GAS TURBINE

• US 20160251962A1
• Filed: 10/10/2014
• Published: 09/01/2016
• Est. Priority Date: 10/15/2013
• Status: Abandoned Application

• Current Assignee: mitsubishi hitachi power systems, ltd. (Mitsubishi Heavy Industries, Ltd.)
• Original Assignee: mitsubishi hitachi power systems, ltd. (Mitsubishi Heavy Industries, Ltd.)
• Inventors: HASHIMOTO, Shinya
• Application Number:
  US15/028,121
• Publication Number:
  US 20160251962A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 25/14 Casings modified therefor double casings F01D25/26
• CPC Class Codes: F01D 5/081 Cooling fluid being directed on the side of the rotor disc or at the roots of the blades F01D5/087 takes precedence
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/522 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/542 Bladed diffusers fixing blades to stators F01D9/042
• CPC Class Codes: F04D 29/584 cooling or heating the machine F04D29/5846, F04D29/5853 take precedence
• CPC Class Codes: F04D 29/5853 heat insulation or conduction
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/3219 for the last stage of a compressor or a high pressure compressor
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F05D 2260/205 Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
• CPC Class Codes: F05D 2260/213 by the provision of a heat exchanger within the cooling circuit

Abstract

There is provided a gas turbine, in which a compressor is provided with: a compressor casing which forms a ring-shaped air path; a rotor; a plurality of blade bodies which are fixed on the outer circumference of the rotor and disposed in the air path; a plurality of vane bodies fixed on the compressor casing between the blade bodies and disposed in the air path; a cooling air flow passage provided so as to face the outer side of the plurality of blade bodies in the compressor casing; a first cooling air supply channel which supplies a part of compressed air to the cooling air flow passage; a cooler which cools the compressed air in the first cooling air supply channel; and a second cooling air supply channel which supplies the cooling air from the cooling air flow passage to a part to be cooled of a turbine.

Claims

1. A gas turbine comprising:

a compressor which compresses air;

a combustor which mixes compressed air compressed by the compressor and fuel and combusts the fuel;

a turbine which produces rotary power from combustion gas generated by the combustor; and

a rotating shaft which is driven by the air to rotate around a rotation axis, wherein

the compressor includes;

a casing which forms an air path having a ring shape around the rotation axis;

a plurality of blade bodies which are fixed on the outer circumference of the rotating shaft at predetermined intervals in the axial direction and disposed in the air path;

a plurality of vane bodies which are fixed on the casing between the plurality of blade bodies and disposed in the air path;

a blade ring which is provided so as to face the radially outer side of the plurality of blade bodies and on the inside of which a cooling air flow passage is formed;

a first cooling air supply channel which supplies a part of the compressed air compressed by the compressor to the cooling air flow passage; and

a second cooling air supply channel which supplies the cooling air from the cooling air flow passage to a part to be cooled of the turbine; and

a plurality of isolation rings which are supported by the blade ring through a support part, which is protruding toward the radially inner side, of the blade ring, forms a ring shape around the rotation axis and supports the vane bodies through a collar protruding toward the axial direction at the radially inner terminal.

2. The gas turbine according to claim 1, wherein

the collar supports the vane body through an outer shroud of the vane body.

3. The gas turbine according to claim 1, wherein the cooling air flow passage has a plurality of manifolds which are disposed at predetermined intervals in an air flow direction in the air path, and coupling paths which couple the plurality of manifolds in series.

4. The gas turbine according to claim 3, wherein

the plurality of manifolds have a first manifold to which the first cooling air supply channel is coupled, a second manifold disposed on the upstream side in the air flow direction in the air path, and a third manifold which is disposed on the downstream side in the air flow direction in the air path and to which the second cooling air supply channel is coupled, and

the coupling paths have a first coupling path which couples the first manifold and the second manifold with each other, and a second coupling path which couples the second manifold and the third manifold with each other.

5. The gas turbine according to claim 1, wherein the casing has the blade ring which has a cylindrical shape, forms the air path, and supports the outer circumference of the plurality of vane bodies, and the cooling air flow passage is formed as a cavity inside the blade ring.

6. The gas turbine according to claim 2, wherein the isolation ring is divided into a plurality of parts in the circumferential direction with a certain clearance provided therebetween.

7. The gas turbine according to claim 2, wherein the isolation ring forms a ring shape around the rotation axis, and is fixed on the inner circumference of the blade ring further on the downstream side in a flow direction of the compressed air in the air path than the plurality of blade bodies and the plurality of vane bodies.