Gas turbine engine split torque fan drive gear system

Patent metadata

Field	Value
Publication number	US-10072571-B2
Application number	US-201514597410-A
Country	US
Kind code	B2
Filing date	Jan 15, 2015
Priority date	Jan 15, 2015
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A gas turbine engine includes a turbine section configured to rotate about an engine axis relative to an engine static structure. A fan section is configured to rotate about the engine axis relative to the engine static structure. A geared architecture operatively connects the fan section to the turbine section. The geared architecture includes an input gear and an output gear both configured to rotate about the engine axis. A set of idler gears are arranged radially outward relative to and operatively coupling with the input and output gears.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a turbine section configured to rotate about an engine axis relative to an engine static structure;
a fan section configured to rotate about the engine axis relative to the engine static structure; and
a geared architecture operatively connects the fan section to the turbine section, the geared architecture includes an input gear and an output gear both configured to rotate about the engine axis, and a set of idler gears arranged radially outward relative to and operatively coupling with the input and output gears, wherein the geared architecture is without a ring gear.

2. The engine according to claim 1 , wherein the turbine section includes a high pressure turbine mounted for rotation to a high spool, and low pressure turbine mounted for rotation to a low spool and arranged downstream from the high pressure turbine, the low pressure turbine coupled to the input gear.

3. The engine according to claim 2 , wherein the engine static structure provides a bypass flow path and a core flow path, the turbine section arranged in the core flow path, and the fan section arranged in the bypass flow path.

4. The engine according to claim 2 , wherein the fan section is coupled to the output gear.

5. The engine according to claim 1 , wherein the input gear and the output gear are arranged axially adjacent to one another.

6. The engine according to claim 1 , wherein the set of idler gears are mounted to the engine static structure and fixed against rotation about the engine axis.

7. The engine according to claim 6 , wherein the set of idler gears includes multiple idler shafts arranged circumferentially about the input gear and the output gear.

8. The engine according to claim 7 , wherein the input gear has a first and second input gear portions axially spaced from one another and that provide different tooth geometries than one another.

9. The engine according to claim 7 , wherein the output gear has a first and second output gear portions axially spaced from one another and that provide different tooth geometries than one another.

10. The engine according to claim 7 , wherein each idler shaft has a first idler gear meshing with the input gear and a second idler gear meshing with the output gear.

11. The engine according to claim 7 , wherein the set of idler gears includes first and second sets of idler gears, the first set of idler gears meshing with the input gear and the second set of idler gears, and the second set of idler gears meshing with the output gear.

12. The engine according to claim 11 , wherein the second set of idler gears is arranged radially outward from the first set of idler gears.

13. The engine according to claim 6 , comprising rolling element bearings that support the set of idler gears relative to the engine static structure.

14. The engine according to claim 1 , wherein the geared architecture provides a gear reduction ratio in the range of 8:1.

15. The engine according to claim 1 , wherein the geared architecture is arranged forward of the turbine section.

16. The engine according to claim 15 , comprising a compressor section arranged upstream of the turbine section and downstream from the fan section, the geared architecture arranged forward of the compressor section.

Assignees

• United Technologies Corp

Inventors

• Zimmitti Jonathan F
• Stachowiak David Allen

Classifications

• F02C3/107 Primary

  with two or more rotors connected by power transmission · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2220/323

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

• F02K3/06

  with front fan · CPC title

• F16H1/22

  with a plurality of driving or driven shafts; with arrangements for dividing torque between two or more intermediate shafts · CPC title