# US 2016/0251981 A1 · Gas turbine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2016/0251981 A1 - Document ID: US20160251981A1 - Status: Published application - Kind: A1 - Application number: 15/028,564 - Filed: 2014-09-08 - Published: 2016-09-01 - Earliest claimed: 2013-10-15 - Assignees: Mitsubishi Hitachi Power Systems, Ltd. - Applicants: Mitsubishi Hitachi Power Systems, Ltd. - Inventors: Shinya HASHIMOTO - Web page: https://patentgrep.com/patent/US20160251981A1 ## CPC - F01D 25/12: Cooling - F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 11/24: by selectively cooling-heating stator or rotor components - F01D 25/10: Heating, e.g. warming-up before starting - F01D 25/14: Casings modified therefor (double casings F01D25/26) - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F01D 25/246: {Fastening of diaphragms or stator-rings} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F02C 7/24: Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F05D 2220/32: in gas turbines - F05D 2240/15: Heat shield - F05D 2240/35: Combustors or associated equipment - F05D 2260/213: by the provision of a heat exchanger within the cooling circuit - F05D 2260/231: Preventing heat transfer - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract There is provided a gas turbine including: a blade ring which is coupled on the inner circumference of a turbine casing so as to define an annular first cavity; a plurality of heat shield rings coupled on the inner circumference of the blade ring; a plurality of ring segments coupled on the inner circumference of the plurality of heat shield rings; a plurality of blade bodies fixed on the outer circumference of a rotor and disposed so as to radially face the ring segments; a plurality of vane bodies of which an outer shroud is fixed on the heat shield rings between the plurality of blade bodies so as to define an annular second cavity; a second cooling air supply channel; a first cooling air supply channel; and a cooling air discharge channel which discharges the cooling air from the first cavity. ## Claims ### Claim 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 combustion gas to rotate around a rotation axis, wherein the turbine includes: a turbine casing forming a ring shape around the rotation axis; a blade ring which forms a ring shape around the rotation axis and is supported on the inner circumference of the turbine casing so as to define a ring-shaped first cavity; a plurality of heat shield rings which form a ring shape around the rotation axis and are supported on the inner circumference of the blade ring at predetermined intervals in the axial direction; a plurality of ring segments which form a ring shape around the rotation axis and are supported on the inner circumference of the plurality of heat shield rings; 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 so as to radially face the ring segments; a plurality of vane bodies of which a shroud forming a ring shape around the rotation axis between the plurality of blade bodies is fixed on the adjacent heat shield rings so as to define a ring-shaped second cavity; a second cooling air supply channel which supplies a part of the compressed air compressed by the compressor to the second cavity; a first cooling air supply channel which supplies cooling air having a lower temperature than the compressed air compressed by the compressor to the first cavity; and a cooling air discharge channel which discharges the cooling air from the first cavity. ### Claim 2 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 combustion gas to rotate around a rotation axis, wherein the turbine includes: a turbine casing forming a ring shape around the rotation axis; a blade ring which forms a ring shape around the rotation axis and is coupled on the inner circumference of the turbine casing so as to define an annular first cavity; a plurality of heat shield rings which form a ring shape around the rotation axis and are coupled on the inner circumference of the blade ring at predetermined intervals in the axial direction; a plurality of ring segments which form a ring shape around the rotation axis and are coupled on the inner circumference of the plurality of heat shield rings; 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 so as to radially face the ring segments; a plurality of vane bodies of which a shroud forming a ring shape around the rotation axis between the plurality of blade bodies is fixed on the adjacent heat shield rings so as to define an annular second cavity; a second cooling air supply channel which supplies a part of the compressed air compressed by the compressor to the second cavity; a cooling air flow passage which is provided inside the blade ring and of which one end communicates with the first cavity; a first cooling air supply channel which supplies cooling air having a lower temperature than the compressed air compressed by the compressor to one of the other end of the cooling air flow passage and the first cavity; and a cooling air discharge channel which discharges the cooling air from the other one of the other end of the cooling air flow passage and the first cavity. ### Claim 3 (depends on 1) The gas turbine according to claim 1, wherein a heat shield member is provided on the inner circumferential surface of the blade ring. ### Claim 4 (depends on 2) The gas turbine according to claim 2, wherein the cooling air flow passage has a plurality of manifolds disposed at predetermined intervals in the axial direction of the rotating shaft, and coupling paths coupling the plurality of manifolds in series. ### Claim 5 (depends on 2) The gas turbine according to claim 2, wherein the blade ring has a cylindrical part extending along the axial direction of the rotating shaft, and a first outer circumferential flange and a second outer circumferential flange provided respectively at both ends of the cylindrical part, the plurality of manifolds are formed as cavities in the first outer circumferential flange and the second outer circumferential flange, and the coupling paths are formed as a plurality of communication holes in the cylindrical part. ### Claim 6 (depends on 1) The gas turbine according to claim 1, wherein the first cooling air supply channel supplies atmospheric air suctioned by means of a blower. ### Claim 7 (depends on 1) The gas turbine according to claim 1, wherein the heat shield ring is composed of a material having a higher thermal expansion rate than the blade ring. ### Claim 8 (depends on 1) The gas turbine according to claim 1, wherein the first cooling air supply channel includes a heating device which heats the cooling air. ### Claim 9 (depends on 1) The gas turbine according to claim 1, wherein the cooling air discharge channel introduces the cooling air discharged from the first cavity into an exhaust cooling system. ### Claim 10 (depends on 2) The gas turbine according to claim 2, wherein a heat shield member is provided on the inner circumferential surface of the blade ring. ### Claim 11 (depends on 2) The gas turbine according to claim 2, wherein the first cooling air supply channel supplies atmospheric air suctioned by means of a blower. ### Claim 12 (depends on 2) The gas turbine according to claim 2, wherein the heat shield ring is composed of a material having a higher thermal expansion rate than the blade ring. ### Claim 13 (depends on 2) The gas turbine according to claim 2, wherein the first cooling air supply channel includes a heating device which heats the cooling air. ### Claim 14 (depends on 2) The gas turbine according to claim 2, wherein the cooling air discharge channel introduces the cooling air discharged from the first cavity into an exhaust cooling system.