Bearing load sharing system

Patent metadata

Field	Value
Publication number	US-10060480-B2
Application number	US-201514958306-A
Country	US
Kind code	B2
Filing date	Dec 3, 2015
Priority date	Dec 9, 2014
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A bearing load sharing system comprising:
first and second rotors extending in an axial direction; a first thrust bearing having an inner race and an outer race, the inner race connected to the first rotor; a second thrust bearing having an inner race and an outer race, the inner race connected to the second rotor; and an inter-rotor bearing having an inner race and an outer race, the inner race connected to one of the first and second rotor and the outer race connected to the other of the first and second rotor; wherein the outer race of the first bearing and/or the outer race of the second bearing is movable to vary the axial spacing between the outer races.

First claim

What is claimed is:

1. A bearing load sharing system comprising:
first and second rotors extending in an axial direction;
a first thrust bearing having an inner race and an outer race, the inner race connected to the first rotor;
a second thrust bearing having an inner race and an outer race, the inner race connected to the second rotor; and
an inter-rotor bearing having an inner race and an outer race, the inner race connected to one of the first and second rotor and the outer race connected to the other of the first and second rotor;
wherein at least one of the outer race of the first thrust bearing and the outer race of the second thrust bearing is movable to vary axial spacing between the outer race of the first thrust bearing and the outer race of the second thrust bearing so as to transfer axial load between the first thrust bearing on the first rotor and the second thrust bearing on the second rotor.

2. The system according to claim 1 wherein:
the first rotor is a low pressure rotor extending from an upstream fan to a downstream low pressure turbine;
the second rotor is an intermediate pressure rotor extending from an upstream intermediate pressure compressor to a downstream intermediate pressure turbine;
the first thrust bearing is a low pressure load-share thrust bearing (LP1); and
the second thrust bearing is a first intermediate pressure load-share thrust bearing (IP1).

3. The system according to claim 2 wherein the intermediate pressure load-share thrust bearing (IP1) is downstream from the low pressure load-share thrust bearing (LP1).

4. The system according to claim 3 wherein the low pressure load-share thrust bearing (LP1) is positioned on the low pressure rotor proximal the fan and the intermediate pressure load-share thrust bearing (IP1) is positioned on the intermediate rotor at the upstream axial end of the intermediate pressure compressor.

5. The system according to claim 2 wherein the low pressure load-share thrust bearing (LP1) and the intermediate pressure load-share thrust bearing (IP1) are substantially axially aligned.

6. The system according to claim 2 wherein the inter-rotor bearing is a low pressure inter-rotor thrust bearing (LP2), the inner race of the inter-rotor bearing is connected to the low pressure rotor, and the outer race of the inter-rotor bearing is connected to the intermediate pressure rotor.

7. The system according to claim 1 wherein:
the first rotor is a high pressure rotor extending from an upstream high pressure compressor to a downstream high pressure turbine;
the second rotor is an intermediate pressure rotor extending from an upstream intermediate pressure compressor to a downstream intermediate pressure turbine;
the first thrust bearing is a high pressure load-share thrust bearing (HP1); and
the second thrust bearing is an intermediate pressure load-share thrust bearing (IP2′).

8. The system according to claim 7 wherein the high pressure load-share thrust bearing (HP1) is downstream from the intermediate pressure load-share thrust bearing (IP2′).

9. The system according to claim 8 wherein the high pressure load-share thrust bearing (HP1) is positioned on the high pressure rotor proximal and upstream from the high pressure compressor and the intermediate pressure load-share thrust bearing (IP2′) is positioned on the intermediate pressure rotor proximal the downstream axial end of the intermediate pressure compressor.

10. The system according to claim 7 wherein the high pressure load-share thrust bearing (HP1) and the intermediate pressure load-share bearing (IP2′) are substantially axially aligned.

11. The system according to claim 7 wherein the inter-rotor bearing is a high pressure inter-rotor thrust bearing (HP2), the inner race of the inter-rotor bearing is connected to the intermediate pressure rotor, and the outer race of the inter-rotor bearing is connected to the high pressure rotor.

12. A gas turbine engine having the bearing load sharing system according to claim 1 .

13. The system according to claim 1 wherein the outer races of the first and second thrust bearings are flexibly connected by a hydraulic connection to effect movement of the at least one of the outer race of the first thrust bearing and the outer race of the second thrust bearing.

14. A bearing load sharing system comprising:
first and second rotors extending in an axial direction;
a first thrust bearing having an inner race and an outer race, the inner race connected to the first rotor;
a second thrust bearing having an inner race and an outer race, the inner race connected to the second rotor;
an inter-rotor bearing having an inner race and an outer race, the inner race connected to the first rotor and the outer race connected to the second rotor;
a third rotor extending in an axial direction;
a third bearing having an inner race and an outer race, the inner race connected to the second rotor;
a fourth bearing having an inner race and an outer race, the inner race connected to the third rotor; and
a second inter-rotor bearing having an inner race and an outer race, the inner race connected to the second rotor, and the outer race connected to the third rotor,
wherein at least one of the outer race of the first thrust bearing and the outer race of the second thrust bearing is movable to vary axial spacing between the outer race of the first thrust bearing and the outer race of the second thrust bearing so as to transfer axial load between the first thrust bearing on the first rotor and the second thrust bearing on the second rotor.

15. The system according to claim 14 wherein:
the first rotor is a low pressure rotor extending from an upstream fan to a downstream low pressure turbine;
the second rotor is an intermediate pressure rotor extending from an upstream intermediate pressure compressor to a downstream intermediate pressure turbine;
the third rotor is a high pressure rotor extending from an upstream high pressure compressor to a downstream high pressure turbine;
the first thrust bearing is a low pressure load-share thrust bearing (LP1);
the second thrust bearing is a first intermediate pressure load-share thrust bearing (IP1);
the third bearing is a second intermediate pressure load-share bearing (IP2′); and
the fourth bearing is a high pressure load-share thrust bearing (HP1).

16. The system according to claim 14 wherein the outer races of the first and second thrust bearings and/or the third and fourth bearings are flexibly connected by a hydraulic connection to effect movement of one or both of the outer races.

17. The system according to claim 14 wherein the outer races of the first and second thrust bearings and/or the third and fourth bearings are flexibly connected by a compliant element to effect movement of one or both of the outer races.

Assignees

• Rolls Royce Plc

Inventors

• Gallimore Stephen

Classifications

• F01D25/168

  for axial load mainly · CPC title

• F05D2240/54

  Radial bearings · CPC title

• F16C19/547

  with two angular contact rolling bearings · CPC title

• F05D2240/52

  Axial thrust bearings · CPC title

• F16C41/02 Primary

  Arrangements for equalising the load on a plurality of bearings or their elements · CPC title