Gas turbine rotor, gas turbine, and gas turbine equipment

Patent metadata

Field	Value
Publication number	US-10738618-B2
Application number	US-201615768709-A
Country	US
Kind code	B2
Filing date	Oct 21, 2016
Priority date	Oct 23, 2015
Publication date	Aug 11, 2020
Grant date	Aug 11, 2020

Abstract

A ventilation flow path, a cooling air flow path, a mixing space, and a mixed air flow path are formed in a gas turbine rotor. The ventilation flow path guides compressed air farther on an axially upstream side than an air discharge port of a compressor to an interior of a compressor rotor as compressor extracted air. The cooling air flow path guides cooling air to a part farther on an axially downstream side than the air discharge port. The compressor extracted air and the cooling air are mixed in the mixing space. The mixed air flow path guides mixed air containing the compressor extracted air and the cooling air into a turbine rotor.

First claim

The invention claimed is:

1. A gas turbine rotor inside a gas turbine casing, the gas turbine rotor comprising:
a compressor rotor of a compressor that rotates around an axial line extending in an axial direction of the gas turbine rotor;
an intermediate rotor shaft that rotates around the axial line and is connected to the compressor rotor;
a turbine rotor of a turbine, connected to the compressor rotor via the intermediate rotor shaft, that rotates integrally with the compressor rotor around the axial line;
a ventilation flow path configured to guide compressed air flowing inside the gas turbine casing to an interior of the compressor rotor, wherein the ventilation flow path is axially upstream of an air discharge port of the compressor;
a cooling air flow path configured to guide cooling air having a lower temperature than that of the compressed air flowing through the ventilation flow path to a part of the gas turbine rotor that is axially downstream of the air discharge port of the compressor, wherein the cooling air flow path is formed in the intermediate rotor shaft;
a mixing space which is connected to the ventilation flow path and the cooling air flow path, and in which the compressed air that has flowed through the ventilation flow path and the cooling air that has flowed through the cooling air flow path are mixed; and
a mixed air flow path that is connected to the mixing space and guides mixed air generated by the mixing of the compressed air and the cooling air into the turbine rotor.

2. The gas turbine rotor according to claim 1 , wherein the mixing space is formed in the intermediate rotor shaft.

3. The gas turbine rotor according to claim 1 , wherein
the compressor rotor has a compressor rotor shaft and a plurality of blade rows attached to an outer circumference of the compressor rotor shaft and aligned in the axial direction, and
the ventilation flow path has an introduction part for guiding the compressed air flowing between two blade rows adjacent in the axial direction of the plurality of blade rows of the compressor rotor to the interior of the compressor rotor, a plurality of branch parts which branch from the introduction part and are formed in mutually different positions in the axial direction, and into which the compressed air flows from the introduction part, and a collection part which is connected to each of the plurality of branch parts, into which the compressed air flows after passing through the plurality of branch parts, and through which the compressed air that has flowed in flows out to the mixing space.

4. A gas turbine comprising:
the gas turbine rotor according to claim 1 ; and
the gas turbine casing.

5. A gas turbine assembly comprising:
the gas turbine according to claim 4 ; and
a cooling system for generating the cooling air by cooling the compressed air which is air compressed by the compressor of the gas turbine, wherein
the gas turbine has a cooling air introduction member for guiding the cooling air generated in the cooling system to the cooling air flow path of the gas turbine rotor.

6. A gas turbine rotor inside a gas turbine casing, the gas turbine rotor comprising:
a compressor rotor of a compressor that rotates around an axial line extending in an axial direction of the gas turbine rotor;
a turbine rotor of a turbine connected to the compressor rotor and rotates integrally with the compressor rotor around the axial line;
a ventilation flow path configured to guide compressed air flowing inside the gas turbine casing to an interior of the compressor rotor, wherein the ventilation flow path is axially upstream of an air discharge port of the compressor;
a cooling air flow path configured to guide cooling air having a lower temperature than that of the compressed air flowing through the ventilation flow path to a part of the gas turbine rotor that is axially downstream of the air discharge port of the compressor;
a mixing space which is connected to the ventilation flow path and the cooling air flow path, and in which the compressed air that has flowed through the ventilation flow path and the cooling air that has flowed through the cooling air flow path are mixed; and
a mixed air flow path that is connected to the mixing space and guides mixed air generated by the mixing of the compressed air and the cooling air into the turbine rotor,
wherein the turbine rotor has a turbine rotor shaft and a plurality of blade rows attached to an outer circumference of the turbine rotor shaft and aligned in the axial direction, and
the mixed air flow path is connected through an interior of the turbine rotor shaft to a blade row of the plurality of blade rows, wherein the blade row is positioned axially downstream of a first blade row of the plurality of blade rows that is axially upstream of all other blade rows of the plurality of blade rows.

7. The gas turbine rotor according to claim 6 , wherein, in addition to a first cooling air flow path which is the cooling air flow path connected to the mixing space, a second cooling air flow path for guiding the cooling air to the first blade row is also formed.

8. The gas turbine rotor according to claim 7 , wherein a third cooling air flow path linking the second cooling air flow path and the mixed air flow path is formed in the turbine rotor.

9. The gas turbine rotor according to claim 6 , wherein
the compressor rotor has a compressor rotor shaft and a plurality of blade rows attached to an outer circumference of the compressor rotor shaft and aligned in the axial direction, and
the ventilation flow path has an introduction part for guiding the compressed air flowing between two blade rows adjacent in the axial direction of the plurality of blade rows of the compressor rotor to the interior of the compressor rotor, a plurality of branch parts which branch from the introduction part and are formed in mutually different positions in the axial direction, and into which the compressed air flows from the introduction part, and a collection part which is connected to each of the plurality of branch parts, into which the compressed air flows after passing through the plurality of branch parts, and through which the compressed air that has flowed in flows out to the mixing space.

10. A gas turbine comprising:
the gas turbine rotor according to claim 6 ; and
the gas turbine casing.

11. A gas turbine assembly comprising:
the gas turbine according to claim 10 ; and
a cooling system for generating the cooling air by cooling the compressed air which is air compressed by the compressor of the gas turbine, wherein
the gas turbine has a cooling air introduction member for guiding the cooling air generated in the cooling system to the cooling air flow path of the gas turbine rotor.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Hashimoto Shinya
• Takamura Keita

Classifications

• F01D5/08 Primary

  Heating, heat-insulating or cooling means {(specially adapted for radial flow machines or engines F01D5/04)} · CPC title

• F05D2260/97

  Reducing windage losses · CPC title

• F04D29/053

  Shafts · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title