Rotor shaft architectures for a gas turbine engine and methods of assembly thereof

Patent metadata

Field	Value
Publication number	US-2018119574-A1
Application number	US-201615341838-A
Country	US
Kind code	A1
Filing date	Nov 2, 2016
Priority date	Nov 2, 2016
Publication date	May 3, 2018
Grant date	—

Abstract

A shaft assembly for a rotary machine, the rotary machine includes a low pressure compressor, a high pressure compressor, a high pressure turbine, and a low pressure turbine. The shaft assembly includes an outer shaft configured to couple the high pressure compressor to the high pressure turbine. The outer shaft includes a first forward bearing assembly positioned forward of the high pressure compressor, and a first aft bearing assembly positioned between the high pressure compressor and the high pressure turbine. The shaft assembly also includes an inner shaft rotatable about a common axis with the outer shaft that at least partially extends about the inner shaft. The inner shaft is configured to couple the low pressure compressor to the low pressure turbine. The inner shaft includes a second forward bearing assembly positioned forward of the low pressure compressor, and a second aft bearing assembly positioned proximate the high pressure turbine.

First claim

What is claimed is:

1 . A shaft assembly for a rotary machine including a low pressure compressor, a high pressure compressor, a high pressure turbine, and a low pressure turbine in a serial flow relationship, said shaft assembly comprising:
an outer shaft configured to couple the high pressure compressor to the high pressure turbine, said outer shaft comprising:
a first forward bearing assembly positioned forward of the high pressure compressor; and
a first aft bearing assembly positioned between the high pressure compressor and the high pressure turbine; and
an inner shaft rotatable about a common axis with said outer shaft, wherein said outer shaft at least partially extends about said inner shaft, said inner shaft configured to couple the low pressure compressor to the low pressure turbine, said inner shaft comprising:
a second forward bearing assembly positioned forward of the low pressure compressor; and
a second aft bearing assembly positioned proximate the high pressure turbine.

2 . The shaft assembly in accordance with claim 1 , wherein a span of said inner shaft is defined between said second forward bearing assembly and said second aft bearing assembly, said second aft bearing assembly configured to reduce said span of said inner shaft.

3 . The shaft assembly in accordance with claim 1 , wherein a position of said second forward bearing assembly and a position of said second aft bearing assembly are determined to facilitate increasing a rotational speed of said inner shaft associated with inducing a bending natural frequency mode.

4 . The shaft assembly in accordance with claim 1 , wherein at least a portion of said second aft bearing assembly is positioned radially inward from the high pressure turbine.

5 . The shaft assembly in accordance with claim 1 , wherein said outer shaft further comprises an outboard bearing assembly positioned aft of the high pressure turbine.

6 . The shaft assembly in accordance with claim 5 , wherein said outboard bearing assembly comprises an air bearing assembly.

7 . The shaft assembly in accordance with claim 5 , wherein said outboard bearing assembly has a first diameter and said second aft bearing assembly has a second diameter, the first diameter greater than the second diameter.

8 . The shaft assembly in accordance with claim 1 , wherein at least one of said first forward bearing assembly, said second forward bearing assembly, said first aft bearing assembly, and said second aft bearing assembly comprises a roller element bearing.

9 . The shaft assembly in accordance with claim 1 , wherein said inner shaft is coupled to a gearbox.

10 . A shaft assembly for a rotary machine including a low pressure compressor, a high pressure compressor, a high pressure turbine, and a low pressure turbine in a serial flow relationship, said shaft assembly comprising:
an outer shaft configured to couple the high pressure compressor to the high pressure turbine, said outer shaft comprising:
a first forward bearing assembly positioned forward of the high pressure compressor; and
a first aft bearing assembly positioned aft of the high pressure turbine; and
an inner shaft rotatable about a common axis with said outer shaft, wherein said outer shaft at least partially extends about said inner shaft, said inner shaft configured to couple the low pressure compressor to the low pressure turbine, said inner shaft comprising:
a second forward bearing assembly positioned forward of the low pressure compressor; and
a second aft bearing assembly positioned forward of the low pressure turbine, at least a portion of said second aft bearing assembly is positioned in a stacked relationship with said first aft bearing assembly.

11 . The shaft assembly in accordance with claim 10 , wherein a span of said inner shaft is defined between said second forward bearing assembly and said second aft bearing assembly, said second aft bearing assembly configured to reduce said span of said inner shaft.

12 . The shaft assembly in accordance with claim 10 , wherein a position of said second forward bearing assembly and a position of said second aft bearing assembly are determined to facilitate increasing a rotational speed of said inner shaft associated with inducing a bending natural frequency mode

13 . The shaft assembly in accordance with claim 10 , wherein a said first aft bearing assembly and at least a portion of said second aft bearing assembly coupled to a static frame assembly.

14 . The shaft assembly in accordance with claim 13 , wherein said static frame assembly is positioned between said first aft bearing assembly and at least a portion of said second aft bearing assembly.

15 . The shaft assembly in accordance with claim 10 , wherein said first aft bearing assembly is coupled to a first static frame assembly and said second aft bearing assembly is coupled to a second static frame assembly.

16 . The shaft assembly in accordance with claim 10 , wherein said first aft bearing assembly has a first diameter and said second aft bearing assembly has a second diameter, the first diameter greater than the second diameter.

17 . The shaft assembly in accordance with claim 10 , wherein at least one of said first forward bearing assembly, said second forward bearing assembly, said first aft bearing assembly, and said second aft bearing assembly comprises a roller element bearing.

18 . The shaft assembly in accordance with claim 10 , wherein said inner shaft is coupled to a gearbox.

19 . A method of assembling a shaft assembly for a rotary machine, including a low pressure compressor, a high pressure compressor, a high pressure turbine, and a low pressure turbine in a serial flow relationship, said method comprising:
coupling the high pressure compressor to the high pressure turbine through an outer shaft; coupling a first forward bearing assembly to the outer shaft forward of the high pressure compressor; coupling a first aft bearing assembly to the outer shaft between the high pressure compressor and the high pressure turbine; coupling the low pressure compressor to the low pressure turbine through an inner shaft, wherein the outer shaft at least partially extends about the inner shaft; coupling a second forward bearing assembly to the inner shaft forward of the low pressure compressor; coupling a second aft bearing assembly to the inner shaft proximate the high pressure turbine; and positioning the outer shaft radially outward from the inner shaft to define a gap therebetween such that the inner shaft and the outer shaft are rotatable about a common axis.

20 . The method in accordance with claim 19 further comprising coupling an outboard bearing assembly to the outer shaft aft of the high pressure turbine.

Assignees

• Gen Electric

Inventors

• Ertas Bugra Han
• Miller Brandon Wayne

Classifications

• F04D29/321

  for axial flow compressors · CPC title

• F02K3/06

  with front fan · CPC title

• F05D2240/60

  Shafts · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2220/32

  in gas turbines · CPC title