine engine.