Gas turbine rotor cover

Patent metadata

Field	Value
Publication number	US-10443433-B2
Application number	US-201615259555-A
Country	US
Kind code	B2
Filing date	Sep 8, 2016
Priority date	Sep 8, 2015
Publication date	Oct 15, 2019
Grant date	Oct 15, 2019

Abstract

A gas turbine rotor cover includes a body, the body having an inner side facing towards a central axis and an outer side facing away from the central axis, wherein the gas turbine rotor cover is configured and arranged to extend in an axial direction and a circumferential direction relative to the central axis. An inner layer of insulation is attached to the inner side of the body and extends along at least part of the length of the body in the axial direction and/or an outer layer of insulation is attached to the outer side of the body, and extends along at least part of the length of the body in the axial direction. A gas turbine containing the gas turbine rotor cover is also disclosed.

First claim

The invention claimed is:

1. A gas turbine rotor cover comprising:
a body, the body having an inner side configured to face towards a rotor central axis and an outer side configured to face away from the rotor central axis, wherein the gas turbine rotor cover is configured to extend in a rotor axial direction and a circumferential direction relative to the rotor central axis;
a diffuser;
an inner layer of thermal insulation attached to the inner side of the body which, extends along at least part of a length of the body in the rotor axial direction;
an outer layer of thermal insulation attached to the outer side of the body, which extends along at least part of the length of the body in the rotor axial direction; and
the outer layer of thermal insulation is configured to overlap with the diffuser in the rotor axial direction, and wherein at least part of the outer layer of thermal insulation configured to overlap with the diffuser includes a thermal barrier coating.

2. The gas turbine rotor cover of claim 1 , wherein the gas turbine rotor cover is configured to overlap with the diffuser in the rotor axial direction when installed in a gas turbine having the diffuser.

3. The gas turbine rotor cover of claim 1 , wherein at least one of the inner and/or outer layers of thermal insulation extend only on a portion of the gas turbine rotor cover that is configured to not overlap with the diffuser in the rotor axial direction.

4. The gas turbine rotor cover of claim 1 , wherein at least one of the inner layer of thermal insulation and/or the outer layer of thermal insulation is at least 10 mm thick in a radial direction relative to the rotor central axis.

5. A gas turbine comprising the gas turbine rotor cover according to claim 1 .

6. The gas turbine of claim 5 , comprising:
a compressor, a combustor downstream of the compressor;
a turbine downstream of the combustor; and
a rotor extending from the compressor to the turbine, wherein the gas turbine rotor cover extends between the compressor and the turbine in the rotor axial direction and extends around at least part of the rotor in a circumferential direction relative to the rotor central axis.

7. The gas turbine of claim 6 , comprising:
an outer housing extending around at least part of the gas turbine, wherein the gas turbine rotor cover is supported in least in the rotor axial direction by the outer housing.

8. The gas turbine of claim 6 , wherein the turbine comprises:
a first vane, wherein the first vane is supported at least in the rotor axial direction by the gas turbine rotor cover.

9. The gas turbine of claim 8 , wherein a radial thickness and an axial extension of the first and/or second layers of thermal insulation are configured and arranged so as to minimise movement of the first vane relative to a sequential liner by balancing a thermal time constant of the rotor cover with a thermal time constant of the outer housing.

10. The gas turbine of claim 6 , wherein the gas turbine comprises:
the diffuser downstream of the compressor, and at least one of the inner layer of thermal insulation and the outer layer of thermal insulation extend only on a portion of the gas turbine rotor cover that does not overlap with the diffuser in the rotor axial direction.

11. The gas turbine of claim 10 comprising:
a thermal barrier coating applied on at least part of the axial diffuser.

12. A gas turbine rotor cover comprising:
a body, the body having an inner side configured to face towards a rotor central axis and an outer side configured to face away from the rotor central axis, wherein the gas turbine rotor cover is configured to extend in a rotor axial direction and a circumferential direction relative to the rotor central axis; and
an outer layer of thermal insulation attached to the outer side of the body, which extends along at least part of the length of the body in the rotor axial direction,
wherein the gas turbine rotor cover is configured to overlap with a diffuser in the rotor axial direction when installed in a gas turbine having the diffuser,
wherein the outer layer of thermal insulation is configured to overlap with the diffuser in the rotor axial direction, and at least part of the outer layer of thermal insulation configured to overlap with the diffuser includes a thermal barrier coating.

13. The gas turbine rotor cover of claim 12 , wherein the outer layer of thermal insulation is at least 10 mm thick in a radial direction relative to the rotor central axis.

14. A gas turbine comprising:
a compressor;
a combustor downstream of the compressor;
a turbine downstream of the combustor;
a rotor extending from the compressor to the turbine;
a gas turbine rotor cover extends between the compressor and the turbine in a rotor axial direction and extends around at least part of the rotor in a circumferential direction relative to a rotor central axis, the gas turbine rotor cover including,
a body, the body having an inner side configured to face towards the rotor central axis and an outer side configured to face away from the rotor central axis, wherein the gas turbine rotor cover is configured to extend in the rotor axial direction and the circumferential direction relative to the rotor central axis, an inner layer of thermal insulation attached to the inner side of the body which, extends along at least part of a length of the body in the rotor axial direction, and an outer layer of thermal insulation attached to the outer side of the body, which extends along at least part of the length of the body in the rotor axial direction;
a diffuser; and
an outer housing extending around at least part of the gas turbine, wherein the gas turbine rotor cover is supported in least in the rotor axial direction by the outer housing,
wherein the outer layer of thermal insulation is configured to overlap with the diffuser in the rotor axial direction, and wherein at least part of the outer layer of thermal insulation configured to overlap with the diffuser includes a thermal barrier coating.

15. The gas turbine of claim 14 , wherein the turbine comprises:
a first vane, wherein the first vane is supported at least in the rotor axial direction by the gas turbine rotor cover.

16. The gas turbine of claim 15 , wherein a radial thickness and an axial extension of the first and/or second layers of thermal insulation are configured to minimise movement of the first vane relative to a sequential liner by balancing a thermal time constant of the rotor cover with a thermal time constant of the outer housing.

17. The gas turbine of claim 14 comprising:
a diffuser downstream of the compressor, and at least one of the inner layer of thermal insulation and the outer layer of thermal insulation extend only on a portion of the gas turbine rotor cover that does not overlap with the diffuser in the rotor axial direction.

18. The gas turbine of claim 17 comprising:
a thermal barrier coating applied on at least part of the diffuser.

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Cataldi Giovanni
• Corradi Mauro
• Sistaninia Meisam
• Schaefer Martin
• Herzog Tobias

Classifications

• F01D25/145 Primary

  Thermally insulated casings · CPC title

• F05D2260/231

  Preventing heat transfer · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F01D25/08 Primary

  Cooling (of machines or engines in general F01P); Heating; Heat-insulation (of blade-carrying members, of blades F01D5/00) · CPC title