Method and device for connecting fan rotor to low pressure turbine rotor

Patent metadata

Field	Value
Publication number	US-11261753-B2
Application number	US-201715832814-A
Country	US
Kind code	B2
Filing date	Dec 6, 2017
Priority date	Dec 6, 2017
Publication date	Mar 1, 2022
Grant date	Mar 1, 2022

Abstract

A rotor assembly includes a fan rotor shaft coupled to a fan rotor, a low pressure turbine rotor shaft coupled to a low pressure turbine rotor, and a joint device configured to connect the fan rotor shaft to the low pressure turbine rotor shaft, to allow torsion, shear and bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and allow torsion and shear but prevent bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event.

First claim

The invention claimed is:

1. A rotor assembly comprising:
a fan rotor shaft coupled to a fan rotor;
a low pressure turbine rotor shaft coupled to a low pressure turbine rotor; and
a joint device configured to connect the fan rotor shaft to the low pressure turbine rotor shaft, to transfer torsion, shear and bending between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and maintain transfer of torsion and shear and disconnect transfer of bending between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event,
wherein the joint device comprises a plurality of circumferentially-spaced curved splines in a spline joint and the circumferentially-spaced curved splines are accommodated in and engaging with corresponding plurality of grooves defined in the fan rotor shaft.

2. The rotor assembly according to claim 1 , wherein the joint device is configured to allow angular misalignment between the fan rotor shaft and the low pressure turbine rotor shaft under the fan blade-out event.

3. The rotor assembly according to claim 1 , wherein the joint device comprises a load reduction joint selected from the group consisting of a spherical spline joint, a constant velocity universal joint, an axial coupling, or a combination thereof.

4. The rotor assembly according to claim 3 , wherein the joint device further comprises a cylindrical spline joint coupled to the load reduction joint.

5. The rotor assembly according to claim 1 , wherein the joint device comprises a spherical spline joint coupled to the fan rotor shaft, and a cylindrical spline joint coupled between the spherical spline joint and the low pressure turbine rotor shaft.

6. The rotor assembly according to claim 5 , wherein the spherical spline joint comprises spherical splines and spherical spline grooves defined in the fan rotor shaft for accommodating the spherical splines.

7. The rotor assembly according to claim 5 , wherein the cylindrical spline joint comprises cylindrical splines formed on the outer face of the low pressure turbine shaft and cylindrical spline grooves defined on an inner face of the spherical spline joint.

8. The rotor assembly according to claim 5 , wherein the joint device further comprises circumferentially-spaced mechanical fuses extending into both the fan rotor shaft and the spherical spline joint.

9. The rotor assembly according to claim 1 , wherein the joint device comprises a cylindrical spline joint coupled to the fan rotor shaft and a load reduction joint coupled between the cylindrical spline joint and the low pressure turbine rotor shaft, wherein the cylindrical spline joint comprises cylindrical splines and cylindrical spline grooves, wherein the cylindrical spline grooves are defined in the fan rotor shaft, and the load reduction joint is selected from the group consisting of a constant velocity universal joint and an axial coupling.

10. The rotor assembly according to claim 1 , further comprising:
a support frame;
a bearing assembly supporting the fan rotor shaft to the support frame; and
a cone shaft, comprising a conical cross-section and extending between the bearing assembly and the fan rotor shaft.

11. The rotor assembly according to claim 10 , wherein at least a part of the fan rotor shaft is sandwiched between the cone shaft and the joint device.

12. A method for fabricating a rotor assembly for a gas turbine engine, the method comprising:
coupling a fan rotor shaft to a fan rotor;
coupling a low pressure turbine rotor shaft to a low pressure turbine rotor; and
connecting the fan rotor shaft to the low pressure turbine rotor shaft through a joint device, which is configured to transfer torsion, shear and bending between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and maintain transfer of torsion and shear and disconnect transfer of bending between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event, wherein the joint device comprises a plurality of circumferentially-spaced curved splines in a spline joint and the circumferentially-spaced curved splines are accommodated in and engaging with corresponding plurality of grooves defined in the fan rotor shaft.

13. The method according to claim 12 , wherein the joint device is configured to allow angular misalignment between the fan rotor shaft and the low pressure turbine rotor shaft under the fan blade-out event.

14. The method according to claim 12 , wherein the joint device comprises a load reduction joint selected from the group consisting of a spherical spline joint, a constant velocity universal joint, an axial coupling, or a combination thereof.

15. The method according to claim 14 , wherein the joint device further comprises a cylindrical spline joint coupled to the load reduction joint.

16. The method according to claim 12 , wherein the joint device comprises a spherical spline joint coupled to the fan rotor shaft, and a cylindrical spline joint coupled between the spherical spline joint and the low pressure turbine rotor shaft.

17. The method according to claim 16 , wherein the joint device further comprises circumferentially-spaced mechanical fuses extending into both the fan rotor shaft and the spherical spline joint.

18. The method according to claim 12 , wherein the joint device comprises a cylindrical spline joint coupled to the fan rotor shaft and a load reduction joint coupled between the cylindrical spline joint and the low pressure turbine rotor shaft, wherein the cylindrical spline joint comprises cylindrical splines and cylindrical spline grooves, wherein the cylindrical spline grooves are defined in the fan rotor shaft, and the load reduction joint is selected from the group consisting of a constant velocity universal joint and an axial coupling.

19. The method according to claim 12 , further comprising supporting the fan rotor shaft on a support frame with a bearing assembly, with a cone shaft extending between the bearing assembly and the fan rotor shaft, the cone shaft comprising a conical cross-section.

Assignees

• Gen Electric

Inventors

• Yadav Abhijeet Jayshingrao
• Kray Nicholas Joseph
• Jain Nitesh
• Rasal Saurabh Sanjay

Classifications

• 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

• F05D2260/40

  Transmission of power · CPC title

• F16D3/18

  the coupling parts (1) having slidably-interengaging teeth · CPC title

• F16D3/16

  Universal joints in which flexibility is produced by means of pivots or sliding or rolling connecting parts · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title