Turbine engine gearbox mount with multiple fuse joints

Patent metadata

Field	Value
Publication number	US-9777639-B2
Application number	US-201213726133-A
Country	US
Kind code	B2
Filing date	Dec 23, 2012
Priority date	Dec 23, 2012
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of mounts connecting the gearbox to the case. Each of the mounts includes a linkage and a fuse joint. The linkage extends towards the case substantially in a first direction. The fuse joint is configured to substantially prevent movement between the gearbox and the case when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the gearbox and the case when the loading is greater than the threshold. The fuse joint of a first of the mounts has a different configuration than the fuse joint of a second of the mounts.

First claim

What is claimed is:

1. A turbine engine assembly, comprising:
a turbine engine case;
a gearbox;
a bracket comprising a first aperture and a second aperture; and
a plurality of mounts connecting the gearbox to the turbine engine case, each of the plurality of mounts comprising:
a linkage extending towards the turbine engine case substantially in a first direction; and
a fuse joint configured to substantially prevent movement between the gearbox and the turbine engine case when the fuse joint is subject to a loading less than a threshold, and to permit a constrained movement between the gearbox and the turbine engine case when the loading is greater than the threshold;
wherein the fuse joint of a first of the plurality of mounts has a different configuration than the fuse joint of a second of the plurality of mounts;

wherein the linkage of the first of the plurality of mounts comprises a third aperture and a fourth aperture;
wherein the fuse joint of the first of the plurality of mounts comprises a first fastener and a second fastener;
wherein the first fastener extends into the first and the third apertures, and has a diameter that is substantially equal to diameters of the first and the third apertures; and
wherein the second fastener extends into the second and the fourth apertures, and has a diameter that is less than at least one of a diameter of the second aperture and a diameter of the fourth aperture.

2. The engine assembly of claim 1 , wherein the turbine engine case extends along an axis, and the first direction is a radial inward direction.

3. The engine assembly of claim 1 , wherein the turbine engine case extends along an axis, and the first direction is an axial direction.

4. The engine assembly of claim 1 , wherein
the turbine engine case extends along an axis; and
each of the plurality of mounts has a radial height and an axial length that is greater than the radial height.

5. The engine assembly of claim 1 , wherein
the turbine engine case extends along an axis; and
each of the plurality of mounts has a radial height and an axial length that is less than the radial height.

6. The engine assembly of claim 1 , wherein the linkage of the first of the plurality of mounts is one of a strut and a bracket.

7. The engine assembly of claim 1 , wherein the fuse joint of each of the plurality of mounts connects the respective linkage to the gearbox.

8. The engine assembly of claim 1 , wherein the fuse joint of each of the plurality of mounts connects the respective linkage to the turbine engine case.

9. The engine assembly of claim 1 , wherein the fuse joint of the second of the plurality of mounts comprises a fastener configured to transfer a load between the turbine engine case and the gearbox when the loading is less than the threshold, and to deform and/or fracture when the loading is greater than the threshold.

10. The engine assembly of claim 9 , wherein the fuse joint of the second of the plurality of mounts further comprises a second fastener configured to transfer a load between the turbine engine case and the gearbox when the loading is greater than the threshold.

11. The engine assembly of claim 1 , wherein
the linkage of the second of the plurality of mounts comprises an aperture;
the fuse joint of the second of the plurality of mounts comprises a sleeve that extends into the aperture, and a fastener that extends into the sleeve; and
the sleeve has an outer diameter that is substantially equal to a diameter of the aperture, and an inner diameter that is greater than a diameter of the fastener.

12. The engine assembly of claim 1 , wherein
the turbine engine case extends along an axis; and
the fuse joint of the first of the plurality of mounts is axially aligned with the fuse joint of the second of the plurality of mounts.

13. The engine assembly of claim 1 , further comprising a second mount that connects the gearbox to the turbine engine case, and comprises a second linkage that extend towards the turbine engine case substantially in a second direction that is different than the first direction.

14. The engine assembly of claim 1 , wherein one of the plurality of mounts comprises:
a base connected to the turbine engine case; and
a plurality of arms connected to the gearbox, wherein the arms converge to the base.

15. A turbine engine assembly, comprising:
a turbine engine case extending along an axis;
a gearbox; and
a plurality of mounts connecting the gearbox to the turbine engine case, each of the plurality of mounts comprising a fuse joint configured to substantially prevent movement between the gearbox and the turbine engine case when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the gearbox and the turbine engine case when the loading is greater than the threshold;
wherein the fuse joint of a first of the plurality of mounts has a first configuration and the fuse joint of a second of the plurality of mounts has a second configuration;
wherein the fuse joint of the first of the plurality of mounts is substantially axially aligned with the fuse joint of the second of the plurality of mounts; and
wherein the fuse joint of the first of the plurality of mounts comprises:
a first fastener configured to transfer a load between the turbine engine case and the gearbox when the loading is less than the threshold, and to deform and/or fracture when the loading is greater than the threshold; and
a second fastener located proximate the first fastener, configured to transfer a load between the turbine engine case and the gearbox when the loading is greater than the threshold, and configured to transfer substantially no load between the turbine engine case and the gearbox when the loading is less than the threshold.

16. The engine assembly of claim 15 , wherein each of the plurality of mounts further comprises a linkage that extends towards the turbine engine case substantially in one of an axial direction and a radial inward direction.

17. The engine assembly of claim 15 , wherein the fuse joint of the second of the plurality of mounts comprises:
a sleeve configured to transfer a load between the turbine engine case and the gearbox when the loading is less than the threshold, and to deform and/or fracture when the loading is greater than the threshold; and
a fastener that extends into the sleeve, and is configured to transfer a load between the turbine engine case and the gearbox when the loading is greater than the threshold.

18. A turbine engine assembly, comprising:
a gearbox; and
a plurality of mounts connected to the gearbox, each of the plurality of mounts comprising:
a first linkage;
a second linkage; and
a fuse joint configured to substantially prevent movement between the first linkage and the second linkage when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the first linkage and the second linkage when the loading is greater than the threshold;
wherein the fuse joint of a first of the plurality of mounts is configured as a multi-point fuse joint, and the fuse joint of a second of the plurality of mounts is configured as a concentric fuse joint.

Assignees

• United Technologies Corp

Inventors

• Davis Todd A
• Webb Timothy
• Ronski Mark
• Stachowiak David A

Classifications

• F05D2260/311

  of the frangible or shear type · CPC title

• F02C7/36 Primary

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F01D21/045 Primary

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic