CN107781847B - Dual gas fuel combustor and method of operating gas turbine using the same - Google Patents

Dual gas fuel combustor and method of operating gas turbine using the same Download PDF

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CN107781847B
CN107781847B CN201710869013.6A CN201710869013A CN107781847B CN 107781847 B CN107781847 B CN 107781847B CN 201710869013 A CN201710869013 A CN 201710869013A CN 107781847 B CN107781847 B CN 107781847B
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compressed air
gas
channel
auxiliary
combustion chamber
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CN107781847A (en
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张波
史绍平
闫姝
陈新明
穆延非
刘鑫
秦晔
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CHINA HUANENG GROUP
Huaneng Clean Energy Research Institute
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CHINA HUANENG GROUP
Huaneng Clean Energy Research Institute
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
    • Y02E20/18—Integrated gasification combined cycle [IGCC], e.g. combined with carbon capture and storage [CCS]

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  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

The invention discloses a combustor with double gas fuels and a gas turbine operation method adopting the combustor. When the power grid requires the IGCC to rapidly increase/decrease the load, but the yield of the synthetic gas cannot be rapidly changed due to the slow change of the load of the gasification furnace, the invention can also rapidly change the load of the gas turbine by rapidly increasing/decreasing the auxiliary natural gas flow and switching part of natural gas/synthetic gas channels to rapidly increase the natural gas flow greatly so as to respond to the demand of the power grid.

Description

Dual gas fuel combustor and method of operating gas turbine using the same
Technical Field
The invention relates to the technical field of gas turbines, in particular to a combustor suitable for double gas fuels and a gas turbine operation method adopting the combustor.
Background
An Integrated Gasification Combined Cycle (IGCC) is an advanced, efficient and environment-friendly power generation system integrating a gasification purification and gas-steam combined cycle system and comprises two major systemsThe system comprises a coal gasification and purification system and a gas and steam combined cycle system. Coal gasification and purification system utilizing gasification of coal to produce CO and H 2 Synthesis gas as main component and removing H entrained therein 2 S，NH 3 And dust, and the gas-steam combined cycle system generates electric power by using the purified synthesis gas as fuel. Because the synthesis gas has low heat value and contains a large amount of H 2 In order to avoid the occurrence of auto-ignition and flashback phenomena inside the combustor, gas turbines using syngas fuels typically employ diffusion combustion, i.e., mixed-and-fired. When the diffusion combustion mode is adopted, the synthesis gas and air enter the combustion chamber from different pipelines, the phenomenon of local uneven mixing is easy to occur, and meanwhile, H in the synthesis gas 2 The propagation speed difference of the CO adiabatic flame can reach several times, and the two functions are superposed, so that the flame front is difficult to stabilize at the same position, and the thermoacoustic coupling oscillation phenomenon of the flame appears, which is shown in that the vibration of a combustion chamber of the gas turbine is larger. In addition, the IGCC system is a tightly coupled system, which is characterized in that all the synthesis gas produced by the coal gasification and purification system is used for the gas-steam combined cycle system, and the only fuel of the gas-steam combined cycle system is the synthesis gas produced by the coal gasification and purification system. Therefore, if the output of the IGCC system needs to be increased, the load of the coal gasification system must be increased firstly, and then the load of the gas-steam combined cycle system must be increased, and if the output of the IGCC system needs to be reduced, the load of the coal gasification system must be reduced firstly, then the load of the gas-steam combined cycle system must be reduced, the whole process is long, and the adjustment rate of the load of the IGCC system is limited by the subsystem with the slowest adjustment rate, namely the coal gasification system taking the gasification furnace as the core equipment. For an entrained-flow gasifier using slag tapping, in order to ensure smooth slag tapping, the load increase and decrease generally adopt a mode of multiple small ranges, and the change of gasification process parameters is closely concerned, so that the load change rate of the gasifier is slow, the exertion of the load quick adjustment capability of a gas turbine is limited, and the overall load adjustment rate of an IGCC system is slowed.
Disclosure of Invention
Aiming at the two problems, namely the adoption of IGCC systemThe unstable combustion phenomenon of a gas turbine of the synthetic gas fuel and the slow load change rate of a tightly coupled IGCC system; the invention provides a combustor with double gas fuels and a gas turbine operation method adopting the combustor 4 Natural gas as main component and CO, H 2 The operation method of the gas turbine comprises a starting mode and a load rapid adjusting mode of the gas turbine adopting the combustor.
In order to achieve the purpose, the invention adopts the technical scheme that:
a burner with double gas fuels comprises a cylindrical combustion chamber 10 and a plurality of composite burners which are arranged at the top of the combustion chamber 10 and used for introducing natural gas and synthetic gas into the combustion chamber;
the external of the combustion chamber 10 is provided with a pressure-bearing shell 12 which is arranged concentrically with the combustion chamber 10, a space is arranged between the pressure-bearing shell and the combustion chamber, a vertical channel 13 of compressed air 21 is formed on the side surface, an annular horizontal channel 15 of compressed air is formed on the top surface, the upper wall surface of the combustion chamber 10 is provided with a heat insulation material layer 14 for protecting the inner wall of the combustion chamber 10, the lower part of the combustion chamber 10 adopts a necking design, and a necking section is not provided with a heat insulation material; the top of the combustion chamber 10 is also uniformly provided with a large number of small holes for injecting compressed air 21 for cooling the top area of the combustion chamber 10;
the composite burner mainly comprises a main compressed air channel 41, a main fuel channel 42, an auxiliary fuel channel 43, an auxiliary compressed air channel 44, a main compressed air channel flow measuring device 51 and an auxiliary compressed air channel flow measuring device 52; the main fuel channel 42 and the auxiliary fuel channel 43 are both cylindrical and concentrically arranged, the auxiliary fuel channel 43 is arranged inside, the main fuel channel 42 is arranged outside, and a gap between the two is used as an auxiliary compressed air channel 44; a plurality of channels which are tangential to the auxiliary compressed air channel 44 are arranged inside the main fuel channel 42, and the auxiliary compressed air channel 44 is communicated with the annular compressed air horizontal channel 15; a main compressed air passage flow rate measuring device 51 is disposed at an inlet of the main compressed air passage 41, and an auxiliary compressed air passage flow rate measuring device 52 is disposed at an inlet of the auxiliary compressed air passage 44, i.e., a passage inlet connected to the auxiliary compressed air passage 44 inside the main fuel passage 42; under normal conditions, syngas 22 enters combustion chamber 10 through primary fuel passage 42, natural gas 23 enters auxiliary fuel passage 43, and compressed air 21 enters combustion chamber 10 through primary compressed air passage 41 and auxiliary compressed air passage 44, respectively.
The ends of the primary compressed air channel 41, the primary fuel channel 42, the secondary fuel channel 43 and the secondary compressed air channel 44 entering the combustion chamber 10 are each provided with a swirler to enhance the mixing between the fuel and the air.
The arrangement mode of the composite burners at the top of the combustion chamber 10 is that eight separated composite burners are arranged in a circumferential symmetry mode.
The main compressed air passage flow measuring device 51 and the auxiliary compressed air passage flow measuring device 52 measure the flow of the compressed air 21 entering the combustion chamber 10 through the main compressed air passage 41 and the auxiliary compressed air passage 44, respectively, and feed back to the control system; the control system adjusts the flow of the synthesis gas 22 flowing through the main fuel passage 42 of the same composite burner according to formula 1 according to the flow of the compressed air 21 flowing through the main compressed air passage 41; the control system adjusts the natural gas flow flowing through the auxiliary fuel channel 43 of the same composite burner according to the formula 2 according to the flow of the compressed air 21 of the auxiliary compressed air channel 44;
Figure BDA0001416745700000031
Figure BDA0001416745700000032
aiming at ensuring the proper proportion of compressed air and fuel in the formula
Figure BDA0001416745700000033
For the quality flow of synthesis gas>
Figure BDA0001416745700000034
As mass flow of natural gasVolume, or>
Figure BDA0001416745700000041
For air mass flow, H syngas Is the unit mass calorific value of the synthesis gas, H rated For a rated specific mass heating value flowing through the passage, f 1 ,f 2 Is a linear relationship.
The method comprises the following steps of adopting a gas turbine operation mode of the combustor, wherein the combustor is a part of a gas turbine body, adopting a starting mode that when the yield of synthetic gas reaches more than 50% of the rated flow of the synthetic gas required by the gas turbine, turning the gas turbine by using other power sources, after the gas turbine reaches a certain rotating speed, adding auxiliary fuel natural gas 23 for ignition, continuing to increase the rotating speed of the gas turbine, adding synthetic gas 22 at the same time until the rotating speed of the gas turbine is stabilized at about 3000rpm, merging the gas turbine into a grid, and completing starting;
when the load of the gas turbine is quickly increased, if the required load increasing speed exceeds the range which can be borne by the gasification furnace, when the load of the gas turbine is increased to be not more than 5% of the rated load, the flow of the auxiliary fuel natural gas 23 is quickly increased, the load increasing requirement of the gas turbine is met firstly, and meanwhile, the yield of the synthetic gas 22 is gradually increased; when the power grid requires that the load of the gas turbine is quickly increased by more than 5% of the rated load, if the required load increasing rate exceeds the range which can be borne by the gasification furnace, natural gas 23 is adopted to replace synthetic gas 22 to flow through the main fuel channel 42 in the individual composite burner to enter the combustion chamber 10, and meanwhile, the flow of the replaced synthetic gas 22 is evenly distributed to the main fuel channels 42 of other composite burners, namely, the supply of the natural gas 23 is quickly and greatly increased, and meanwhile, the yield of the synthetic gas 22 is gradually increased to meet the requirement of quickly increasing the load of the gas turbine greatly;
when the load of the gas turbine is reduced rapidly, if the required load reduction rate exceeds the range that the gasification furnace can bear, the flow of the auxiliary fuel natural gas 23 is reduced rapidly, the load reduction requirement of the gas turbine is met firstly, and meanwhile, the yield of the synthesis gas 22 is reduced gradually.
The syngas 22 comes from a coal gasification and purification system in the IGCC system, and the natural gas 23 comes from a natural gas storage tank or pipeline.
Compared with the prior art, the invention utilizes the combustion of the natural gas 23 entering the combustion chamber 10 from the auxiliary fuel channel 43 as a stable combustion source, and provides enough heat to keep the synthesis gas 22 continuously combusted, so that the synthesis gas 22 can be stably combusted in a wider flow range (30-115% of rated flow), and the vibration caused by unstable combustion is reduced. When the power grid requires the IGCC to rapidly increase/decrease the load, but the yield of the synthetic gas cannot be rapidly changed due to the slow change of the load of the gasification furnace, the invention can also rapidly change the load of the gas turbine by rapidly increasing/decreasing the auxiliary natural gas flow and switching part of natural gas/synthetic gas channels to rapidly increase the natural gas flow greatly so as to respond to the demand of the power grid.
Drawings
FIG. 1: the gas turbine system adopts a structure schematic diagram suitable for a double gas fuel combustor.
FIG. 2 is a schematic diagram: the structure of the composite burner is shown schematically.
FIG. 3: the main fuel channel, the auxiliary compressed air channel and the auxiliary fuel channel in the composite burner are schematically shown in cross section.
FIG. 4: the arrangement mode of the composite burner at the top of the combustion chamber is shown schematically.
FIG. 5: a start-up procedure for a gas turbine adapted for use with a dual gas fuel burner is employed.
FIG. 6: when the gas turbine suitable for the double-gas fuel combustor is adopted to rapidly increase the load in a small range, the load of the gas turbine, the natural gas flow and the synthetic gas flow change trend.
FIG. 7: when the gas turbine suitable for the double-gas fuel combustor is adopted to rapidly and greatly increase the load, the load of the gas turbine, the natural gas flow and the synthetic gas flow change trend.
FIG. 8: when the gas turbine suitable for the double-gas fuel combustor is adopted to rapidly reduce the load in a small range, the load of the gas turbine, the natural gas flow and the synthetic gas flow change trend.
In the figure: 10-a combustion chamber; 11a,11b,11c,11d,11e,11f,11g, 11h-composite burners; 12-a pressure-bearing housing; 13-a vertical channel; 14-an insulating material; 15-compressed air horizontal channel; 20-outside air; 21-compressed air; 22-synthesis gas; 23-natural gas; 24-high temperature high pressure gas; 25-off gas; 30-a compressor; 31-axis; 32-turbine; 33-a generator; 41-main compressed air channel; 42-primary fuel channel; 43-an auxiliary fuel channel; 44-auxiliary compressed air channel; 51-primary compressed air channel flow measurement device; 52-auxiliary compressed air channel flow measuring device;
Detailed Description
The invention is described in further detail below with reference to the following figures and detailed description:
as shown in FIG. 1, the burner with double gas fuels of the present invention comprises a cylindrical combustion chamber 10 and a plurality of composite burners arranged on the top of the combustion chamber 10 for introducing natural gas and synthesis gas into the combustion chamber; the external of the combustion chamber 10 is provided with a pressure-bearing shell 12 which is arranged concentrically with the combustion chamber 10, a space is arranged between the pressure-bearing shell and the combustion chamber, a vertical channel 13 of compressed air 21 is formed on the side surface, an annular horizontal channel 15 of compressed air is formed on the top surface, the upper wall surface of the combustion chamber 10 is provided with a heat insulation material layer 14 for protecting the inner wall of the combustion chamber 10, the lower part of the combustion chamber 10 adopts a necking design, and a necking section is not provided with a heat insulation material; the top of the combustion chamber 10 is also uniformly provided with a large number of small holes for injecting compressed air 21 for cooling the top area of the combustion chamber 10;
as shown in fig. 2 and fig. 3, the composite burner is mainly composed of a main compressed air passage 41, a main fuel passage 42, an auxiliary fuel passage 43, an auxiliary compressed air passage 44, and a main compressed air passage flow measuring device 51 and an auxiliary compressed air passage flow measuring device 52; the main fuel channel 42 and the auxiliary fuel channel 43 are both cylindrical and concentrically arranged, the auxiliary fuel channel 43 is arranged inside, the main fuel channel 42 is arranged outside, and a gap between the two is used as an auxiliary compressed air channel 44; a plurality of channels which are tangential to the auxiliary compressed air channel 44 are arranged inside the main fuel channel 42 and are communicated with the auxiliary compressed air channel 44 and the annular compressed air horizontal channel 15; a main compressed air passage flow measuring device 51 is disposed at the inlet of the main compressed air passage 41, and an auxiliary compressed air passage flow measuring device 52 is disposed at the inlet of the auxiliary compressed air passage 44, i.e., the passage inlet inside the main fuel passage 42 connected to the auxiliary compressed air passage 44; under normal conditions, syngas 22 enters combustion chamber 10 through primary fuel passage 42, natural gas 23 enters auxiliary fuel passage 43, and compressed air 21 enters combustion chamber 10 through primary compressed air passage 41 and auxiliary compressed air passage 44, respectively.
As a preferred embodiment of the present invention, the ends of the main compressed air channel 41, the main fuel channel 42, the auxiliary fuel channel 43 and the auxiliary compressed air channel 44 entering the combustion chamber 10 are each provided with a swirler to enhance the mixing between the fuel and the air.
As shown in FIG. 4, as a preferred embodiment of the present invention, the composite burners are arranged on the top of the combustion chamber 10 in a manner that eight spaced composite burners are arranged in a circumferential symmetrical manner.
The gas turbine combustor and compressor 30, shaft 31, turbine 32, and generator 33 shown in fig. 1 together constitute a gas turbine body. The gas turbine system shown in fig. 1 is operated in the following manner: the gas turbine main fuel syngas 22 comes from a gasifier in the IGCC system and the auxiliary fuel natural gas 23 comes from a natural gas storage tank or pipeline. The external air 20 is compressed to about 1.7MPa by the compressor 30, and enters the combustion chamber 10 through the pressure-bearing shell and the vertical channel 13, the annular compressed air horizontal channel 15 between the top of the combustion chamber and the pressure-bearing shell, and the main compressed air channel 41 and the auxiliary compressed air channel 44 in the composite burner. The compressed air 21 flowing in this way can cool the combustion chamber 10 in a convective manner, and at the same time, can raise the initial temperature of the compressed air 21. Because 8 composite burners are arranged at the top of the combustion chamber 10, the compressed air 21 of the main compressed air channel 41 and the auxiliary compressed air channel 44 of the 8 composite burners comes from the annular compressed air horizontal channel 15 between the top of the combustion chamber and the pressure-bearing shell, which results in uneven distribution of the compressed air 21 flowing through the 8 composite burners to some extent. The main compressed air passage flow measuring device 51 and the auxiliary compressed air passage flow measuring device 52 measure the flow rate of the compressed air 21 entering the combustor 10 through the main compressed air passage 41 and the auxiliary compressed air passage 44, respectively, and feed back to the control system. The control system adjusts the flow of the synthesis gas 22 flowing through the main fuel passage 42 of the same composite burner according to formula 1 according to the flow of the compressed air 21 flowing through the main compressed air passage 41; the control system adjusts the natural gas flow through the auxiliary fuel channel 43 of the same composite burner according to equation 2 based on the flow of compressed air 21 in the auxiliary compressed air channel 44.
Figure BDA0001416745700000071
Figure BDA0001416745700000072
Aiming at ensuring the proper proportion of compressed air and fuel in the formula
Figure BDA0001416745700000081
For the quality and flow of the synthesis gas, is determined>
Figure BDA0001416745700000082
Is the mass flow of the natural gas and is based on the pressure>
Figure BDA0001416745700000083
For air mass flow, H syngas Is the unit mass calorific value of the synthesis gas, H rated For a rated specific mass heating value flowing through the passage, f 1 ,f 2 The relationship may be generally linear. The natural gas 23 and the auxiliary compressed air 21 respectively enter the combustion chamber 10 through the auxiliary fuel passage 43 and the auxiliary compressed air passage 44 in the composite burner for combustion to form stable flame, so as to create a stable flow field and a stable temperature field for the synthesis gas 22 entering the combustion chamber 10 through the main fuel passage 42 in the composite burner, thereby being beneficial to fully mixing the synthesis gas 22 and the main compressed air 21 entering the combustion chamber 10 through the main air passage 41 in the composite burner for stable combustion. The auxiliary fuel passage 43 is formed to be,the auxiliary compressed air channel 44 is arranged inside the main fuel channel 42 of the composite burner, which is beneficial to reducing the influence of the flow of the synthesis gas 22 and the main compressed air 21 on the flow of the natural gas 23 and the auxiliary compressed air 21, and in addition, the flow of the natural gas 23 and the flow of the auxiliary compressed air 21 are accurately matched, so that a continuous stable flame is created below the center of the composite burner, even when the flow of the synthesis gas 22 fluctuates, a stable high-temperature area can be continuously provided, the stable combustion of the synthesis gas 22 is facilitated, and the oscillation is reduced. High-temperature and high-pressure gas 24 generated by combustion enters a turbine channel through the exhaust of the combustion chamber and enters a turbine 32 to push turbine blades to rotate, and mechanical work is output through a shaft 31. Since the shaft 31 is connected to the compressor 30, the turbine 32 and the generator 33, a part of the mechanical work is used for compressing air by the compressor 30, and the rest is used for driving the generator 33 to generate electricity. Finally, the exhaust gas 25 from the turbine 32 is discharged through the exhaust passage.
The starting method of the gas turbine adopting the double-gas-fuel combustor is shown in fig. 5, when the yield of the synthetic gas reaches more than 50% of the rated flow of the synthetic gas required by the gas turbine, the gas turbine is turned by using other power sources, after the gas turbine reaches 600rpm, auxiliary fuel natural gas 23 can be added for ignition, after the ignition is successfully observed, the rotating speed of the gas turbine is continuously increased, and meanwhile, the synthetic gas 22 is added until the rotating speed of the gas turbine is stabilized at about 3000rpm, and the gas turbine is connected to the grid to finish the starting.
The mode of the gas turbine adopting the double gas fuel combustor for rapidly changing the load is as follows: 1, when the power grid requires IGCC to rapidly increase the load, but the load of the gasification furnace is adjusted in a small-amplitude manner for many times, and the load change rate of the gasification furnace cannot reach the rate required by the power grid, the output increase of the gas turbine cannot reach the change rate required by the power grid, at this time, because the natural gas 23 comes from a natural gas storage tank or a pipeline, the flow adjustment is flexible, as shown in a region 2 in fig. 6, the flow of the auxiliary fuel natural gas 23 can be rapidly increased to increase the load of the gas turbine, and meanwhile, the yield of the synthetic gas 22 is gradually increased. But the flow area of the auxiliary fuel channel 43 in the composite burner is limited, the method is only suitable for rapidly and slightly increasing the load of the gas turbine, and the load increasing range of the gas turbine does not exceed 5% of the rated load. After the required load on the grid is reached, as shown in FIG. 6, zone 3, the flow of natural gas 23 may be reduced gradually as the production of syngas 22 is increased gradually to maintain the gas turbine load constant. When the power grid requires a large-scale (more than 5% of rated load of the gas turbine) rapid increase of IGCC load, natural gas 23 may be used to replace syngas 22 and flow through the main fuel passage 42 of a particular composite burner into the combustion chamber 10, and meanwhile, the flow rate of the replaced syngas 22 is evenly distributed to the main fuel passages 42 of other composite burners, that is, the supply of natural gas 23 is increased greatly, and the yield of syngas 22 is increased gradually, so as to achieve the requirement of rapid increase of gas turbine load, at this time, the gas turbine load, the flow rate of natural gas 23, and the flow rate of syngas 22 change as shown in fig. 7. In the embodiment, as shown in the region 2 of fig. 7, the supply of the synthesis gas 22 to the composite burners 11a and 11e in fig. 4 is cut off, the line outside the gas turbine corresponding to the main fuel passage 42 inside the composite burners 11a and 11e is switched to high-pressure nitrogen or steam, the main fuel passage 42 inside the composite burners 11a and 111e is rapidly purged, and then the natural gas 23 mixed with an inert gas such as nitrogen or steam is switched to flow through the main fuel passage 42 inside the composite burners 11a and 111e and enter the combustion chamber 10 for combustion. In addition, the replaced syngas 22 is distributed equally to the other composite burners and enters the combustion chamber 10 for combustion through the main fuel passage 42. When the synthetic gas is switched to the natural gas, since the calorific value of the synthetic gas is lower than that of the natural gas, it is necessary to mix a certain amount of inert gas, preferably steam, with the natural gas 23 to reduce the calorific value of the mixed fuel containing the natural gas 23 as a main component, which enters the main fuel passage 42 inside the composite burners 11a,11e, to a level slightly higher than that of the synthetic gas 22, thereby preventing the excessive temperature of the burners due to the rapid entry of high calorific value fuel into the combustion chamber for combustion, and at this time, attention should be paid to the wall temperature change of the composite burners 111a, 11e. At the same time, as shown in the area 3 of fig. 7, it is necessary to gradually increase the production of the syngas 22 and simultaneously reduce the flow of the natural gas mixed fuel mixed with the inert gas flowing through the main fuel passage 42 inside the composite burners 11a,11e into the combustor 10, thereby maintaining the gas turbine load. When the natural gas mixed fuel mixed with the inert gas flowing through the main fuel passages 42 in the composite burners 11a,11e approaches the lower limit of self-sustaining combustion, the supply of the mixed fuel is cut off, the main fuel passages 42 in the composite burners 11a,11e are purged with high-pressure nitrogen or steam at a high speed, and then the mixture is switched to the synthesis gas 22.2, when the power grid requires IGCC to reduce the load rapidly, the flow of the synthesis gas cannot be reduced rapidly due to the limitation of the gasification furnace, and the natural gas comes from a storage tank or a pipeline, and the flow regulation is more flexible and convenient, as shown in region 2 of fig. 8, the flow of the natural gas 23 flowing through the auxiliary fuel channel 43 inside the composite burner can be reduced rapidly, the load reduction requirement of the gas turbine is met first, and the flow of the synthesis gas 22 is reduced gradually, because the auxiliary fuel natural gas 23 plays a role of stable combustion, the auxiliary fuel natural gas cannot be completely cut off, the load reduction range of the gas turbine is limited, and cannot exceed 3% of the rated load. After the gas turbine reaches the required load, the flow of syngas 22 is reduced and the flow of natural gas 23 is simultaneously increased to maintain the gas turbine load as shown in region 3 of fig. 8.

Claims (6)

1. A burner for dual gas fuels, characterized by: comprises a cylindrical combustion chamber (10) and a plurality of composite burners which are arranged at the top of the combustion chamber (10) and are used for introducing natural gas and synthetic gas into the combustion chamber;
a pressure-bearing shell (12) which is arranged concentrically with the combustion chamber (10) is arranged outside the combustion chamber (10), a space is formed between the pressure-bearing shell and the combustion chamber, a vertical channel (13) for compressed air (21) is formed on the side surface of the pressure-bearing shell, an annular horizontal channel (15) for compressed air is formed on the top surface of the pressure-bearing shell, a heat insulation material layer (14) is arranged on the upper wall surface of the combustion chamber (10) and used for protecting the inner wall of the combustion chamber (10), the lower part of the combustion chamber (10) adopts a necking design, and a necking section is not provided with a heat insulation material; the top of the combustion chamber (10) is also uniformly provided with a large number of small holes for injecting compressed air (21) for cooling the top area of the combustion chamber (10);
the composite burner mainly comprises a main compressed air channel (41), a main fuel channel (42), an auxiliary fuel channel (43), an auxiliary compressed air channel (44), a main compressed air channel flow measuring device (51) and an auxiliary compressed air channel flow measuring device (52); the main fuel channel (42) and the auxiliary fuel channel (43) are both cylindrical and are concentrically arranged, the auxiliary fuel channel (43) is arranged inside, the main fuel channel (42) is arranged outside, and a gap between the main fuel channel and the auxiliary fuel channel is used as an auxiliary compressed air channel (44); a plurality of channels tangential to the auxiliary compressed air channel (44) are arranged in the main fuel channel (42) and communicated with the auxiliary compressed air channel (44) and the annular compressed air horizontal channel (15); a main compressed air passage flow measuring device (51) is arranged at the inlet of the main compressed air passage (41), and an auxiliary compressed air passage flow measuring device (52) is arranged at the inlet of the auxiliary compressed air passage (44), namely the passage inlet which is connected with the auxiliary compressed air passage (44) in the main fuel passage (42); under normal working conditions, synthetic gas (22) flows through a main fuel channel (42), natural gas (23) flows through an auxiliary fuel channel (43), and compressed air (21) respectively flows through a main compressed air channel (41) and an auxiliary compressed air channel (44) to enter a combustion chamber (10).
2. A dual gas fuel burner as in claim 1, wherein: the ends of the main compressed air channel (41), the main fuel channel (42), the auxiliary fuel channel (43) and the auxiliary compressed air channel (44) entering the combustion chamber (10) are provided with swirlers for enhancing the mixing between fuel and air.
3. A dual gas fuel burner as in claim 1, wherein: the arrangement mode of the composite burners at the top of the combustion chamber (10) is that eight separated composite burners are arranged in a circumferential symmetry mode.
4. A dual gas fuel burner as recited in claim 1, wherein: the main compressed air channel flow measuring device (51) and the auxiliary compressed air channel flow measuring device (52) respectively measure the flow of the compressed air (21) entering the combustion chamber (10) through the main compressed air channel (41) and the auxiliary compressed air channel (44), and feed back to the control system; the control system adjusts the flow rate of the synthesis gas (22) flowing through the main fuel channel (42) of the same composite burner according to the formula 1 according to the flow rate of the compressed air (21) flowing through the main compressed air channel (41); the control system adjusts the flow of natural gas (23) flowing through an auxiliary fuel channel (43) of the same composite burner according to the formula 2 according to the flow of compressed air (21) of an auxiliary compressed air channel (44);
Figure FDA0001416745690000021
Figure FDA0001416745690000022
aiming at ensuring the proper proportion of compressed air and fuel in the formula
Figure FDA0001416745690000023
For the quality and flow of the synthesis gas, is determined>
Figure FDA0001416745690000024
Is the mass flow of the natural gas and is based on the pressure>
Figure FDA0001416745690000025
For air mass flow, H syngas Is the unit mass calorific value of the synthesis gas, H rated For a rated specific mass heating value flowing through the passage, f 1 ,f 2 Is a linear relationship.
5. A gas turbine operating mode using the combustor of claim 1, wherein: the combustor is a part of a gas turbine body, the starting mode is that when the yield of the synthetic gas reaches more than 50% of the rated flow of the synthetic gas required by the gas turbine, the gas turbine is turned by using other power sources, after the gas turbine reaches a certain rotating speed, auxiliary fuel natural gas (23) is input for ignition, at the moment, the rotating speed of the gas turbine is continuously increased, and meanwhile, the synthetic gas (22) is input until the rotating speed of the gas turbine is stabilized at about 3000rpm, and the gas turbine is connected to the grid to finish the starting;
when the load of the gas turbine is quickly increased, if the required load increasing speed exceeds the range which can be borne by the gasification furnace, when the load of the gas turbine is increased to be less than 5 percent of the rated load, the flow of auxiliary fuel natural gas (23) is quickly increased, the load increasing requirement of the gas turbine is met firstly, and meanwhile, the yield of the synthetic gas (22) is gradually increased; when the load of the gas turbine is required to be quickly increased by more than 5% of the rated load by the power grid, if the required load increasing rate exceeds the range which can be borne by the gasification furnace, natural gas (23) is adopted to replace synthetic gas (22) to flow through a main fuel channel (42) in a respective composite burner to enter the combustion chamber (10), and meanwhile, the flow of the replaced synthetic gas (22) is evenly distributed to main fuel channels (42) of other composite burners, namely, the supply of the natural gas (23) is quickly and greatly increased, and meanwhile, the yield of the synthetic gas (22) is gradually increased to meet the requirement of quickly increasing the load of the gas turbine to a large extent;
when the load of the gas turbine is rapidly reduced, if the required load reduction rate exceeds the range which can be borne by the gasification furnace, the flow of the auxiliary fuel natural gas (23) is rapidly reduced, the load reduction requirement of the gas turbine is met firstly, and meanwhile, the yield of the synthesis gas (22) is gradually reduced.
6. The gas turbine engine operating mode of claim 5, wherein: the synthesis gas (22) comes from a coal gasification and purification system in the IGCC system, and the natural gas (23) comes from a natural gas storage tank or a pipeline.
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