# US 10,865,991 B2 · Combustion apparatus and gas turbine including the same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,865,991 B2 - Document ID: US10865991B2 - Status: Granted - Kind: B2 - Application number: 16/025,966 - Filed: 2018-07-02 - Published: 2019-01-17 - Granted: 2020-12-15 - Earliest claimed: 2017-07-14 - Assignees: Doosan Heavy Industries Construction Co., Ltd - Applicants: Doosan Heavy Industries & Construction Co., Ltd. - Inventors: Sung Hyun Kim; Ho Keun Kim; Chea Hong Choi - Web page: https://patentgrep.com/patent/US10865991B2 ## CPC - F23R 3/343: {Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00)} - F02C 7/222: {Fuel flow conduits, e.g. manifolds} - F02C 7/228: Dividing fuel between various burners - F02C 7/232: Fuel valves {(control of fuel supply by means of fuel metering valves F02C9/263)}; Draining valves or systems (valves in general F16K) - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23R 3/46: Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings - F05D 2270/14: to control thermoacoustic behaviour in the combustion chambers - F23R 2900/00013: Reducing thermo-acoustic vibrations by active means - 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) - 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 A combustion apparatus can avoid instability in combustion by controlling a pressure ratio of fuel mixed with air. The combustion apparatus includes a casing; a pilot nozzle disposed at the center of the casing and supplied with fuel by a pilot fuel supply pipe; and a plurality of main nozzles arranged around the pilot nozzle and supplied with fuel by a main fuel supply pipe, each main nozzle including a pair of parallel fuel channels each extending to a respective fuel spray position within the main nozzle. A gas turbine adopting the combustion apparatus includes a plurality of combustors, each combustor including the casing, pilot nozzle, and plurality of main nozzles, with each main nozzle having first and second fuel channels respectively extending to a fuel spray position of the corresponding fuel channel. A pilot manifold connects the respective pilot nozzles, and a main manifold connects the respective main nozzles. ## Claims ### Claim 1 A combustion apparatus comprising: a casing; a pilot nozzle disposed at the center of the casing and supplied with fuel by a pilot fuel supply pipe; and a plurality of main nozzles arranged around the pilot nozzle and supplied with fuel by a main fuel supply pipe, each main nozzle including a pair of parallel fuel channels, the pair of parallel fuel channels including a first fuel channel extending to a first fuel spray position of a corresponding main nozzle of the plurality of main nozzles and a second fuel channel extending to a second fuel spray position of the corresponding main nozzle, wherein the main fuel supply pipe includes a pair of fuel supply pipes for respectively supplying fuel to either channel of the pair of parallel fuel channels. ### Claim 2 (depends on 1) The combustion apparatus of claim 1, further comprising: a pilot fuel flow rate control valve for controlling a flow rate of the fuel supplied through the pilot fuel supply pipe; and a main fuel flow rate control valve for controlling a flow rate of the fuel supplied through the main fuel supply pipe. ### Claim 3 (depends on 2) The combustion apparatus of claim 2, wherein the main fuel supply pipe further includes a main pipe in which the main fuel flow rate control valve is installed, and wherein the pair of fuel supply pipes are branched from the main pipe. ### Claim 4 (depends on 3) The combustion apparatus of claim 3, further comprising a three-way valve installed in the main pipe to control a flow rate of fuel distributed to either channel of the pair of parallel fuel channels. ### Claim 5 (depends on 3) The combustion apparatus of claim 3, wherein the pair of fuel supply pipes include: a first fuel supply pipe branched from the main pipe and connected to a first main manifold for supplying fuel to one channel of the pair of parallel fuel channels; and a second fuel supply pipe branched from the main pipe and connected to a second main manifold for supplying fuel to the other channel of the pair of parallel fuel channels. ### Claim 6 (depends on 5) The combustion apparatus of claim 5, further comprising: a first two-way valve installed in the first fuel supply pipe to control a flow rate of fuel distributed to one channel of the pair of parallel fuel channels; and a second two-way valve installed in the second fuel supply pipe to control a flow rate of fuel distributed to the other channel of the pair of parallel fuel channels. ### Claim 7 (depends on 3) The combustion apparatus of claim 3, further comprising: a first connection pipe for daisy-chaining one channel of the pair of parallel fuel channels of each main nozzle, which channels are respectively adjacent to one another; and a second connection pipe for daisy-chaining the other channel of the pair of parallel fuel channels of each main nozzle, which channels are respectively adjacent to one another, wherein the pair of fuel supply pipes includes first and second fuel supply pipes respectively branched from the main pipe, the first fuel supply pipe being connected to only one of the channels daisy-chained by the first connection pipe, the second fuel supply pipe being connected to only one of the channels daisy-chained by the second connection pipe. ### Claim 8 (depends on 1) The combustion apparatus of claim 1, further comprising a controller for controlling a flow rate of fuel distributed to either channel of the pair of parallel fuel channels. ### Claim 9 (depends on 8) The combustion apparatus of claim 8, wherein the flow rate of the distributed fuel is controlled according to a pressure ratio of the fuel mixed with air. ### Claim 10 (depends on 9) The combustion apparatus of claim 9, wherein the fuel of the main fuel supply pipe is delivered entirely to only one channel of the pair of parallel fuel channels when a pressure of the fuel is lower than or equal to a pressure of the air, and the fuel of the main fuel supply pipe is divided and distributed to either channel of the pair of parallel fuel channels respectively when the pressure of the fuel is higher than the pressure of the air. ### Claim 11 (depends on 9) The combustion apparatus of claim 9, wherein, when a pressure of the fuel is higher than a pressure of the air, the fuel of the main fuel supply pipe is distributed to either channel of the parallel fuel channels and is otherwise delivered entirely to only one channel of the parallel fuel channels. ### Claim 12 (depends on 8) The combustion apparatus of claim 8, wherein, when combustion instability occurs, the fuel of the main fuel supply pipe is distributed to either channel of the parallel fuel channels and is otherwise delivered entirely to only one channel of the parallel fuel channels. ### Claim 13 (depends on 1) The combustion apparatus of claim 1, wherein the respective fuel spray positions of the pair of parallel fuel channels each occur where the fuel is sprayed into a mixing zone for pre-mixing air and fuel. ### Claim 14 (depends on 1) The combustion apparatus of claim 1, wherein the fuel spray position of one of the pair of parallel fuel channels occurs where the fuel is sprayed into a mixing zone for pre-mixing air and fuel, and the fuel spray position of the other of the pair of parallel fuel channels occurs where the fuel is sprayed to a zone in which the air and the fuel meet and a diffusion flame occurs. ### Claim 15 (depends on 1) The combustion apparatus of claim 1, wherein the the first fuel channel extends lengthwise along one side of the corresponding main nozzle, and wherein the second fuel channel extends lengthwise along a side opposite to the one side of the corresponding main nozzle, in parallel to the first fuel channel. ### Claim 16 A gas turbine comprising: a compressor for sucking air and compressing the sucked air to a high pressure; a plurality of combustors for mixing the compressed air with fuel and combusting the mixture, each combustor comprising: a casing, a pilot nozzle disposed at the center of the casing, and a plurality of main nozzles arranged around the pilot nozzle, each main nozzle including a first fuel channel extending to a fuel spray position of the first fuel channel and a second fuel channel extending to a fuel spray position of the second fuel channel; a turbine for generating electric power by rotating a turbine blade using high temperature and high pressure combustion gas discharged from the combustors; a pilot manifold connected to the respective pilot nozzles of the plurality of combustors and supplied with fuel by a pilot fuel supply pipe; and a main manifold connected to the respective main nozzles of the plurality of combustors and supplied with fuel by a main fuel supply pipe, wherein the main fuel supply pipe of the main manifold includes: a first fuel supply pipe supplying the fuel to a first main manifold connected to each of the first fuel channels; and a second fuel supply pipe supplying the fuel to a second main manifold connected to each of the second fuel channels. ### Claim 17 (depends on 16) The gas turbine of claim 16, further comprising: a pilot fuel flow rate control valve for controlling a flow rate of the fuel supplied through the pilot fuel supply pipe; and a main fuel flow rate control valve for controlling a flow rate of the fuel supplied through the main fuel supply pipe. ### Claim 18 (depends on 17) The gas turbine of claim 17, wherein the main fuel supply pipe of the main manifold further includes a main pipe in which the fuel flow rate control valve is installed, and wherein the first fuel supply pipe and the second fuel supply pipe are branched from the main pipe. ### Claim 19 (depends on 18) The gas turbine of claim 18, further comprising a three-way valve installed at a point at which the first fuel supply pipe and the second fuel supply pipe are branched from the main pipe to control the flow rate of the fuel distributed to the first fuel supply pipe and the second fuel supply pipe. ### Claim 20 (depends on 18) The gas turbine of claim 18, wherein a plurality of first main branch pipes extend to connect the first fuel channels of the respective combustors from the first main manifold, one first main branch pipe is connected to connect one first fuel channel per each combustor, and the respective first fuel channels of the respective combustors are all connected to each other by a first connection pipe connecting the first fuel channels which are adjacent to each other, and a plurality of second main branch pipes extend to connect the second fuel channels of the respective combustors from the second main manifold, one second main branch pipe is connected to connect one second fuel channel per each combustor, and the respective second fuel channels of the respective combustors are all connected to each other by a second connection pipe connecting the second fuel channels which are adjacent to each other.