Geared turbofan with low pressure turbine features

Patent metadata

Field	Value
Publication number	US-2018355802-A1
Application number	US-201715619799-A
Country	US
Kind code	A1
Filing date	Jun 12, 2017
Priority date	Jun 12, 2017
Publication date	Dec 13, 2018
Grant date	—

Abstract

A turbine engine has a fan and a low pressure compressor that rotate at a common speed and in a common direction. A fan drive turbine drives a gear reduction to, in turn, drive the low pressure compressor and the fan at a speed which is slower than a speed of the fan drive turbine. A combustor intermediate the low pressure compressor and the fan drive turbine and a thrust bearing mount the fan drive turbine, the thrust bearing being aft of a location of the combustor. A shear section in a drive connection connecting the fan drive turbine to the gear reduction is weaker than other portions of the drive connection. The shear section is aft of the thrust bearing.

First claim

1 . A gas turbine engine comprising:
a fan and a low pressure compressor, said fan and said low pressure compressor configured for rotating at a common speed and in a common direction; a fan drive turbine configured for driving a gear reduction, in turn configured for driving said low pressure compressor and said fan at a speed which is slower than a speed of said fan drive turbine; a combustor intermediate said low pressure compressor and said fan drive turbine and a thrust bearing configured for mounting said fan drive turbine, said thrust bearing being aft of a location of said combustor; and a shear section in a drive connection configured for connecting said fan drive turbine to said gear reduction that is weaker than other portions of said drive connection, and said shear section being aft of said thrust bearing.

2 . The gas turbine engine as set forth in claim 1 , wherein there is a high pressure turbine and a high pressure compressor and said shear section is aft of said blades on high pressure turbine.

3 . The gas turbine engine as set forth in claim 1 , wherein said gear reduction is configured to be supported on a bearing forward of said gear reduction and on a second bearing which is aft of said gear reduction.

4 . The gas turbine engine as set forth in claim 3 , wherein said shear section is between 1.5 and 2.0 times weaker than any other shaft section between said fan drive turbine and said gear reduction.

5 . The gas turbine engine as set forth in claim 3 , wherein said shear section is between 1.15 and 1.5 times weaker than any other shaft section between said fan drive turbine and said gear reduction.

6 . The gas turbine engine as set forth in claim 1 , wherein said shear section is between 1.5 and 2.0 times weaker than any other shaft section between said fan drive turbine and said gear system.

7 . The gas turbine engine as set forth in claim 1 , wherein said shear section is between 1.15 and 1.5 times weaker than any other shaft section between said fan drive turbine and said gear reduction.

8 . The gas turbine engine as set forth in claim 1 , wherein said shear section is provided by connections configured for connecting a shaft section extending toward said gear reduction to a hub of said fan drive turbine.

9 . The gas turbine engine as set forth in claim 7 wherein said connections are one of bolts and pins.

10 . The gas turbine engine as set forth in claim 1 , wherein said shear section is provided by a thin portion.

11 . The gas turbine engine as set forth in claim 10 , wherein said thin portion is in a hub configured for connecting said fan drive turbine to a shaft.

12 . The gas turbine engine as set forth in claim 1 , wherein said fan drive turbine is configured to be supported on said thrust bearing and on a second bearing which is aft of said thrust bearing.

13 . The gas turbine engine as set forth in claim 1 , wherein said gear reduction is an epicyclic gear reduction.

14 . A gas turbine engine comprising:
a fan and a low pressure compressor, said fan and said low pressure compressor configured for rotating at a common speed and in a common direction; a fan drive turbine configured for driving an epicyclic gear reduction, in turn, configured for driving said low pressure compressor and said fan at a speed which is slower than a speed of said fan drive turbine; a combustor intermediate said low pressure compressor and said fan drive turbine and a thrust bearing configured for mounting said fan drive turbine, said thrust bearing being aft of a location of said combustor; a shear section in a drive connection configured for connecting said fan drive turbine to said gear reduction that is weaker than other portions of said drive connection, and said shear section being aft of said thrust bearing; and said gear reduction configured to be supported on a bearing forward of said gear reduction and on a second bearing which is aft of said gear reduction.

15 . The gas turbine engine as set forth in claim 14 , wherein there is a high pressure turbine and a high pressure compressor and said shear section is aft of blades on said high pressure turbine.

16 . The gas turbine engine as set forth in claim 14 , wherein said shear section is between 1.5 and 2.0 times weaker than any other shaft section between said fan drive turbine and said gear reduction.

17 . The gas turbine engine as set forth in claim 14 , wherein said shear section is between 1.15 and 1.5 times weaker than any other shaft section between said fan drive turbine and said gear reduction.

18 . The gas turbine engine as set forth in claim 14 , wherein said shear section is provided by connections configured for connecting a shaft section extending toward said gear reduction to a hub of said fan drive turbine.

19 . The gas turbine engine as set forth in claim 14 , wherein said shear section is provided by a thin portion.

20 . The gas turbine engine as set forth in claim 19 , wherein said thin portion is in a hub configured for connecting said fan drive turbine to a shaft.

Assignees

• United Technologies Corp

Inventors

• Sheridan William G

Classifications

• F05D2260/311

  of the frangible or shear 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

• F01D21/045 Primary

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F02K3/06

  with front fan · CPC title