Flexible support structure for a geared architecture gas turbine engine

Patent metadata

Field	Value
Publication number	US-9523422-B2
Application number	US-201313938476-A
Country	US
Kind code	B2
Filing date	Jul 10, 2013
Priority date	Jun 8, 2011
Publication date	Dec 20, 2016
Grant date	Dec 20, 2016

Abstract

A geared architecture for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan shaft and a frame which supports the fan shaft, the frame defines a frame stiffness. A plurality of gears drives the fan shaft. A flexible support at least partially supports the plurality of gears, the flexible support defines a flexible support stiffness that is less than the frame stiffness. An input coupling to the plurality of gears, the input coupling defines an input coupling stiffness with respect to the frame stiffness.

First claim

What is claimed is:

1. A geared architecture for a gas turbine engine comprising:
a fan shaft;
a frame which supports said fan shaft, said frame defines a frame stiffness;
a plurality of gears which drives said fan shaft said plurality of gears includes a gear mesh that defines a gear mesh stiffness, wherein a stiffness of a ring gear of said plurality of gears is less than 20% of said gear mesh stiffness;
a flexible support which at least partially supports said plurality of gears, said flexible support defines a flexible support stiffness that is less than said frame stiffness and less than said gear mesh stiffness; and
an input coupling to said plurality of gears, said input coupling defines an input coupling stiffness with respect to said frame stiffness and said gear mesh stiffness, wherein said flexible support stiffness and said input coupling stiffness are each less than 20% of said frame stiffness, said flexible support stiffness is less than 8% of said gear mesh stiffness, and said input coupling stiffness is less than 5% of said gear mesh stiffness.

2. The geared architecture as recited in claim 1 , wherein said frame and said flexible support are mounted to a static structure of a gas turbine engine.

3. The geared architecture as recited in claim 1 , wherein said frame and said flexible support are mounted to a front center body of a gas turbine engine.

4. The geared architecture as recited in claim 1 , wherein said input coupling is mounted to a sun gear of said gear system.

5. The geared architecture as recited in claim 4 , wherein said fan shaft is mounted to a ring gear of said gear system.

6. The geared architecture as recited in claim 5 , wherein said plurality of gears form a star system.

7. The geared architecture as recited in claim 4 , wherein said fan shaft is mounted to a planet carrier of said gear system.

8. The geared architecture as recited in claim 7 , wherein said plurality of gears form a planet system.

9. The geared architecture as recited in claim 1 , further comprising a low speed spool which drives said input coupling.

10. The geared architecture of claim 1 , wherein said flexible support stiffness defines at least one of a lateral stiffness and a transverse stiffness, said frame stiffness defines at least one of a lateral stiffness and a transverse stiffness, and said input coupling stiffness defines at least one of a lateral stiffness and a transverse stiffness.

11. The geared architecture as recited in claim 10 , wherein at least one of said flexible support stiffness and said input coupling stiffness are less than 11% of said frame stiffness.

12. The geared architecture as recited in claim 10 , wherein said flexible support stiffness and said input coupling stiffness are each less than 11% of said frame stiffness.

13. The geared architecture as recited in claim 10 , wherein said frame which supports said fan shaft and defines said frame stiffness is a K-frame bearing support, said K-frame bearing support supporting a bearing system that supports said fan shaft.

14. The geared architecture as recited in claim 10 , wherein said lateral stiffness refers to a perpendicular direction with respect to an axis of rotation of said gas turbine engine and said transverse stiffness refers to a pivotal bending movement with respect to said axis of rotation of said gas turbine engine.

15. The geared architecture of claim 1 , wherein said flexible support stiffness defines at least one of a lateral stiffness and a transverse stiffness, said gear mesh stiffness defines at least one of a lateral stiffness and a transverse stiffness, and said input coupling stiffness defines at least one of a lateral stiffness and a transverse stiffness.

16. The geared architecture as recited in claim 15 , wherein at least one of a lateral stiffness and a transverse stiffness of a ring gear of said plurality of gears is less than 12% of said gear mesh stiffness.

17. The geared architecture as recited in claim 15 , wherein at least one of a lateral stiffness and a transverse stiffness of a planet journal bearing which supports a planet gear of said plurality of gears is less than or equal to said gear mesh stiffness.

18. The geared architecture as recited in claim 15 , wherein said gear mesh stiffness is defined between a sun gear and a multiple planet gears of said plurality of gears.

19. The geared architecture as recited in claim 15 , wherein said plurality of gears floats with said fan shaft.

20. The geared architecture as recited in claim 15 , wherein a planet journal bearing which supports a planet gear of said plurality of gears defines at least one of a lateral stiffness and a transverse stiffness with respect to said gear mesh stiffness.

21. The geared architecture as recited in claim 15 , wherein a ring gear of said plurality of gears defines at least one of a lateral stiffness and a transverse stiffness with respect to said gear mesh stiffness.

22. The geared architecture as recited in claim 15 , wherein said lateral stiffness refers to a perpendicular direction with respect to an axis of rotation of said gas turbine engine and said transverse stiffness refers to a pivotal bending movement with respect to said axis of rotation of said gas turbine engine.

Assignees

• United Technologies Corp

Inventors

• Mccune Michael E
• Husband Jason

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2300/501

  Elasticity · 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

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F01D25/164

  Flexible supports; Vibration damping means associated with the bearing · CPC title