# US 2018/0320898 A1 · Combustor, gas turbine including the same and method of distributing compressed air in combustor > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2018/0320898 A1 - Document ID: US20180320898A1 - Status: Published application - Kind: A1 - Application number: 15/947,707 - Filed: 2018-04-06 - Published: 2018-11-08 - Earliest claimed: 2017-05-08 - Assignees: Doosan Heavy Industries Construction Co., Ltd - Applicants: Doosan Heavy Industries & Construction Co., LTD - Inventors: Jongho Uhm - Web page: https://patentgrep.com/patent/US20180320898A1 ## CPC - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings} - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F05D 2260/201: by impingement of a fluid - F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - 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 Disclosed herein is a combustor capable of improving impingement cooling performance by reducing the influence of a cross-flow on a jet flow. The combustor includes a combustion liner, in which fuel sprayed from fuel nozzles of a gas turbine is mixed with compressed air and the mixture is combusted, a sleeve surrounding the outer surface of the combustion liner while being spaced apart therefrom in order to form a flow passage for compressed air, a cooling hole formed in the sleeve to introduce compressed air discharged from a compressor into the flow passage, and a first auxiliary hole formed upstream of the cooling hole in the airflow direction. Compressed air discharged from the compressor is introduced into the flow passage through the first auxiliary hole, impinges with compressed air flowing through the flow passage, and forms an air column. ## Claims ### Claim 1 A combustor comprising: a combustion liner constituting a combustion chamber and disposed on an upstream side in a combustion gas flow direction; a transition piece constituting the combustion chamber and disposed on a downstream side in the combustion gas flow direction; a sleeve surrounding the combustion liner and the transition piece while being spaced apart therefrom a flow passage formed between the combustion liner and the sleeve and between the transition piece and the sleeve; a cooling hole formed in the sleeve to introduce compressed air discharged from a compressor into the flow passage; and a first auxiliary hole formed upstream of the cooling hole in an airflow direction, wherein compressed air discharged from the compressor is introduced into the flow passage through the first auxiliary hole, impinges with compressed air flowing through the flow passage, and forms an air column. ### Claim 2 (depends on 1) The combustor according to claim 1, wherein, when the cooling hole has a diameter of a value of D, the first auxiliary hole is formed to have a diameter of a value of 0.5 D or less. ### Claim 3 (depends on 1) The combustor according to claim 1, wherein the cooling hole and the first auxiliary hole are spaced apart from each other such that a straight-line distance therebetween has a value that is equal to or less than a diameter (D) of the cooling hole. ### Claim 4 (depends on 1) The combustor according to claim 1, further comprising: a second auxiliary hole formed downstream of the cooling hole in the airflow direction, wherein compressed air discharged from the compressor is introduced into the flow passage through the second auxiliary hole, mitigates turbulence generated downstream of the cooling hole, and maintains momentum of compressed air introduced through the cooling hole. ### Claim 5 (depends on 4) The combustor according to claim 4, wherein, when the cooling hole has a diameter of a value of D, the second auxiliary hole is formed to have a diameter of a value of 0.5 D or less. ### Claim 6 (depends on 4) The combustor according to claim 4, wherein the cooling hole and the second auxiliary hole are spaced apart from each other such that a straight-line distance therebetween has a value that is equal to or less than a diameter (D) of the cooling hole. ### Claim 7 (depends on 1) The combustor according to claim 1, wherein the first auxiliary hole is formed such that at least a portion thereof overlaps the cooling hole. ### Claim 8 (depends on 4) The combustor according to claim 4, wherein at least one of the first auxiliary hole or the second auxiliary hole is formed such that at least a portion thereof overlaps the cooling hole. ### Claim 9 A combustor comprising: a combustion liner constituting a combustion chamber and disposed on an upstream side in a combustion gas flow direction; a transition piece constituting the combustion chamber and disposed on a downstream side in the combustion gas flow direction; a sleeve surrounding the combustion liner and the transition piece while being spaced apart therefrom; a flow passage formed between the combustion liner and the sleeve and between the transition piece and the sleeve; a cooling hole formed in the sleeve to introduce compressed air discharged from a compressor into the flow passage; and a second auxiliary hole formed downstream of the cooling hole in an airflow direction, wherein compressed air discharged from the compressor is introduced into the flow passage through the second auxiliary hole, mitigates turbulence generated downstream oh the cooling hole, and maintains momentum of compressed air introduced through the cooling hole. ### Claim 10 The combustor according to claim wherein, when the cooling hole has a diameter of a value of D, the second auxiliary hole is formed to have a diameter of a value of 0.5 D or less. ### Claim 11 (depends on 9) The combustor according to claim 9, wherein the cooling hole and the second auxiliary hole are spaced apart from each other such that a straight-line distance therebetween has a value that is equal to or less than a diameter (D) of the cooling hole. ### Claim 12 (depends on 9) The combustor according to claim 9, wherein the second auxiliary hole is formed such that at least a portion thereof overlaps the cooling hole. ### Claim 13 A gas turbine comprising: a compressor configured to compress air; a combustor configured to receive compressed air from the compressor, to form a mixture by mixing the compressed air with fuel, and to combust the mixture; and a turbine configured to be rotated by combustion gas discharged from the combustor to produce power, wherein the combustor comprises: a combustion liner constituting a combustion chamber and disposed on an upstream side in a combustion gas flow direction; a transition piece constituting the combustion chamber and disposed on a downstream side in the combustion gas flow direction; a sleeve surrounding the combustion liner and the transition piece while being spaced apart therefrom; a flow passage formed between the combustion liner and the sleeve and between the transition piece and the sleeve; a cooling hole formed, in the sleeve to introduce compressed air discharged from the compressor into the flow passage; and a first auxiliary hole formed upstream of the cooling hole in an airflow direction, and wherein, compressed air discharged, from the compressor is introduced into the flow passage through the first auxiliary hole, impinges with compressed air flowing through the flow passage, and forms an air column. ### Claim 14 (depends on 13) The gas turbine according to claim 13, wherein, when the cooling hole has a diameter of a value of D, the first auxiliary hole is formed to have a diameter of a value of 0.5 D or less, and wherein the cooling hole and the first auxiliary hole are spaced apart from each other such that a straight-line distance therebetween has a value that is equal to or less than the diameter (D) of the cooling hole. ### Claim 15 (depends on 13) The gas turbine according to claim 13, wherein the combustor further comprises a second auxiliary hole formed downstream of the cooling hole in the airflow direction, and wherein compressed air discharged from the compressor is introduced into the flow passage through the second auxiliary hole, mitigates turbulence generated downstream of the cooling hole, and maintains momentum of compressed air introduced through the cooling hole. ### Claim 16 (depends on 15) The gas turbine according to claim 15, wherein, when the cooling hole has a diameter of a value of D, the second auxiliary hole is formed to have a diameter of a value of 0.5 D or less, and wherein the cooling hole and the second auxiliary hole are spaced apart from each other such that a straight-line distance therebetween has a value that is equal to or less than the diameter (D) of the cooling hole. ### Claim 17 (depends on 15) The gas turbine according to claim 15, wherein at least one of the first auxiliary hole or the second auxiliary hole is formed such that at least a portion thereof overlaps the cooling hole. ### Claim 18 A method of distributing compressed air in a combustor configured to receive compressed air from a compressor, to form a mixture by mixing the compressed air with fuel, and to combust the mixture, the method comprising: forming a cross-flow by allowing compressed air to be introduced into a flow passage, formed between a combustion liner and a sleeve and between a transition piece and the sleeve, through a cooling hole and to flow through the flow passage; and forming an air column by allowing compressed air introduced into the flow passage through a first auxiliary hole, formed upstream of the cooling hole in an airflow direction, to impinge with the cross-flow. ### Claim 19 (depends on 18) The method according to claim 18, further comprising: mitigating turbulence generated downstream of the cooling hole in the airflow direction and maintaining momentum of compressed air introduced through the cooling hole by allowing compressed air to be introduced into the flow passage through a second auxiliary hole formed downstream of the cooling hole in the airflow direction. ### Claim 20 A method of distributing compressed air in a combustor configured to receive compressed air from a compressor, to form a mixture by mixing the compressed air with fuel, and to combust the mixture, the method comprising: forming a cross-flow by allowing compressed air to be introduced into a flow passage, formed between a combustion liner and a sleeve and between a transition piece and the sleeve, through a cooling hole and to flow through the flow passage; and mitigating turbulence generated downstream of the cooling hole in an airflow direction and maintaining momentum of compressed air introduced through the cooling hole by allowing compressed air to be introduced into the flow passage through a second auxiliary hole formed downstream of the cooling hole in the airflow direction.