Gas turbine and component-temperature adjustment method therefor

Patent metadata

Field	Value
Publication number	US-2018340468-A1
Application number	US-201615778122-A
Country	US
Kind code	A1
Filing date	Nov 25, 2016
Priority date	Nov 26, 2015
Publication date	Nov 29, 2018
Grant date	—

Abstract

A gas turbine includes a compressor, a turbine, an extraction line, and a component introduction line. A compressed air from an intermediate compression stage of the compressor, as an extraction air, is extracted through the extraction line and is introduced to a first component configuring a portion of the turbine casing through the extraction line. The extraction air, which has passed through the first component, is introduced to a second component serving as a component configuring the turbine through the component introduction line. The second component is a low-pressure component, which is disposed under a pressure environment lower than a pressure of the compressed air at an outlet of the intermediate compression stage.

First claim

1 - 32 . (canceled)

33 . A gas turbine comprising:
a compressor which includes a plurality of compression stages and is configured to sequentially compress air at each of the compression stages; a combustor which is configured to combust a fuel in air compressed by the compressor to generate a combustion gas; a turbine which includes a turbine rotor which is rotated about an axis by the combustion gas, a tubular turbine casing which covers the turbine rotor, and a plurality of vane rows which are fixed to an inner peripheral side of the turbine casing; an extraction line through which the compressed air from an intermediate compression stage among the plurality of compression stages is extracted as an extraction air and the extraction air is introduced to a first component configuring a portion of the turbine casing; and a component introduction line through which the extraction air which has passed through the first component is introduced to a second component, which is different from the first component, among components configuring the turbine, wherein a first air flow path which extends in an axial direction in which the axis extends and through which the extraction air from the extraction line flows is formed in the first component, wherein the second component is a low-pressure component which is disposed under a pressure environment lower than a pressure of the compressed air at an outlet of the intermediate compression stage, and wherein a second air flow path through which the extraction air from the component introduction line flows is formed in the low-pressure component, wherein in the first air cooling step, the extraction air flowing through the first component flows into a reuse pipe, a first end of the reuse pipe is connected to the first component, and a second end of the reuse pipe is connected to the turbine casing from the outside of the turbine casing.

34 . A gas turbine comprising:
a compressor which includes a plurality of compression stages and is configured to sequentially compress air at each of the compression stages; a combustor which is configured to combust a fuel in air compressed by the compressor to generate a combustion gas; a turbine which includes a turbine rotor which is rotated about an axis by the combustion gas, a tubular turbine casing which covers the turbine rotor, and a plurality of vane rows which are fixed to an inner peripheral side of the turbine casing; an extraction line through which the compressed air from an intermediate compression stage among the plurality of compression stages is extracted as an extraction air and the extraction air is introduced to a first component configuring a portion of the turbine casing; and a component introduction line through which the extraction air which has passed through the first component is introduced to a second component, which is different from the first component, among components configuring the turbine, wherein a first air flow path which extends in an axial direction in which the axis extends and through which the extraction air from the extraction line flows is formed in the first component, wherein the second component is a low-pressure component which is disposed under a pressure environment lower than a pressure of the compressed air at an outlet of the intermediate compression stage, wherein a second air flow path through which the extraction air from the component introduction line flows is formed in the low-pressure component, wherein the low-pressure component is disposed on an axially downstream side, which is a side to which the combustion gas flows, from the first air flow path in the first component, wherein the extraction line is connected to an axially downstream end of the first air flow path, and wherein the component introduction line is connected to an axially upstream end of the first air flow path.

35 . The gas turbine according to claim 33 ,
wherein the low-pressure component is disposed in a region, in which the first air flow path in the first component exists, in the axial direction.

36 . The gas turbine according to claim 33 ,
wherein the second air flow path of the low-pressure component is formed such that the extraction air from the component introduction line is able to flow to a combustion gas flow path through which the combustion gas flows.

37 . The gas turbine according to claim 33 ,
wherein each of the plurality of vane rows includes a plurality of vanes which are arranged in a circumferential direction with respect to the axis, and wherein the low-pressure component is a plurality of vanes configuring at least one vane row which is disposed under the pressure environment lower than the pressure of the compressed air at the outlet of the intermediate compression stage, among the plurality of vane rows.

38 . The gas turbine according to claim 37 ,
wherein the vane includes a vane body which extends in a radial direction with respect to the axis to form a vane profile, an outer shroud which is provided radially outside the vane body, and an inner shroud which is provided radially inside the vane body, and wherein the second air flow path is formed in the plurality of vanes configuring the low-pressure component, and the extraction air from the component introduction line flows from the outer shroud into the second air flow path and flows out through the second air flow path from the inner shroud via the vane body.

39 . The gas turbine according to claim 33 ,
wherein the turbine rotor includes a rotor shaft which extends in the axial direction about the axis and a plurality of blade rows which are arranged at intervals in the axial direction, wherein the low-pressure component is a plurality of blades configuring at least one blade row which is disposed under the pressure environment lower than the pressure of the compressed air at the outlet of the intermediate compression stage, among the plurality of blade rows, wherein a third air flow path which extends from an axial end of the rotor shaft to the plurality of blades configuring the low-pressure component is formed in the rotor shaft, and wherein the component introduction line includes the third air flow path of the rotor shaft.

40 . The gas turbine according to claim 33 ,
wherein the turbine rotor includes a rotor shaft which extends in the axial direction about the axis and a plurality of blade rows which are arranged at intervals in the axial direction, wherein the turbine casing includes a plurality of ring segments which face the blade rows in the radial direction with respect to the axis, a vane ring which supports the plurality of ring segments and the plurality of vane rows from a radially outer side, and a casing main body which supports the vane ring from the radially outer side, and wherein the first component is the vane ring.

41 . The gas turbine according to claim 40 ,
wherein the vane ring is an integrally formed product in the axial direction in a region in which the first air flow path is formed.

42 . A gas turbine comprising:
a compressor which includes a plurality of compression stages and is configured to sequentially compress air at each of the compression stages; a combustor which is configured to combust a fuel in air compressed by the compressor to generate a combustion gas; a turbine which includes a turbine rotor which is rotated about an axis by the combustion gas, a tubular turbine casing which covers the turbine rotor, and a plurality of vane rows which are fixed to an inner peripheral side of the turbine casing; an extraction line through which the compressed air from an intermediate compression stage among the plurality of compress

Assignees

• Mitsubishi Hitachi Power Sys
• Mitsubishi Hitachi Power Sys

Inventors

• Takamura Keita
• Takata Kazumasa

Classifications

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F01D11/24

  by selectively cooling-heating stator or rotor components · CPC title

• F01D17/00

  Regulating or controlling by varying flow (for reversing F01D1/30; by varying rotor-blade position F01D7/00; specially for starting F01D19/00; shutting-down F01D21/00; regulating or controlling in general G05 {; specially adapted for hand-held tools or the like F01D15/06}) · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title