Gas turbine architecture

Patent metadata

Field	Value
Publication number	US-10151249-B2
Application number	US-201514866113-A
Country	US
Kind code	B2
Filing date	Sep 25, 2015
Priority date	Oct 3, 2014
Publication date	Dec 11, 2018
Grant date	Dec 11, 2018

Abstract

A geared architecture for a gas turbine comprising an output shaft for connection with a fan, an input shaft and a gearbox connecting the input shaft with the output shaft. The gearbox has a forward planet carrier plate supported by a forward radially fixed bearing structure and a rearward planet carrier plate supported by a rearward radially fixed bearing structure. By supporting the carrier plates on radially fixed bearing structures the planet carriers can rotate about their own axis to lower vibration and mesh forces within the gearbox.

First claim

The invention claimed is:

1. A geared architecture for a gas turbine, the geared architecture comprising:
an output shaft connected to a fan;
an input shaft; and
a gearbox connecting the input shaft with the output shaft, the gearbox including:
a forward carrier supported by a forward bearing structure, the forward bearing structure being axially and radially fixed relative to a central axis of the gas turbine, the forward bearing structure axially and radially fixing the forward carrier; and
a rearward carrier supported by a rearward bearing structure, the rearward bearing structure being axially and radially fixed relative to the central axis of the gas turbine, the rearward bearing structure axially and radially fixing the rearward carrier, wherein:
at least one of the forward bearing structure and the rearward bearing structure includes a squeeze film damper; and
a flexible coupling is coupled to the output shaft and the forward carrier.

2. The geared architecture according to claim 1 , wherein each bearing structure has a radially outer bearing race, the squeeze film damper being located between a gearbox support arm and the radially outer bearing race.

3. The geared architecture according to claim 2 , wherein each squeeze film damper includes a cavity filled with lubricant.

4. The geared architecture according to claim 3 , wherein the cavity is connected with a conduit in the gearbox support arm and bounded at axially spaced locations by seals permitting a controlled leakage of lubricant.

5. The geared architecture according to claim 2 , wherein the gearbox is an epicyclic gearbox having a central sun gear and a plurality of planet gears adapted to orbit the sun gear.

6. The geared architecture according to claim 5 , wherein the forward carrier includes a plurality of planet pins extending into the gearbox, each planet pin supporting a planet gear.

7. The geared architecture according to claim 6 , wherein each planet gear is supported on a respective planet pin by a spherical joint permitting relative movement of the planet pin and planet gear.

8. The geared architecture according to claim 2 , wherein the forward carrier includes a forward extending flange, the flange having a radially outer surface supported by the forward bearing structure.

9. The geared architecture according to claim 1 , wherein the rearward bearing structure has a lubricant transfer coupling configured to supply lubricant to the gearbox.

10. The geared architecture according to claim 9 , wherein the rearward carrier has an internal passage configured to supply lubricant from the lubricant transfer coupling to the gearbox.

11. The geared architecture according to claim 10 , wherein the internal passage has an inlet adjacent to the lubricant transfer coupling and one or more outlets adjacent to one or more gears in the gearbox.

12. The geared architecture according to claim 1 , wherein the gearbox includes a radially outer ring gear flexibly mounted to a fixed structure.

13. The geared architecture according to claim 12 , wherein the ring gear has two axially spaced gear regions separated by a non-geared region, and each gear region is separately mounted to the fixed structure by respective flexible mounts.

14. The geared architecture according to claim 13 , wherein the separate flexible mounts attach to the fixed structure at a common location point.

15. The geared architecture according to claim 14 , wherein a first one of the flexible mounts extends axially forward from the common location point to a respective gear region and a second one of the flexible mounts extends axially rearward from the common location point to a respective gear region.

16. A gas turbine engine comprising:
a geared architecture, the geared architecture including:
an output shaft connected to a fan;
an input shaft; and
a gearbox connecting the input shaft with the output shaft, the gearbox including:
a forward carrier supported by a forward bearing structure, the forward bearing structure being axially and radially fixed relative to a central axis of the gas turbine, the forward bearing structure axially and radially fixing the forward carrier; and
a rearward carrier supported by a rearward bearing structure, the rearward bearing structure being axially and radially fixed relative to the central axis of the gas turbine, the rearward bearing structure axially and radially fixing the rearward carrier, wherein:

at least one of the forward bearing structure and the rearward bearing structure includes a squeeze film damper; and
a flexible coupling is coupled to the output shaft and the forward carrier.

Assignees

• Rolls Royce Plc
• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Venter Gideon Daniel
• Mountney Michael John

Classifications

• F16C2360/23

  Gas turbine engines · CPC title

• F02C7/06

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

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow 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

• F16C19/26

  with a single row of rollers · CPC title