Granted Patent B2

US 12,203,418 · App. 17/929,105 · Granted Jan 21, 2025

Inventors: Bugra H. Ertas (Niskayuna, NY); Ravindra Shankar Ganiger (Bengaluru, IN); Andrea Piazza (Turin, IT)

Assignees: GENERAL ELECTRIC COMPANY; GE AVIO S.R.L.

F02C7/36F16H57/025F16H57/08

Abstract

Claims (40)

1. A mounting assembly for a gearbox assembly of a gas turbine engine, the mounting assembly comprising:

a flex coupling configured to mount a first gear of the gearbox assembly to a rotating shaft of the gas turbine engine;

a flex mount configured to mount a second gear of the gearbox assembly to an engine static structure; and

a fan frame configured to mount a third gear of the gearbox assembly to the engine static structure,

wherein each of the flex coupling and the flex mount is characterized by a lateral impedance parameter ratio, a bending impedance parameter ratio, and a torsional impedance parameter ratio,

wherein the lateral impedance parameter ratio of the flex coupling, the flex mount, or both is less than or equal to 0.5,

wherein the bending impedance parameter ratio of the flex coupling, the flex mount, or both is less than or equal to 0.5, and

wherein the torsional impedance parameter ratio of the flex coupling, the flex mount, or both is greater than or equal to 0.1.

2. The mounting assembly of claim 1 , wherein the first gear is a sun gear, the second gear is a plurality of planet gears, and the third gear is a ring gear.

3. The mounting assembly of claim 1 , wherein the first gear is a sun gear, the second gear is a ring gear, and the third gear is a plurality of planet gears.

4. The mounting assembly of claim 1 , wherein the gearbox assembly is arranged in a planetary configuration.

5. The mounting assembly of claim 1 , wherein the gearbox assembly is arranged in a star configuration.

6. The mounting assembly of claim 1 , wherein the lateral impedance parameter ratio of the flex mount is less than or equal to 0.5.

7. The mounting assembly of claim 1 , wherein the bending impedance parameter ratio of the flex mount is less than or equal to 0.5.

8. The mounting assembly of claim 1 , wherein the lateral impedance parameter ratio of the flex coupling is less than or equal to 0.5.

9. The mounting assembly of claim 1 , wherein the bending impedance parameter ratio of the flex coupling is less than or equal to 0.5.

10. The mounting assembly of claim 1 , wherein the torsional impedance parameter ratio of the flex mount is greater than or equal to 0.1.

11. The mounting assembly of claim 10 , wherein the torsional impedance parameter ratio of the flex mount is between 0.1 and 0.95.

12. The mounting assembly of claim 1 , wherein the torsional impedance parameter ratio of the flex coupling is greater than or equal to 0.1.

13. The mounting assembly of claim 12 , wherein the torsional impedance parameter ratio of the flex mount is between 0.1 and 0.95.

14. The mounting assembly of claim 1 , wherein the flex coupling is characterized by a flex coupling lateral impedance parameter, a flex coupling bending impedance parameter, and a flex coupling torsional impedance parameter, the flex mount is characterized by a flex mount lateral impedance parameter, a flex mount bending impedance parameter, and a flex mount torsional impedance parameter, and the fan frame is characterized by a fan frame lateral impedance parameter, a fan frame bending impedance parameter, and a fan frame torsional impedance parameter.

15. The mounting assembly of claim 14 , wherein the fan frame has a fan frame structural stiffness, the flex mount has a flex mount structural stiffness based on the fan frame structural stiffness, and the flex coupling has a flex coupling structural stiffness based on the fan frame structural stiffness.

16. The mounting assembly of claim 15 , wherein the fan frame structural stiffness includes a fan frame lateral structural stiffness, a fan frame bending structural stiffness, and a fan frame torsional structural stiffness, and the flex mount structural stiffness includes a flex mount lateral structural stiffness, a flex mount bending structural stiffness, and a flex mount torsional structural stiffness,

wherein the flex mount lateral structural stiffness and the flex mount bending structural stiffness are less than the fan frame lateral structural stiffness and the fan frame bending structural stiffness, respectively and

wherein the flex mount torsional structural stiffness is greater than the fan frame torsional structural stiffness.

17. The mounting assembly of claim 16 , wherein the fan frame lateral structural stiffness is from 400,000 lb/in to 1,2000,000 lb/in, the fan frame bending structural stiffness is from 200,000,000 in-lb/rad to 600,000,000 in-lb/rad, and the fan frame torsional structural stiffness is from 1E+11 in-lb/rad to 5E+12 in-lb/rad.

18. The mounting assembly of claim 15 , wherein the fan frame structural stiffness includes a fan frame lateral structural stiffness, a fan frame bending structural stiffness, and a fan frame torsional structural stiffness, and the flex coupling structural stiffness includes a flex coupling lateral structural stiffness, a flex coupling bending structural stiffness, and a flex coupling torsional structural stiffness,

wherein the flex coupling lateral structural stiffness and the flex coupling bending structural stiffness are less than, the fan frame lateral structural stiffness and the fan frame bending structural stiffness, respectively, and

wherein the flex coupling torsional structural stiffness is greater than the fan frame torsional structural stiffness.

19. A gas turbine engine comprising:

a gearbox assembly configured to transfer rotational energy from a turbine section to a fan; and

a mounting assembly for coupling the gearbox assembly to the gas turbine engine, the mounting assembly having:

a flex coupling configured to mount a first gear of the gearbox assembly to a rotating shaft of the gas turbine engine;

a flex mount configured to mount a second gear of the gearbox assembly to an engine static structure; and

a fan frame configured to mount a third gear of the gearbox assembly to the engine static structure,

wherein each of the flex coupling and the flex mount is characterized by a lateral impedance parameter ratio, a bending impedance parameter ratio, and a torsional impedance parameter ratio, and

wherein the lateral impedance parameter ratio of the flex coupling, the flex mount, or both is less than or equal to 0.5,

wherein the bending impedance parameter ratio of the flex coupling, the flex mount, or both is less than or equal to 0.5, and

wherein the torsional impedance parameter ratio of the flex coupling, the flex mount, or both is greater than or equal to 0.1.

20. The gas turbine engine of claim 19 , further comprising an oil transfer device configured to deliver a lubricant to the gearbox assembly.

Assignments (2)

Priority Claims (1)

Continuity (1)

References Cited (33)