CN117605579A - Combustion control method for gas turbine generator set - Google Patents
Combustion control method for gas turbine generator set Download PDFInfo
- Publication number
- CN117605579A CN117605579A CN202311632576.5A CN202311632576A CN117605579A CN 117605579 A CN117605579 A CN 117605579A CN 202311632576 A CN202311632576 A CN 202311632576A CN 117605579 A CN117605579 A CN 117605579A
- Authority
- CN
- China
- Prior art keywords
- gas
- combustion
- fuel
- valve
- natural gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 148
- 238000000034 method Methods 0.000 title claims abstract description 29
- 239000007789 gas Substances 0.000 claims description 226
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 172
- 239000003345 natural gas Substances 0.000 claims description 86
- 239000000446 fuel Substances 0.000 claims description 74
- 230000015572 biosynthetic process Effects 0.000 claims description 43
- 238000003786 synthesis reaction Methods 0.000 claims description 43
- 239000002918 waste heat Substances 0.000 claims description 12
- 239000002737 fuel gas Substances 0.000 claims description 10
- 230000008859 change Effects 0.000 claims description 9
- 239000003245 coal Substances 0.000 claims description 9
- 238000011217 control strategy Methods 0.000 claims description 9
- 238000009792 diffusion process Methods 0.000 claims description 9
- 238000011045 prefiltration Methods 0.000 claims description 9
- 230000008569 process Effects 0.000 claims description 7
- 230000000740 bleeding effect Effects 0.000 claims description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 4
- 230000001133 acceleration Effects 0.000 claims description 3
- 230000009471 action Effects 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims description 3
- 239000000295 fuel oil Substances 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 230000010355 oscillation Effects 0.000 claims description 3
- 230000001737 promoting effect Effects 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 230000005611 electricity Effects 0.000 description 5
- 239000000571 coke Substances 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000010795 Steam Flooding Methods 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
- F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
- F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention belongs to the technical field of generator sets, and particularly relates to a combustion control method of a gas turbine generator set.
Description
Technical Field
The invention relates to the technical field of generator sets, in particular to a combustion control method of a gas turbine generator set.
Background
The gas-steam combined cycle generator set becomes a power device with great development potential by virtue of the advantages of high efficiency, environmental protection, low water consumption and the like. Gas turbine generator sets using rich gas as raw fuel are increasingly used in metallurgical enterprises in recent years. Realizing the high-efficiency comprehensive utilization of byproducts in the metallurgical industry.
Because the gas turbine has more severe requirements on the stability of the heating value of the raw fuel, a certain amount of coke oven gas must be equipped to meet the requirements. For example, the GE company PG9171E type gas engine and the Mitsubishi M701DSA type gas engine in Japan each require gas heating value control at 1050kcal/Nm3. The gas turbine generator sets in the prior art rely excessively on coke oven gas.
However, the production and supply of coke oven gas are related to and interact with the main product process of steel production, and its volatility inevitably affects the downstream gas turbine generator sets. When the coke oven gas is insufficient, the blast furnace gas can be supplemented, and even the blast furnace gas is completely burned. However, the high-efficiency and long-period operation of the unit is restricted, and the unit becomes a technical bottleneck for further popularization and application of the combined cycle power generation technology of the metallurgical production enterprises.
Disclosure of Invention
The invention provides a combustion control method of a gas turbine generator set.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the method for controlling the combustion of the generator set of the gas turbine comprises a first generator set and a second generator set, wherein the first generator set is driven by the gas turbine, the gas outlet end of the gas turbine is connected with the waste heat boiler, the second generator set is driven by the steam turbine, high-pressure steam generated by the waste heat boiler enters the steam turbine, liquid water generated by the steam turbine returns to the waste heat boiler, the fuel inlet of the gas turbine is connected with the fuel control system, and the control method of the fuel control system comprises the following steps:
step 1, a control strategy before and after fuel switching: at the initial stage of switching, firstly checking and confirming whether various indexes of an outlet of a coal press reach set values or not, wherein the unit load is 40% -50% of a load interval of fuel switching; when the natural gas flow control valve is gradually closed to 10% of the maximum nonlinear valve position in the switching end stage, the natural gas flow control valve is rapidly closed at the maximum closing rate; simultaneously closing a synthetic gas to a torch bleeding valve to enable the synthetic gas to fully enter a gas turbine for combustion;
step 2, a dual-fuel switching control strategy: when the two fuels meet the switching conditions, the natural gas flow ratio is reduced from 100% to 0% according to the set rate, and the synthetic gas ratio is increased from 0% to 100% according to the set rate; the synthesis gas to flare bleed valve is gradually closed according to the rate of 5%/s, and the pressure of the coal press outlet is maintained at 18bar through the recirculation regulating valve; in the switching process, the closed-loop control of the performance of the combustion chamber and the closed-loop control of the combustion stability are carried out.
Further, the closed loop control of the combustion chamber performance includes: load controller, exhaust temperature controller and compressor pressure limit.
Further, the combustion stability closed-loop control comprises the steps of judging whether the combustion of the gas turbine is stable or not, and realizing the combustion stability by measuring the dynamic pressure change condition in the combustion chamber and the oscillation dynamic amplitude change generated by combustion; the combustion stability closed-loop control is to dynamically adjust the combustion state in real time according to a preset adjustment curve by taking Weng Ming and ACC as performance indexes; when the combustion is unstable, the unstable combustion condition is reflected in real time through Weng Ming and acceleration, and the exhaust temperature set value of the combustion engine, the change of the IGV opening and the real-time correction of the natural gas flow are automatically adjusted before the combustion is deteriorated, so that all parameters of a unit are ensured to be adjusted to an optimal state in the fuel switching process.
Further, the dual fuel switching control strategy includes a natural gas fuel system and a syngas fuel system.
Further, the natural gas fuel system uses natural gas fuel as ignition fuel of the gas turbine, controls the natural gas mass flow entering the combustion chamber of the gas turbine, and prevents natural gas from entering the gas turbine under specific conditions; the system consists of a pre-filter module, a natural gas emergency shut-off valve, a natural gas diffusing valve, a natural gas control valve and a natural gas ball valve; the pre-filter is used for preventing any coarse foreign matters in a pipeline between the upstream fine filter unit and the filter from entering the natural gas emergency shut-off valve; the natural gas emergency shut-off valve is a valve that supplies or shuts off natural gas to the combustor at startup and shutdown of the gas turbine, as well as during startup or shutdown of the natural gas system; after the natural gas emergency shut-off valve, the gas supply line splits into two branches: one path is led to the synthesis gas system, and the other path directly enters the combustion chamber through the diffusion burner; the relief valve is arranged between the natural gas emergency shutoff valve and the natural gas control valve and is used for discharging natural gas in a pipe section between the shutoff valves into the air; the natural gas control valve controls the natural gas flow to the diffusion combustor according to the requirements of the gas turbine control system, and each pipeline leading to the combustion chamber is provided with a natural gas ball valve for supplying or cutting off the natural gas flow to the combustor.
Further, when the syngas fuel system controls the syngas mass flow into the combustion chamber of the gas turbine, and shuts off the supply of syngas to the gas turbine under conditions of gas turbine protection action or emergency shutdown; one path of the synthesis gas from the outlet of the coal press is led to the diffusion torch for adjusting the heat value of the synthesis gas, the other path of the synthesis gas is led to the burner, the two branch lines of the combustion chamber A and the combustion chamber B are connected after passing through the outlet of the filter, and a synthesis gas shutoff valve group is arranged on the branch line of the burner, and the synthesis gas shutoff valve group comprises: the device comprises a synthesis gas emergency shut-off valve, a synthesis gas bleeding valve and a synthesis gas control valve.
Further, the burner has three different fuel gas nozzle piping systems, including: a diffuser line, a synthesis gas line, and an on duty gas line; the diffuser pipeline is used for starting through the minimum fuel quantity, accelerating to the rated rotating speed and running at partial load until load switching; the on-duty gas pipeline is a fuel oil pipeline and is used for promoting the operation of the burner; the synthesis gas pipeline is used for converting the synthesis gas from load to be combusted to basic load; after passing through the synthetic gas cyclone, the synthetic gas flows into a combustion chamber, is mixed with combustion air in the combustion chamber and combusted, and the air is supplied to the combustor through a combustion air inlet through the inclined cyclone and the central axial cyclone; a small amount of combustion air enters the internal air passage and enters the combustion chamber through the central axial swirler; a smaller portion of the combustion air is used to cool the center nozzle, with the remainder of the combustion air flowing through the hydrocyclone.
Further, the gas turbine adopts dual-fuel switching when a dual-fuel gas turbine control system is operated, natural gas is used as fuel from ignition, speed rising, constant speed and grid connection to 40% -50% of fuel switching load points, the natural gas is pressurized to a preset pressure by a supercharger and then enters a combustion chamber through a pre-filter by a natural gas control valve through a natural gas fuel passage; at this stage, both the syngas fuel passage and other valves are closed; and after the unit load reaches a certain initial load, the fuel is quickly switched.
Further, the gas turbine comprises a machine body, an output shaft is arranged in the machine body, a gas compressing section, a combustion section and an exhaust section are sequentially arranged on the machine body, the gas compressing section comprises a gas compressor front cylinder and a gas compressor rear cylinder, the gas compressor front cylinder is connected with the gas compressor rear cylinder end to end, the gas compressor front cylinder is provided with a gas inlet volute and a gas inlet cylinder, a plurality of gas compressor working blades and gas compressor stator blades are arranged in the gas compressor front cylinder and the gas compressor rear cylinder respectively, the gas compressor working blades and the gas compressor stator blades are alternately arranged, the output shaft drives the gas compressor working blades and the gas compressor stator blades to rotate, the tail end of the gas compressor rear cylinder is fixedly provided with the combustion section, the combustion section comprises a combustion chamber outer wall, a plurality of combustion chambers are arranged in the combustion chamber outer wall, and the gas inlet ends of the combustion chambers face the gas compressing section, the gas turbine engine is characterized in that a gas nozzle is arranged at a gas inlet at the front part of the combustion chamber, a gas inlet gap is formed between the gas nozzle and the gas inlet at the front part of the combustion chamber, an igniter is arranged in each combustion chamber, the rear end of the outer wall of the combustion chamber is connected with an exhaust section, a first rotating part is arranged at the joint of the outer wall of the combustion chamber and the exhaust section, the first rotating part is fixedly connected with an output shaft, a plurality of low-pressure turbine stator blades and low-pressure turbine rotor blades are arranged on the rotating part, the low-pressure turbine stator blades and the low-pressure turbine rotor blades are arranged in the exhaust section in a staggered mode, the low-pressure turbine stator blades and the low-pressure turbine rotor blades can freely rotate in a matrix, and an exhaust cylinder is arranged on the exhaust section.
Further, the first rotating part is connected with the machine body through a high-pressure turbine roller bearing.
Further, the low-pressure turbine stator blade is fixed on a second rotating part, and the second rotating part is connected with the machine body through a low-pressure turbine ball bearing.
Further, the low-pressure turbine rotor blade is fixedly connected with a rotating part III, and the rotating part III is fixed on the rotating shaft.
The beneficial points are that: the compressor of the present invention continuously sucks air from the atmosphere through the intake cylinder and compresses it; the compressed air enters a combustion chamber, is mixed with fuel injected by a fuel gas nozzle and then combusted to become high-temperature fuel gas, and then enters a turbine of a combustion engine to expand and do work, so that an output shaft is pushed to carry a generator set to do work for generating electricity. When the gas turbine is started in a static state, the generator is required to be converted into the motor to drive the gas turbine to rotate, and after the gas turbine is accelerated to a certain rotating speed, the starting device is tripped, so that work can be performed in a generator mode to generate electricity. And the exhaust gas of the gas turbine is introduced into a waste heat boiler, and the generated high-temperature and high-pressure steam drives a steam turbine to drive a generator set II to generate electricity. The common mode is that a gas turbine and a steam turbine coaxially push a single-shaft combined cycle of a generator, and the gas turbine and the steam turbine respectively and multi-shaft combined cycle of a generator set.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view of a gas turbine engine according to the present invention.
In the figure: a first generator set, a gas turbine, a 3 waste heat boiler, a 4 steam turbine and a 5 generator set;
201 thrust bearing, 202 sliding bearing, 203 air intake volute, 204 air intake cylinder, 205 compressor working vane, 206 rotatable vane, 207 compressor stator vane, 208 compressor front cylinder, 209 bleed valve, 210 compressor rear cylinder, 211 bolt one, 212 nut one, 213 spring washer, 214 air permeable flat cylinder, 215 bolt two, 216 nut two, 217 spring washer two, 218 gas nozzle, 219 igniter, 220 combustion chamber outer wall, 221 combustion chamber, 222 high pressure turbine stator vane, 223 high pressure turbine working vane, 224 high pressure turbine roller bearing, 225 low pressure turbine stator vane, 226 low pressure turbine working vane, 227 bearing member, 228 exhaust cylinder, 229 low pressure turbine ball bearing, 230 coupling, 231 aft support, 232 fore support, 233 compressor support.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
In the description of the present invention, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Referring to fig. 1-2, a method for controlling the combustion of a generator set of a gas turbine 2 includes a first generator set 1 and a second generator set 5, the first generator set 1 is driven by the gas turbine 2, an air outlet end of the gas turbine 2 is connected with a waste heat boiler 3, the second generator set 5 is driven by a steam turbine 4, high pressure steam generated by the waste heat boiler 3 enters the steam turbine 4, liquid water generated by the steam turbine 4 returns to the waste heat boiler 3, a fuel inlet of the gas turbine 2 is connected with a fuel control system, and a control method of the fuel control system includes the following steps:
step 1, a control strategy before and after fuel switching: at the initial stage of switching, firstly checking and confirming whether various indexes of an outlet of a coal press reach set values or not, wherein the unit load is 40% -50% of a load interval of fuel switching; when the natural gas flow control valve is gradually closed to 10% of the maximum nonlinear valve position in the switching end stage, the natural gas flow control valve is rapidly closed at the maximum closing rate; simultaneously closing a synthetic gas to a torch bleeding valve to enable the synthetic gas to fully enter the gas turbine 2 for combustion;
step 2, a dual-fuel switching control strategy: when the two fuels meet the switching conditions, the natural gas flow ratio is reduced from 100% to 0% according to the set rate, and the synthetic gas ratio is increased from 0% to 100% according to the set rate; the synthesis gas to flare bleed valve is gradually closed according to the rate of 5%/s, and the pressure of the coal press outlet is maintained at 18bar through the recirculation regulating valve; during the switching process, the combustion chamber 221 performance closed-loop control and the combustion stability closed-loop control are performed. The combustion chamber 221 performance closed loop control, comprising: load controller, exhaust temperature controller and compressor pressure limit.
The combustion stability closed-loop control includes determining whether the combustion of the gas turbine 2 is stable or not by measuring the dynamic pressure change condition in the combustion chamber 221 and the oscillation dynamic amplitude change generated by the combustion; the combustion stability closed-loop control is to dynamically adjust the combustion state in real time according to a preset adjustment curve by taking Weng Ming and ACC as performance indexes; when the combustion is unstable, the unstable combustion condition is reflected in real time through Weng Ming and acceleration, and the exhaust temperature set value of the combustion engine, the change of the IGV opening and the real-time correction of the natural gas flow are automatically adjusted before the combustion is deteriorated, so that all parameters of a unit are ensured to be adjusted to an optimal state in the fuel switching process. The dual fuel switching control strategy includes a natural gas fuel system and a syngas fuel system. The natural gas fuel system uses natural gas fuel as ignition fuel for the gas turbine 2, controls the natural gas mass flow rate into the combustion chamber 221 of the gas turbine 2, and prevents natural gas from entering the gas turbine 2 under certain conditions; the system consists of a pre-filter module, a natural gas emergency shut-off valve, a natural gas diffusing valve, a natural gas control valve and a natural gas ball valve; the pre-filter is used for preventing any coarse foreign matters in a pipeline between the upstream fine filter unit and the filter from entering the natural gas emergency shut-off valve; the natural gas emergency shut-off valve is a valve that supplies or shuts off natural gas into the combustor at startup and shutdown of the gas turbine 2, as well as during startup or shutdown of the natural gas system; after the natural gas emergency shut-off valve, the gas supply line splits into two branches: one to the syngas system and the other directly to the combustion chamber 221 via a diffusion combustor; the relief valve is arranged between the natural gas emergency shutoff valve and the natural gas control valve and is used for discharging natural gas in a pipe section between the shutoff valves into the air; the natural gas control valve controls the natural gas flow to the diffusion combustor as required by the control system of the gas turbine 2, and each line leading to the combustion chamber 221 is provided with a natural gas ball valve for supplying or shutting off the natural gas flow to the combustor. When the syngas fuel system controls the syngas mass flow into the combustion chamber 221 of the gas turbine 2 and shuts off the supply of syngas to the gas turbine 2 under conditions of gas turbine 2 protection action or emergency shutdown; one path of the synthesis gas from the outlet of the coal press is led to a diffusion torch for adjusting the heat value of the synthesis gas, the other path of the synthesis gas is led to a burner, the two branch lines of the combustion chamber 221A and the combustion chamber 221B are connected after passing through a filter outlet, and a synthesis gas shut-off valve group is arranged on the branch line of the burner, and the synthesis gas shut-off valve group comprises: the device comprises a synthesis gas emergency shut-off valve, a synthesis gas bleeding valve and a synthesis gas control valve. The burner has three different fuel gas nozzle piping systems, including: a diffuser line, a synthesis gas line, and an on duty gas line; the diffuser pipeline is used for starting through the minimum fuel quantity, accelerating to the rated rotating speed and running at partial load until load switching; the on-duty gas pipeline is a fuel oil pipeline and is used for promoting the operation of the burner; the synthesis gas pipeline is used for converting the synthesis gas from load to be combusted to basic load; after passing through the synthesis gas cyclone, the synthesis gas flows into the combustion chamber 221, is mixed with combustion air in the combustion chamber 221 and combusted, and the air is supplied to the combustor through the inclined cyclone and the central axial cyclone through a combustion air inlet; a small amount of combustion air enters the inner air passage through the central axial swirler into the combustion chamber 221; a smaller portion of the combustion air is used to cool the center nozzle, with the remainder of the combustion air flowing through the hydrocyclone. The gas turbine 2 adopts dual-fuel switching during the operation of a dual-fuel gas turbine control system, natural gas is used as fuel from ignition, speed rise, constant speed and grid connection to 40% -50% of fuel switching load points, and after being pressurized to a preset pressure by a supercharger, the natural gas enters a combustion chamber 221 through a natural gas fuel passage by a natural gas control valve through a pre-filter; at this stage, both the syngas fuel passage and other valves are closed; and after the unit load reaches a certain initial load, the fuel is quickly switched. The dual-fuel switching is performed after confirming that the supply parameters of the fuel, including the heat value, the pressure and the temperature meet the requirements; the handover procedure comprises two phases: a synthesis gas fuel adjustment stage and a fuel dynamic switching stage;
the gas turbine 2 comprises a machine body, an output shaft is arranged in the machine body, a gas compressing section, a combustion section and an exhaust section are sequentially arranged on the machine body, the gas compressing section comprises a gas compressor front cylinder 208 and a gas compressor rear cylinder 210, the gas compressor front cylinder 208 is connected with the gas compressor rear cylinder 210 end to end, the gas compressor front cylinder 208 is provided with a gas inlet volute 203 and a gas inlet cylinder 204, a plurality of gas compressor working blades 205 and gas compressor stator blades 207 are arranged in the gas compressor front cylinder 208 and the gas compressor rear cylinder 210, the gas compressor working blades 205 and the gas compressor stator blades 207 are alternately arranged, the output shaft drives the gas compressor working blades 205 and the gas compressor stator blades 207 to rotate, the tail end of the gas compressor rear cylinder 210 is fixedly provided with the combustion section, the combustion section comprises a combustion chamber 221 outer wall 220, a plurality of combustion chambers 221 are arranged in the combustion chamber 221 outer wall 220, the air inlet end of the combustion chamber 221 faces the air compression section, a gas nozzle 218 is arranged at the air inlet at the front part of the combustion chamber 221, an air inlet gap is arranged between the gas nozzle 218 and the air inlet at the front part of the combustion chamber 221, an igniter 219 is arranged in each combustion chamber 221, the rear end of the outer wall 220 of the combustion chamber 221 is connected with the air exhaust section, a first rotating part is arranged at the connecting part of the outer wall 220 of the combustion chamber 221 and the air exhaust section and fixedly connected with the output shaft, a high-pressure turbine stator blade 222 and a high-pressure turbine rotor blade 223 are arranged on the first rotating part, a plurality of low-pressure turbine stator blades 225 and low-pressure turbine rotor blades 226 are arranged in the air exhaust section, the low-pressure turbine stator blades 225 and the low-pressure turbine rotor blades 226 are arranged in a staggered manner, the low-pressure turbine stator blades 225 and the low-pressure turbine rotor blades 226 can freely rotate in a matrix, the exhaust section is provided with an exhaust cylinder 228. The rotating part one is connected to the machine body by means of a high pressure turbine roller bearing 224. The low pressure turbine stator blade 225 is fixed to a second rotating part, which is connected to the machine body through a low pressure turbine ball bearing 229. The low pressure turbine rotor blade 226 is fixedly connected to a rotating portion III which is fixed to the rotating shaft. The low pressure turbine ball bearing 229 is mounted on the rotating shaft. The exhaust section is internally provided with a bearing part 227, the bearing part 227 is fixed on a rotating part IV, and the rotating part IV is sleeved on a bearing through a low-pressure turbine ball bearing 229. The end of the rotating shaft is provided with a coupling 230. A bleed valve 209 is arranged at the joint of the front compressor cylinder 208 and the rear compressor cylinder 210. The outer wall 220 of the combustion chamber 221 and the exhaust section are fixed together through a second bolt 215 and a second nut 216, and a second spring washer 217 is arranged between the second nut 216 and the exhaust section. The first rotating part is provided with a first bolt 211, the first bolt 211 is provided with a first nut 212, and a first spring washer 213 is arranged on the inner side of the first nut 212. The outer wall 220 of the combustion chamber 221 is externally provided with a gas-permeable flat cylinder 214. The output shaft is provided with a thrust bearing 201 and a sliding bearing 202, and the thrust bearing 201 and the sliding bearing 202 are arranged in the compressed air section. The compressor front cylinder 208 houses the rotatable vanes 206. The lower part of the exhaust section is provided with a rear support 231. The lower part of the air compressing section is provided with a front support 232. The lower portion of the inlet volute 203 is provided with a compressor support 233.
The compressor continuously draws in air from the atmosphere through the intake cylinder 204 and compresses it; the compressed air enters the combustion chamber 221, is mixed with fuel injected through the fuel gas nozzle 218 and combusted to become high-temperature fuel gas, and then enters the turbine of the gas engine to expand and do work, so that the output shaft is pushed to carry the first power generation unit 1 to do work and generate power. When the gas turbine 2 is started in a static state, the generator is required to be converted into a motor to drive the gas turbine to rotate, and after the gas turbine is accelerated to a certain rotating speed, the starting device is tripped, so that the gas turbine can work in a generator mode to generate electricity. And the exhaust gas of the gas turbine 2 is introduced into the waste heat boiler 3, and the generated high-temperature and high-pressure steam drives the steam turbine 4 to drive the generator set II 5 to generate electricity. The common mode is that the gas turbine 2 and the steam turbine 4 coaxially push a single-shaft combined cycle of a generator, and the gas turbine 2 and the steam turbine 4 respectively and multi-shaft combined cycle of a generator set.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
Claims (10)
1. A combustion control method of a gas turbine generator set is characterized by comprising the following steps of: the method comprises the steps of driving a first generator set (1) and a second generator set (5), wherein the first generator set (1) is driven by a gas turbine (2), the gas outlet end of the gas turbine (2) is connected with a waste heat boiler (3), the second generator set (5) is driven by a steam turbine (4), high-pressure steam generated by the waste heat boiler (3) enters the steam turbine (4), liquid water generated by the steam turbine (4) returns to the waste heat boiler (3), the fuel inlet of the gas turbine (2) is connected with a fuel control system, and the control method of the fuel control system comprises the following steps: step 1, a control strategy before and after fuel switching: at the initial stage of switching, firstly checking and confirming whether various indexes of an outlet of a coal press reach set values or not, wherein the unit load is 40% -50% of a load interval of fuel switching; when the natural gas flow control valve is gradually closed to 10% of the maximum nonlinear valve position in the switching end stage, the natural gas flow control valve is rapidly closed at the maximum closing rate; simultaneously closing a synthetic gas to a torch bleeding valve to enable the synthetic gas to fully enter a gas turbine (2) for combustion; step 2, a dual-fuel switching control strategy: when the two fuels meet the switching conditions, the natural gas flow ratio is reduced from 100% to 0% according to the set rate, and the synthetic gas ratio is increased from 0% to 100% according to the set rate; the synthesis gas to flare bleed valve is gradually closed according to the rate of 5%/s, and the pressure of the coal press outlet is maintained at 18bar through the recirculation regulating valve; during the switching process, closed-loop control of the performance of the combustion chamber (221) and closed-loop control of combustion stability are performed.
2. The gas turbine generator set combustion control method of claim 1, wherein: -said combustion chamber (221) performance closed loop control comprising: load controller, exhaust temperature controller and compressor pressure limit.
3. The gas turbine generator set combustion control method of claim 1, wherein: the combustion stability closed-loop control comprises the steps of judging whether the combustion of the gas turbine (2) is stable or not, and measuring the dynamic pressure change condition in the combustion chamber (221) and the oscillation dynamic amplitude change generated by combustion; the combustion stability closed-loop control is to dynamically adjust the combustion state in real time according to a preset adjustment curve by taking Weng Ming and ACC as performance indexes; when the combustion is unstable, the unstable combustion condition is reflected in real time through Weng Ming and acceleration, and the exhaust temperature set value of the combustion engine, the change of the IGV opening and the real-time correction of the natural gas flow are automatically adjusted before the combustion is deteriorated, so that all parameters of a unit are ensured to be adjusted to an optimal state in the fuel switching process.
4. The gas turbine generator set combustion control method of claim 1, wherein: the dual fuel switching control strategy includes a natural gas fuel system and a syngas fuel system.
5. The gas turbine generator set combustion control method of claim 1, wherein: the natural gas fuel system uses natural gas fuel as ignition fuel for the gas turbine (2), controls the natural gas mass flow into the combustion chamber (221) of the gas turbine (2), and prevents natural gas from entering the gas turbine (2) under specific conditions; the system consists of a pre-filter module, a natural gas emergency shut-off valve, a natural gas diffusing valve, a natural gas control valve and a natural gas ball valve; the pre-filter is used for preventing any coarse foreign matters in a pipeline between the upstream fine filter unit and the filter from entering the natural gas emergency shut-off valve; the natural gas emergency shut-off valve is a valve that supplies or shuts off natural gas into the combustor when the gas turbine (2) is started and shut down, and during start-up or shut-down of the natural gas system; after the natural gas emergency shut-off valve, the gas supply line splits into two branches: one way is led to the synthesis gas system, and the other way directly enters the combustion chamber (221) through the diffusion burner; the relief valve is arranged between the natural gas emergency shutoff valve and the natural gas control valve and is used for discharging natural gas in a pipe section between the shutoff valves into the air; the natural gas control valve controls the natural gas flow to the diffusion burner according to the requirements of the control system of the gas turbine (2), and each pipeline leading to the combustion chamber (221) is provided with a natural gas ball valve for supplying or cutting off the natural gas flow to the burner.
6. The gas turbine generator set combustion control method of claim 1, wherein: when the syngas fuel system controls the syngas mass flow into the combustion chamber (221) of the gas turbine (2) and shuts off the syngas supplied to the gas turbine (2) under the conditions of a gas turbine (2) protection action or an emergency shutdown; one path of the synthesis gas from the outlet of the coal press is led to a diffusion torch for adjusting the heat value of the synthesis gas, the other path of the synthesis gas is led to a burner, the two branch lines of a combustion chamber (221) A and a combustion chamber (221) B are connected after passing through a filter outlet, and a synthesis gas shut-off valve group is arranged on the branch line of the burner, and the synthesis gas shut-off valve group comprises: the device comprises a synthesis gas emergency shut-off valve, a synthesis gas bleeding valve and a synthesis gas control valve.
7. The gas turbine generator set combustion control method of claim 1, wherein: the burner has three different fuel gas nozzle piping systems, including: a diffuser line, a synthesis gas line, and an on duty gas line; the diffuser pipeline is used for starting through the minimum fuel quantity, accelerating to the rated rotating speed and running at partial load until load switching; the on-duty gas pipeline is a fuel oil pipeline and is used for promoting the operation of the burner; the synthesis gas pipeline is used for converting the synthesis gas from load to be combusted to basic load; after passing through the synthesis gas cyclone, the synthesis gas flow enters a combustion chamber (221), is mixed with combustion air in the combustion chamber (221) and combusted, and the air is supplied to the combustor through a combustion air inlet through the inclined cyclone and the central axial cyclone; a small amount of combustion air enters the inner air passage through the central axial swirler into the combustion chamber (221); a smaller portion of the combustion air is used to cool the center nozzle, with the remainder of the combustion air flowing through the hydrocyclone.
8. The gas turbine generator set combustion control method of claim 1, wherein: the gas turbine (2) adopts dual-fuel switching during the operation of a dual-fuel gas turbine control system, natural gas is used as fuel from ignition, speed rise, constant speed and grid connection to a fuel switching load point (40)% - (50)% and is boosted to a preset pressure by a booster, and then enters a combustion chamber (221) from a natural gas control valve through a natural gas fuel passage by a pre-filter; at this stage, both the syngas fuel passage and other valves are closed; and after the unit load reaches a certain initial load, the fuel is quickly switched.
9. The gas turbine generator set combustion control method of claim 1, wherein: the gas turbine (2) comprises a machine body, an output shaft is arranged in the machine body, a gas compressing section, a combustion section and an exhaust section are sequentially arranged on the machine body, the gas compressing section comprises a gas compressing front cylinder (208) and a gas compressing rear cylinder (210), the gas compressing front cylinder (208) is connected with the gas compressing rear cylinder (210) end to end, the gas compressing front cylinder (208) is provided with a gas inlet volute (203) and a gas inlet cylinder (204), a plurality of gas compressing working blades (205) and gas compressing stator blades (207) are arranged in the gas compressing front cylinder (208) and the gas compressing rear cylinder (210), the gas compressing working blades (205) and the gas compressing stator blades (207) are alternately arranged, the output shaft drives the gas compressing working blades (205) and the gas compressing stator blades (207) to rotate, the tail end of the gas compressing rear cylinder (210) is fixedly provided with a combustion section, the combustion section comprises a combustion chamber (221) and an outer wall (220), a plurality of combustion chambers (221) are arranged in the combustion chamber (220), the combustion chamber (221) is provided with a plurality of combustion chambers (221), the combustion chamber (221) are arranged towards a gas inlet nozzle (218) and a gas inlet (218) of the gas compressing front end, and each combustion chamber (221) is provided with a gas inlet nozzle (218), the rear end of the outer wall (220) of the combustion chamber (221) is connected with an exhaust section, a first rotating part is arranged in the joint of the outer wall (220) of the combustion chamber (221) and the exhaust section, the first rotating part is fixedly connected with an output shaft, a high-pressure turbine stator blade (222) and a high-pressure turbine working blade (223) are arranged on the rotating part, be provided with a plurality of low pressure turbine stator blades (225), low pressure turbine rotor blade (226) in the exhaust section, low pressure turbine stator blade (225) set up with low pressure turbine rotor blade (226) are crisscross, low pressure turbine stator blade (225) and low pressure turbine rotor blade (226) can freely rotate in the base member, be provided with exhaust jar (228) on the exhaust section.
10. The gas turbine generator set combustion control method as set forth in claim 9, wherein: the rotating part I is connected with the machine body through a high-pressure turbine roller bearing (224).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311632576.5A CN117605579A (en) | 2023-12-01 | 2023-12-01 | Combustion control method for gas turbine generator set |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311632576.5A CN117605579A (en) | 2023-12-01 | 2023-12-01 | Combustion control method for gas turbine generator set |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117605579A true CN117605579A (en) | 2024-02-27 |
Family
ID=89944073
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311632576.5A Pending CN117605579A (en) | 2023-12-01 | 2023-12-01 | Combustion control method for gas turbine generator set |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117605579A (en) |
-
2023
- 2023-12-01 CN CN202311632576.5A patent/CN117605579A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5634327A (en) | Method of operating a gas-turbine group | |
| US8453461B2 (en) | Power plant and method of operation | |
| EP2119891B1 (en) | Control of working fluid flow of a two-shaft gas turbine | |
| RU2562686C2 (en) | Operating method of power plant in standby mode (versions), and power plant | |
| JP4923014B2 (en) | 2-shaft gas turbine | |
| US20130269360A1 (en) | Method and system for controlling a powerplant during low-load operations | |
| US20130269355A1 (en) | Method and system for controlling an extraction pressure and temperature of a stoichiometric egr system | |
| US9523313B2 (en) | System and method for loading a combined cycle power plant | |
| CN107664046B (en) | Energy-saving starting system of IGCC power station | |
| CN104373164B (en) | A kind of IGCC electric power station system with HRSG with Supplementary Firing and method of work | |
| US9828887B2 (en) | Power generation system having compressor creating excess air flow and turbo-expander to increase turbine exhaust gas mass flow | |
| US20140331686A1 (en) | Gas turbine combined cycle system | |
| EP1953352A2 (en) | Method and system for increasing modified Wobbe index control range of fuel gas | |
| US20160273408A1 (en) | Power generation system having compressor creating excess air flow and eductor for augmenting same | |
| US20170096936A1 (en) | Gas turbine assembly | |
| WO2018106991A1 (en) | Air logic control for auxiliary air injection system | |
| CN1072305C (en) | Starting method for combined device | |
| US20160273399A1 (en) | Power generation system having compressor creating excess air flow and turbo-expander for cooling inlet air | |
| US20160273407A1 (en) | Power generation system having compressor creating excess air flow and burner module therefor | |
| CN111894735B (en) | Hydrogen gas turbine combined cycle poly-generation method without NOx emission | |
| US20160273402A1 (en) | Power generation system having compressor creating excess gas flow for supplemental gas turbine system | |
| RU2018101302A (en) | Floating ship and method of operating a floating vessel | |
| CN101649780A (en) | Gas turbine independently driven by gas compressor | |
| CN117605579A (en) | Combustion control method for gas turbine generator set | |
| CN216198489U (en) | Gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |