ASSEMBLY FOR MOUNTING A TURBINE ENGINE TO A PYLON

• US 20140369810A1
• Filed: 06/14/2013
• Published: 12/18/2014
• Est. Priority Date: 06/14/2013
• Status: Active Grant

• Current Assignee: ROHR Incorporated (Rtx Corporation)
• Original Assignee: ROHR Incorporated (Rtx Corporation)
• Inventors: Penda, Allan R., Binks, Alan J.
• Granted Patent: US 10,144,524 B2
• Time in Patent Office: Days
• US Class Current: 415/108
• CPC Class Codes: B64D 27/40 Arrangements for mounting power plants in aircraft
• CPC Class Codes: B64D 27/404 Suspension arrangements specially adapted for supporting vertical loads
• CPC Class Codes: B64D 27/406 Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links

Abstract

An assembly is provided for mounting a turbofan engine to a pylon. The turbofan engine includes a fan section and an engine core. The mounting assembly includes a fan case, a first mount and a second mount. The fan case is configured to house the fan section of the turbofan engine. The first mount is connected to the fan case, and configured to mount the fan case to the pylon. The second mount is connected to the fan case, and configured to mount the fan case to the pylon.

Claims

1. An assembly for mounting a turbofan engine to a pylon, the turbofan engine comprising a fan section and an engine core, the assembly comprising:

a fan case configured to house the fan section of the turbofan engine;

a first mount connected to the fan case, and configured to mount the fan case to the pylon; and

a second mount connected to the fan case, and configured to mount the fan case to the pylon independent of the first mount.

2. The assembly of claim 1, wherein

the fan case extends along an axial centerline;

and

the first mount is axially separated from the second mount.

3. The assembly of claim 1, wherein

the fan case extends along an axial centerline between a first end and a second end;

and

the first mount is connected to the fan case at the first end, and the second mount is connected to the fan case at the second end.

4. The assembly of claim 1, wherein

the first mount is configured to transfer an axial thrust load between the fan case and the pylon;

and

the second mount is configured to transfer one or more of a radial load, lateral load or a torsional load between the fan case and the pylon.

5. The assembly of claim 1, wherein the first mount includes a plurality of struts that are arranged circumferentially around an axial centerline of the fan case, and each of the struts is connected to and extends axially away from the fan case.

6. The assembly of claim 1, wherein

the second mount includes a mount beam and a plurality of links;

and

the links are arranged circumferentially around an axial centerline of the fan case, and connect the mount beam to the fan case.

7. The assembly of claim 6, wherein the first mount includes a strut that is substantially circumferentially centered between the links and connected to the fan case.

8. The assembly of claim 1, further comprising:

a core case configured to house the engine core of the turbofan engine; and

a third mount connected to the core case, and configured to mount the core case to the pylon.

9. The assembly of claim 8, further comprising at least one vane arranged radially between the fan case and the core case.

10. The assembly of claim 8, wherein

the third mount includes a mount beam and a plurality of links;

and

the links are arranged circumferentially around an axial centerline of the core case, and connect the mount beam to the core case.

11. The assembly of claim 10, wherein the third mount further includes at least one strut that is connected to and extends axially between the mount beam and the core case.

12. The assembly of claim 8, further comprising a fourth mount connected to the core case and configured to mount the core case to the pylon.

13. An assembly for mounting a turbofan engine to a pylon, the turbofan engine comprising a fan section and an engine core, the assembly comprising:

a fan case configured to house the fan section of the turbofan engine, the fan case extending along an axial centerline;

a first mount connected to the fan case; and

a second mount connected to the fan case and axially separated from the first mount;

the first mount and the second mount each configured to mount the fan case to the pylon.

14. A turbine engine system, comprising:

a turbine engine first case;

a turbine engine second case substantially coaxial with the first case;

a vane arranged radially between the first case and the second case; and

a plurality of case-to-pylon mounts including a first mount, a second mount and a third mount, wherein the first mount and the second mount are each connected to the first case, and the third mount is connected to the second case.

15. The system of claim 14, further comprising:

a fan section housed within the first case; and

an engine core housed within the second case.

16. The system of claim 14, further comprising:

a fan section housed within the second case; and

an engine core housed within the first case.

17. The system of claim 14, wherein the first mount is structurally independent of the second mount.

18. The system of claim 14, wherein the first mount is axially separated from the second mount.

19. The system of claim 14, wherein the case-to-pylon mounts further include a fourth mount that is connected to the second case.

20. The system of claim 14, further comprising a pylon that is connected to the first mount, the second mount and the third mount.