CN110375330B - Staged oxygen supply combustion chamber and staged oxygen supply combustion method of gas turbine - Google Patents
Staged oxygen supply combustion chamber and staged oxygen supply combustion method of gas turbine Download PDFInfo
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- CN110375330B CN110375330B CN201910492576.7A CN201910492576A CN110375330B CN 110375330 B CN110375330 B CN 110375330B CN 201910492576 A CN201910492576 A CN 201910492576A CN 110375330 B CN110375330 B CN 110375330B
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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
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- 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
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Abstract
The invention discloses a staged oxygen supply combustion chamber suitable for an oxygen-enriched combustion gas turbine and a staged combustion method. The staged oxygen supply combustion chamber is divided into a main combustion area, a secondary combustion area and a blending area. The front end of the main combustion area is provided with a main nozzle for spraying fuel, primary oxygen and primary carbon dioxide. And the front part of the secondary combustion area is provided with a secondary nozzle for spraying secondary oxygen and secondary carbon dioxide. The mixing area is provided with mixing holes for introducing three-stage carbon dioxide. In a low-load state, fuel and oxygen are all supplied to the main combustion area, so that the fuel is in lean combustion in the main combustion area, and CO emission is reduced; under the high load state, the secondary oxygen supply of the secondary combustion area is increased, so that fuel is burnt in the main combustion area in a rich mode, and the NOx emission is reduced. The invention has the advantages of wide operation load adjusting range (high adjustable ratio), low CO and NOx emission and the like.
Description
Technical Field
The invention relates to a staged oxygen supply combustion chamber suitable for an oxygen-enriched combustion gas turbine and a staged oxygen supply combustion method thereof, belonging to the technical field of power generation.
Background
The oxygen-enriched combustion gas turbine uses carbon dioxide as a circulating working medium, oxygen is used as an oxidant, high-temperature gas generated by combustion drives a turbine to rotate, and drives a generator to generate electricity or drive other loads. Meanwhile, the critical temperature and pressure of the carbon dioxide are low, so that the carbon dioxide is easy to realize in engineering, and the subcritical or supercritical fluid property of the carbon dioxide can be utilized to improve the cycle performance. Therefore, the oxygen-enriched gas turbine taking carbon dioxide as the working medium is widely concerned by scientific research institutions and energy companies all over the world. The gas turbine cycle using the oxygen-enriched combustion technology mainly comprises two modes of a subcritical gas turbine cycle and a supercritical carbon dioxide gas turbine cycle. The subcritical carbon dioxide gas turbine has low pressure (lower than 3MPa) and is relatively easy to realize technically; the supercritical carbon dioxide gas turbine has the advantages of high power density and compact volume due to high working pressure (30MPa), and simultaneously, the high pressure is more beneficial to capturing and storing carbon dioxide carbon and reducing the emission of greenhouse gases.
Due to the rapid development of renewable energy, thermal power needs to be used for peak regulation, and the gas turbine is a device with better variable working condition performance, so that the improvement of the low-load operation capability of the gas turbine and the expansion of the variable working condition operation range are important trends of the development of the gas turbine. This is a challenge for oxyfuel combustion gas turbines that use carbon dioxide as a working fluid.
This is because in an oxycombustion chamber, the flame temperature is not only related to the stoichiometric ratio (φ), but also to the molar ratio of oxygen to carbon dioxide (α). Since the separation of oxygen from air consumes much energy, the stoichiometric ratio of fuel to oxygen should be close to 1 in the entire combustor in order to improve the power generation efficiency, requiring oxygen to be saved. When the stoichiometric ratio is constant, the flame temperature increases as α increases. Otherwise, the flame temperature decreases. Meanwhile, the combustion temperature and the combustion rate can be reduced by high-concentration carbon dioxide in the combustion chamber, so that flameout is easy to occur under a low-load working condition, fuel and oxygen are not sufficiently combusted, and carbon monoxide and oxygen in combustion products are high in emission. In addition, when the operation load of the gas turbine is reduced, the mass flow of fuel is reduced in the traditional oxygen-enriched combustion chamber, and when the chemical equivalence ratio is ensured to be 1, the mass flow of oxygen is correspondingly reduced, so that the molar ratio (alpha) of oxygen to carbon dioxide is reduced when the mass flow of carbon dioxide is unchanged, the outlet temperature of the combustion chamber is reduced, carbon monoxide and oxygen are discharged relatively high when the oxygen-enriched gas turbine operates at low load, and the operation working condition range is relatively small. The discharge of carbon monoxide and oxygen not only reduces the energy utilization efficiency, but also corrodes the carbon dioxide delivery pipeline at the tail of the gas turbine. Therefore, in view of the above application limitations of the conventional combustion chamber in the oxycombustion gas turbine, the combustion chamber needs to be improved to improve the low-load operation capability of the oxycombustion gas turbine, widen the variable operating range, reduce the discharge of carbon monoxide and oxygen, and improve the energy utilization efficiency of the device.
Disclosure of Invention
The invention aims to provide a staged oxygen supply combustion chamber and an operation method thereof, wherein the combustion chamber is divided into a main combustion area, a secondary combustion area and a mixing area, oxygen is supplied through the main combustion area and the secondary combustion area in two stages, and carbon dioxide is supplied through the main combustion area, the secondary combustion area and the mixing area in three stages, so that the low-load operation capacity of a gas turbine is improved, the emission of carbon monoxide and oxygen is reduced, and the emission of NOx under high load is reduced through staged oxygen supply, thereby widening the operation working condition range of the oxygen-enriched combustion gas turbine.
The invention is realized by the following technical scheme:
the utility model provides a hierarchical oxygen suppliment combustion chamber, hierarchical oxygen suppliment combustion chamber can be used for richening combustion gas turbine, hierarchical oxygen suppliment combustion chamber sets up one at least, hierarchical oxygen suppliment combustion chamber includes the combustion chamber overcoat and sets up the flame tube in the combustion chamber overcoat, the flame tube is the tubular structure of convex shrink form for one end, the flame tube with be working medium gas passage between the combustion chamber overcoat. According to the flow direction of the inlet and outlet gases as the front and back directions, the interior of the flame tube is sequentially divided into a main combustion area, a secondary combustion area and a blending area from front to back; the front end of the main combustion zone is provided with a main nozzle; the wall surface of the secondary combustion area is provided with more than two secondary nozzles, each secondary nozzle comprises a secondary oxygen nozzle and a secondary carbon dioxide nozzle, and the secondary carbon dioxide nozzles are communicated with the working medium gas channel; the secondary nozzles are symmetrically or uniformly arranged around the secondary combustion area at one end close to the primary combustion area; the wall surface of the mixing region is provided with a plurality of mixing holes which are uniformly distributed around the mixing region.
In the technical scheme, the main nozzle comprises a fuel channel, a main oxygen channel and a main carbon dioxide channel, and the main carbon dioxide channel is communicated with a working medium gas channel between the flame tube and the combustion chamber outer sleeve.
In the above technical solution, the combustion chamber further includes a swirler disposed in front of the main nozzle and an ignition device disposed at the front end of the main combustion zone.
A gas turbine comprises a compressor, a staged oxygen supply combustion chamber and a turbine which are sequentially connected, wherein at least one staged oxygen supply combustion chamber is arranged.
A gas turbine staged oxygen supply combustion method using a gas turbine as described above, the method comprising:
calculating to obtain the maximum oxygen receiving amount of a main combustion area according to the limit temperature of the main combustion area of the gas turbine staged oxygen supply combustion chamber;
carbon dioxide is compressed by a compressor and then is used as a working medium to be fed into a working medium gas channel formed between a combustion chamber outer sleeve and a flame tube, so that the carbon dioxide respectively enters a main combustion area, a secondary combustion area and a blending area of the staged oxygen supply combustion chamber through a main nozzle, a secondary carbon dioxide nozzle and a blending hole to respectively form primary carbon dioxide, secondary carbon dioxide and tertiary carbon dioxide injection;
feeding a proper amount of fuel into a main combustion area through a main nozzle of a staged oxygen supply combustion chamber of the gas turbine;
setting the chemical equivalence ratio phi of the fuel and the total oxygen amount to be more than or equal to 0.9 and less than or equal to 1, calculating the total oxygen flow according to the chemical equivalence ratio, and comparing the total oxygen flow with the maximum oxygen receiving amount of the main combustion area;
when the total oxygen flow is less than or equal to the maximum oxygen content of the main combustion area, spraying oxygen into the main combustion area through a main nozzle; mixing the fuel, oxygen and carbon dioxide entering through the main nozzle and igniting the fuel, and forming the fuel and oxygen in the main combustion zone with phi of 0.9-phiPZLean combustion of less than or equal to 1 to generate high-temperature fuel gas; mixing high-temperature fuel gas from the main combustion area with secondary carbon dioxide introduced through a secondary nozzle to form high-temperature flue gas;
when the total oxygen flow is larger than the maximum oxygen content of the main combustion area, enabling oxygen to enter the main combustion area and the secondary combustion area through the main nozzle and the secondary oxygen nozzle respectively to form primary oxygen supply and secondary oxygen supply; the primary oxygen quantity entering the main combustion area through the main nozzle is the maximum oxygen receiving quantity of the main combustion area; mixing fuel, oxygen and carbon dioxide entering through the main nozzle and igniting the fuel, and enabling the fuel and the oxygen to form rich combustion in the main combustion area to generate high-temperature fuel gas; mixing the high-temperature fuel gas from the main combustion zone with secondary oxygen and secondary carbon dioxide introduced through a secondary nozzle in the secondary combustion zone, and enabling incomplete combustion in the high-temperature fuel gas to be completely combusted in a partial combustion mode to generate high-temperature flue gas;
spraying three-stage carbon dioxide through the mixing holes, mixing the carbon dioxide with high-temperature flue gas from the secondary combustion area to reduce the temperature of the high-temperature flue gas, and feeding the high-temperature flue gas into a turbine to do work; the temperature of the flue gas is reduced to form waste gas after work is done by a turbine, and the main components of the waste gas are carbon dioxide and water vapor;
the waste gas is separated to obtain dry flue gas and condensed water which take carbon dioxide as main components respectively, part of the dry flue gas is used as recycle gas, is mixed and regulated, then is sent into a compressor to be compressed and boosted, and is used as working medium to be sent into a working medium gas channel formed between a combustion chamber outer sleeve and a flame tube.
When the gas turbine further comprises a condenser, a separation valve and a mixing valve and a carbon dioxide storage tank connected to the mixing valve, the method further comprises:
enabling the waste gas to enter a condenser to recover waste heat, and entering a separation valve to perform steam-water separation, and separating gas with carbon dioxide as a main component from water to obtain dry flue gas; and a part of the separated dry flue gas is used as recycle gas, enters a mixing valve, enters an air compressor after the flow is regulated by a carbon dioxide storage tank, is compressed and raised in pressure, and is used as a working medium to be fed into a working medium gas channel formed between the combustion chamber outer sleeve and the flame tube.
In the technical scheme, the carbon dioxide enters a main combustion area, a secondary combustion area and a blending area of the graded oxygen supply combustion chamber through a main nozzle, a secondary carbon dioxide nozzle and a blending hole respectively, and the spraying proportion of the formed primary carbon dioxide, secondary carbon dioxide and tertiary carbon dioxide is (50-60): (5-20): 20-45).
In the above technical solution, the staged oxygen supply combustion method further includes a staged adjustment method, and the staged adjustment method includes:
the load of the gas turbine is gradually increased, so that the fuel supplied to the main combustion area through a main nozzle of the staged oxygen supply combustion chamber is gradually increased;
adjusting the total oxygen flow according to the stoichiometric ratio phi of the fuel to the oxygen, and adjusting the oxygen to be sprayed into the main combustion area through a main nozzle of a staged oxygen supply combustion chamber when the total oxygen flow is less than or equal to the maximum oxygen receiving amount of the main combustion area so as to ensure that the primary oxygen ratio is 100%; and when the oxygen flow is continuously increased and is larger than the maximum oxygen storage amount of the main combustion area, taking partial oxygen exceeding the maximum oxygen storage amount of the main combustion area as secondary oxygen and spraying the secondary oxygen into the secondary combustion area through a secondary oxygen nozzle.
In the above technical solution, the hierarchical adjustment method further includes:
the load of the gas turbine is gradually reduced, so that the fuel supplied to the main combustion area through a main nozzle of the staged oxygen supply combustion chamber is gradually reduced;
adjusting the total oxygen flow according to the stoichiometric ratio phi of the fuel to the oxygen, and when the total oxygen flow is larger than the maximum oxygen receiving amount of the main combustion area, sequentially adjusting the total oxygen flow according to the sequence of adjusting the secondary oxygen supply first and then adjusting the primary oxygen supply; when the total oxygen flow is less than or equal to the maximum oxygen receiving amount of the main combustion area, the primary oxygen amount of the main combustion area is reduced.
The invention has the following advantages and beneficial effects: 1) oxygen is fed in two stages, and the distribution proportion between the two stages is dynamically adjusted along with the load, so that the operating load range of the gas turbine is widened; 2) through the graded oxygen supply, the combustion mode of the first stage (main combustion zone) is rich in combustion at high load and gradually transits to equal equivalence ratio combustion along with the reduction of the load, so that the main combustion zone maintains stable combustion at high load, the pollutant emission is reduced on the whole, and the stable combustion can be maintained at low load to avoid flameout, stopping and other phenomena; 3) the carbon dioxide is fed in three stages, the second stage carbon dioxide plays a role in protecting the second stage oxygen nozzle, and the third stage carbon dioxide can effectively reduce the temperature of the fuel gas in the combustion chamber.
Drawings
FIG. 1 is a schematic view of an oxycombustion gas turbine cycle system according to the present invention.
Fig. 2 is a schematic view of a staged oxygen supply combustor in accordance with the present invention.
Fig. 3 is a schematic view (view a-a) of the arrangement of the secondary nozzle of the staged oxygen supply combustor according to the present invention.
FIG. 4 is a schematic illustration of gas turbine combustor operating parameter tuning in accordance with the present invention.
In the figure: 1-staged oxygen supply combustion chamber; 2-a turbine; 3, a generator; 4-a condenser; 5-a separation valve; 6-a mixing valve; 7, an air compressor; 8-air separator; 9-a connecting shaft; 11-a flame tube; 12-a primary nozzle; 121-fuel channel; 122-primary oxygen channel; 123-a cyclone; 13-a secondary nozzle; 131-secondary oxygen jets; 132-secondary carbon dioxide jets; 14-a mixing hole; 15-a main combustion zone; 16-secondary combustion zone; 17-a blending region; 18-a flow divider valve.
Detailed Description
The following describes the embodiments and operation of the present invention with reference to the accompanying drawings.
The terms of orientation such as up, down, left, right, front, and rear in the present specification are established based on the positional relationship shown in the drawings. The corresponding positional relationship may also vary depending on the drawings, and therefore, should not be construed as limiting the scope of protection.
The oxycombustion gas turbine of the present invention means that the gas turbine is operated under oxycombustion conditions in which combustion is performed with an oxygen-containing gas having an oxygen content (20.947%) higher than that of air. At this time, there are three combustion states, i.e., rich combustion (Φ >1), equi-equivalent combustion (Φ ═ 1), and lean combustion (Φ <1), analyzed by the stoichiometric ratio (Φ) of fuel and oxygen. Equivalent combustion, i.e. combustion of fuel and oxygen according to the stoichiometric ratio of complete combustion. In actual operation, phi is approximately equal to 1, and the fuel and the oxygen are dynamically supplied, so that the fuel and the oxygen are considered to be equivalent combustion. The combustion state with Fuel rich relative to oxygen (Fuel rich) is rich combustion, whereas the combustion state with Fuel lean relative to oxygen (Fuel lean) is lean combustion.
As shown in figure 1, the oxygen-enriched combustion gas turbine circulating system comprises a staged oxygen supply combustion chamber 1, a turbine 2 and a generator 3 which are sequentially connected, wherein the turbine 2 is further sequentially connected with a condenser 4 and a separating valve 5, the separating valve 5, a mixing valve 6 and a compressor 7 are sequentially connected, and separated carbon dioxide is mixed and compressed and then is sent back to the staged oxygen supply combustion chamber 1. The air separator 8 is connected to the staged oxygen supply combustor 1, separates oxygen in the air from other gases such as nitrogen and carbon dioxide, and sends the oxygen to the staged oxygen supply combustor 1. The connecting shaft 9 is respectively connected between the turbine 2 and the generator 3 and between the turbine 2 and the compressor 7 to realize the transmission between the turbine 2 and the compressor 7 and between the generator 3, and the turbine 2 is transmitted to the generator 3 to generate power. The staged oxygen supply combustion chamber 1 is provided with at least one staged oxygen supply combustion chamber, and when more than two staged oxygen supply combustion chambers are arranged, a plurality of staged oxygen supply combustion chambers are arranged in an annular shape or a plurality of cylindrical shapes around a shaft.
As shown in fig. 2, the staged oxygen supply combustor 1 includes a combustor casing and a liner 11 disposed inside the combustor casing. The flame tube 11 is a cylindrical structure with one end in an arc-shaped contraction shape, a working medium gas channel is arranged between the flame tube 11 and the combustion chamber outer sleeve, and for the oxygen-enriched combustion gas turbine, carbon dioxide is selected as the working medium. According to the flow direction of the inlet and outlet gases as the front and back directions, the interior of the flame tube 11 is divided into a main combustion area 15, a secondary combustion area 16 and a blending area 17 from front to back in sequence.
The front end of the main combustion zone 15 is provided with a main nozzle 12. The main nozzle 12 comprises a fuel passage 121, a main oxygen passage 122 and a main carbon dioxide passage, and the main carbon dioxide passage is communicated with a working medium gas passage between the flame tube and the combustion chamber outer sleeve. Fuel is injected through fuel passage 121, primary oxygen is injected through primary oxygen passage 122, and primary carbon dioxide enters through the primary carbon dioxide passage. The combustion chamber further includes a swirler 123 disposed in front of the main nozzles 12 and an ignition device disposed in front of the main combustion zone 15. The swirler 123 is provided in front of the main nozzle with the fuel passage 121 as a center axis for swirling mixing of the primary oxygen and the primary carbon dioxide.
The secondary combustion zone 16 is provided with more than two secondary nozzles 13 in the wall. Secondary nozzle 13 includes a secondary oxygen port 131 and a secondary carbon dioxide port 132, secondary carbon dioxide port 132 being in communication with the working fluid gas passage. In one embodiment, the secondary oxygen jets 131 are centrally located and the secondary carbon dioxide jets 132 are concentrically located around the secondary oxygen jets 131 such that the secondary carbon dioxide entrains the secondary oxygen jets and creates cross-jet mixing with the incoming flame from the primary combustion zone. The secondary nozzles 13 are arranged symmetrically or uniformly around the secondary combustion zone 16 near one end of the primary combustion zone 15, as shown in fig. 3.
The wall surface of the mixing area 17 is provided with a plurality of mixing holes 14, and the mixing holes 14 are uniformly distributed around the mixing area 17.
The oxygen injected into the primary combustion zone 15 through the primary nozzles 12 of the staged oxygen supply combustor 1 is regarded as primary oxygen, and the oxygen injected into the secondary combustion zone 16 through the secondary oxygen nozzle 131 is regarded as secondary oxygen. Oxygen gasThe air is obtained by separating air through an air separator 8. The total oxygen supply amount is
The primary oxygen ratio and the secondary oxygen ratio are respectively
And
wherein
During operation, the maximum oxygen receiving amount of the main combustion area 15 is calculated according to the limit temperature of the main combustion area 15 of the gas turbine staged oxygen supply combustion chamber 1. The limit temperature of a gas turbine combustor is determined by its material. The temperature of the primary combustion zone is directly related to the amount of fuel, the amount of oxygen, and the amount of carbon dioxide. Under the condition that the flow of carbon dioxide serving as a working medium is unchanged, the combustion heat is increased along with the increase of fuel quantity and oxygen in the main combustion area, the temperature in the main combustion area is continuously increased due to the unchanged flow of the carbon dioxide to reach the limit temperature of the main combustion area, and if the oxygen supply amount of the main combustion area is continuously increased, the temperature of the main combustion area is bound to exceed the limit temperature, so that the main nozzle is corroded to influence the operation of the gas turbine. In order to avoid nozzle erosion, the oxygen supply amount corresponding to the limit temperature is the maximum oxygen storage amount of the main combustion area and is also the critical point for the staged oxygen supply combustion regulation and control of the invention.
Carbon dioxide is compressed by the compressor 7 and then is fed into a working medium gas channel formed between the outer sleeve of the combustion chamber and the flame tube 11 as a working medium, so that the carbon dioxide respectively enters a main combustion area 15, an auxiliary combustion area 16 and a mixing area 17 of the staged oxygen supply combustion chamber 1 through a main nozzle 12, a secondary carbon dioxide nozzle 132 and a mixing hole 14 to respectively form primary carbon dioxide, secondary carbon dioxide and tertiary carbon dioxide injection. Wherein, the first-order carbon dioxide y1Second stage carbon dioxide y2And tertiary carbon dioxide y3The ratio of (50-60) to (5-20) to (20-45).
An appropriate amount of fuel corresponding to the load is supplied to the main combustion zone 15 entirely through the main nozzle 12 of the staged oxygen supply combustor 1 of the gas turbine.
The chemical equivalence ratio phi of the fuel and the total oxygen is set to be more than or equal to 0.9 and less than or equal to 1, the cost is higher because the oxygen is obtained by air separation, the selection of the phi is as close to equivalent combustion as possible, and the full combustion of the oxygen is ensured. The total oxygen flow is calculated from the stoichiometric ratio of the fuel quantity to the oxygen quantity, i.e.
Where k is the fuel coefficient for mass flow versus stoichiometry conversion. The total oxygen flow is compared to the maximum oxygen uptake of the primary combustion zone 15.
When the total oxygen flow is less than or equal to the maximum oxygen receiving amount of the main combustion area 15, the oxygen is sprayed into the main combustion area 15 through the main nozzle 12; fuel, oxygen and carbon dioxide entering through the main nozzle 12 are mixed and the fuel is ignited, and the fuel and oxygen are formed in the main combustion zone 15 at 0.9 ≤ phiPZLean combustion of less than or equal to 1 generates high-temperature fuel gas with relatively sufficient combustion. The high-temperature fuel gas from the main combustion area 15 is mixed with the secondary carbon dioxide introduced through the secondary nozzle 13, and the high-temperature fuel gas is continuously and completely combusted in the secondary combustion area 16 by increasing the gas retention time to generate high-temperature flue gas.
When the total oxygen flow is larger than the maximum oxygen content of the main combustion area 15, the oxygen enters the main combustion area 15 and the secondary combustion area 16 through the main nozzle 12 and the secondary oxygen nozzle 132 respectively to form primary oxygen and secondary oxygen. At this time, the primary oxygen quantity entering the main combustion zone 15 through the main nozzle 12 is the maximum oxygen receiving quantity of the main combustion zone. The fuel, oxygen and carbon dioxide entering through the main nozzle 12 are mixed and ignited, and the fuel and oxygen are caused to form rich combustion in the main combustion zone 15, generating high-temperature combustion gas. The hot gases are propelled toward the turbine 2 and into the secondary combustion zone 16. Mixing the high-temperature fuel gas from the main combustion zone 15 with the secondary oxygen and the secondary carbon dioxide introduced through the secondary nozzle 13 to ensure that incompletely combusted components (such as CO) and O in the high-temperature fuel gas2Complete combustion and high-temperature flue gas generation. Meanwhile, the injection of the secondary carbon dioxide forms low-temperature protection for the secondary nozzle 13, so that the high-temperature combustion is avoidedAnd (4) melting and corroding.
Carbon dioxide is sprayed in through the mixing holes 14 and is mixed with high-temperature flue gas from the secondary combustion zone 16, so that the temperature of the high-temperature flue gas is reduced, the high-temperature flue gas enters the turbine 2 to do work, and the generator 3 is driven to generate electricity. The temperature of the flue gas is reduced to form waste gas after the work of the turbine 2, and the main components of the waste gas are carbon dioxide and water vapor.
The waste gas is separated by a separating valve 5 to respectively obtain dry flue gas and condensed water which take carbon dioxide as main components, part of the dry flue gas is used as recycle gas, and the rest dry flue gas enters a carbon capture device. The recirculated gas enters a regulating valve 6, is mixed and regulated by increasing/reducing the flow of carbon dioxide through a carbon dioxide storage tank, is sent to a gas compressor 7 for compression and boosting, and is sent to a working medium gas channel formed between the outer sleeve of the combustion chamber and the flame tube 11 as a working medium.
When the load of the gas turbine is changed, whether the load is increased or decreased, the oxygen supply of the main combustion area is ensured, namely, the oxygen of the first stage is increased and then decreased.
When the load of the gas turbine is gradually increased, the fuel supplied to the main combustion zone 15 through the main nozzles 12 of the staged oxygen supply combustor 1 is gradually increased. Adjusting the total oxygen flow according to the stoichiometric ratio phi of the fuel to the oxygen, and adjusting the oxygen to be sprayed into a main combustion area 15 through a main nozzle 12 of a staged oxygen supply combustion chamber 1 when the total oxygen flow is less than or equal to the maximum oxygen receiving amount of the main combustion area so that the primary oxygen ratio is 100%; as the oxygen flow continues to increase and is greater than the primary combustion zone maximum oxygen uptake, a portion of the oxygen in excess of the primary combustion zone maximum oxygen uptake is injected into the secondary combustion zone 16 through the secondary oxygen jets 132.
When the gas turbine load is gradually reduced, the fuel supplied to the main combustion zone 15 through the main nozzles 12 of the staged oxygen supply combustor 1 is gradually reduced. At the moment, the total oxygen flow is adjusted and reduced according to the chemical equivalence ratio phi of the fuel and the oxygen, and the total oxygen is adjusted and reduced sequentially according to the sequence of adjusting and reducing the secondary oxygen first and then adjusting and reducing the primary oxygen first. The specific adjustment and reduction method comprises the following steps: when the total oxygen flow is larger than the maximum oxygen receiving amount of the main combustion area, only adjusting and reducing the secondary oxygen amount, and keeping the primary oxygen amount unchanged; when the total oxygen flow is regulated to be less than or equal to the maximum oxygen receiving amount of the main combustion area, the secondary oxygen is stopped, only the oxygen is supplied to the main combustion area, and the primary oxygen amount is gradually regulated.
Under normal operating conditions, i.e. when the gas turbine is operating at a load greater than 30%, the carbon dioxide flow is generally constant. When the load is reduced to a certain extent (usually below 30%, especially close to shutdown), the carbon dioxide flow needs to be gradually reduced until shutdown, since the required working medium has been greatly reduced. The excess carbon dioxide can be recovered by using a carbon dioxide storage tank through the regulating valve 6; or a separate valve 5 is used to drain excess carbon dioxide for carbon capture.
Accordingly, during the start-up of the gas turbine, the carbon dioxide flow also needs to be gradually increased, and after reaching a certain load (usually 30%), the carbon dioxide flow is maintained.
FIG. 4 is a graph showing the load control range of a staged combustion gas turbine as compared with the operating load range of a conventional gas turbine, according to one embodiment of the staged oxygen supply combustion method according to the present invention. As shown, the interval of about 30% to 70% of the gas turbine load is the main combustion zone holding phiPZAn interval of near equivalent combustion state of 1 and temperature rise with increasing load. At the moment, fuel and oxygen in the staged combustion chamber are all supplied through a main nozzle of the main combustion area, carbon dioxide is supplied in three stages, the fuel quantity, the total oxygen quantity and the first-stage oxygen quantity are synchronously increased, and phi in the main combustion areaPZEqual to the diameter of the staged combustion chamber phi, and the fuel in the main combustion zone maintains phi in the stagePZNear equivalent combustion state of 1. The secondary combustion area and the mixing area are both used as a temperature reduction area for further mixing high-temperature fuel gas and working medium. Because the working medium is supplied in three stages, the carbon dioxide in the main combustion area is greatly reduced, namely sufficient oxygen supply is maintained in a small area (main combustion area), so that high-temperature flame of the fuel is maintained and the fuel is fully combusted, and the phenomenon that the CO concentration is too high and even flameout and shutdown are caused due to the fact that the temperature of the fuel flame is difficult to maintain because of too large flow of the working medium and insufficient local oxygen supply is avoided under a low-load state. This is a problem that is difficult to overcome in the low load condition of the rich-burn gas turbine of the conventional combustor. Therefore, the low-load operation range of the rich-combustion gas turbine is greatly widened by the staged oxygen supply combustion mode.
When the load is further increased, the fuel quantity is continuously increased, and the oxygen supply quantity in the main combustion zone is not increased (therefore, the main combustion zone phi is further increasedPZAnd the secondary oxygen is added, so that the fuel is subjected to rich combustion in the primary combustion area to generate incompletely combusted high-temperature fuel gas, the high-temperature fuel gas enters the secondary combustion area to be further completely combusted, the primary combustion area is prevented from exceeding the limit temperature, the fuel is fully combusted, and the NOx emission is enlarged to be reduced in a high-load state. The oxygen is separated from the air, so that the oxygen inevitably contains a small amount of nitrogen, which causes the generation of NOx in the combustion process, and the combustion method of the fractional oxygen supply greatly reduces the generation of NOx because the main combustion zone adopts rich combustion under high load. Therefore, the staged combustion mode not only widens the low-load operation range of the gas turbine, but also reduces the NOx emission during the high-load operation of the gas turbine.
In short, the invention forms staged oxygen supply combustion by staged oxygen supply (oxidant) and staged carbon dioxide supply (working medium), flexibly adjusts the distribution proportion of oxygen in each combustion zone of the combustion chamber, improves the combustion stability of the main combustion zone, and avoids the problem of high-temperature damage by the low-temperature protection effect of the working medium, when the combustion chamber operates at low load, the distribution proportion of the oxygen in the main combustion zone is increased (thereby increasing the α of the main combustion zonePZ) The flame temperature of the main combustion area is increased, and the problems of carbon monoxide and oxygen emission increase, flameout and the like caused by low flame temperature are avoided, so that the operating condition range of the combustion chamber is widened. When the combustion chamber is in a high-load working condition, the oxygen distribution proportion of the main combustion area is reduced, the flame temperature of the main combustion area is prevented from exceeding the limit temperature which can be borne by the material, and the problems of erosion of a flame tube and a nozzle, tempering and the like caused by overhigh flame temperature are avoided.
The staged oxygen supply combustion method is suitable for the conventional oxygen-enriched combustion gas turbine and is also suitable for subcritical and supercritical oxygen-enriched combustion gas turbines.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The staged oxygen supply combustion chamber is characterized in that the staged oxygen supply combustion chamber (1) is internally divided into a main combustion area (15), a secondary combustion area (16) and a mixing area (17) from front to back in sequence according to the flow direction of inlet and outlet air, wherein the staged oxygen supply combustion chamber (1) can be used for a rich combustion gas turbine, at least one staged oxygen supply combustion chamber (1) is arranged, the staged oxygen supply combustion chamber (1) comprises a combustion chamber outer sleeve and a flame tube (11) arranged in the combustion chamber outer sleeve, one end of the flame tube (11) is of a cylindrical structure with an arc-shaped shrinkage shape, and a working medium gas channel is arranged between the flame tube (11) and the combustion chamber outer sleeve; the front end of the main combustion zone (15) is provided with a main nozzle (12), the main nozzle (12) comprises a fuel channel (121), a main oxygen channel (122) and a main carbon dioxide channel, and the main carbon dioxide channel is communicated with a working medium gas channel between the flame tube and the combustion chamber outer sleeve; the wall surface of the secondary combustion area (16) is provided with more than two secondary nozzles (13), each secondary nozzle (13) comprises a secondary oxygen nozzle (131) and a secondary carbon dioxide nozzle (132), and each secondary carbon dioxide nozzle (132) is communicated with the working medium gas channel; one end of the secondary nozzle (13) close to the main combustion area (15) is symmetrically or uniformly arranged around the secondary combustion area (16); the wall surface of the mixing region (17) is provided with a plurality of mixing holes (14), and the mixing holes (14) are uniformly distributed around the mixing region (17).
2. A staged oxygen supply combustor according to claim 1, characterized in that the combustor further comprises a swirler (123) arranged in front of the main nozzles (12) and an ignition device arranged in front of the main combustion zone (15).
3. A gas turbine, characterized in that it comprises a compressor (7), a staged oxygen supply combustor (1) as claimed in any one of claims 1-2, and a turbine (2) arranged in series, wherein at least one staged oxygen supply combustor (1) is provided.
4. A method of staged oxygen supply combustion for a gas turbine using the gas turbine according to claim 3, the method comprising:
calculating the maximum oxygen receiving amount of a main combustion area (15) according to the limit temperature of the main combustion area (15) of the gas turbine staged oxygen supply combustion chamber (1);
carbon dioxide is compressed by a gas compressor (7) and then is used as a working medium to be sent into a working medium gas channel formed between a combustion chamber outer sleeve and a flame tube (11), so that the carbon dioxide respectively enters a main combustion area (15), a secondary combustion area (16) and a mixing area (17) of a staged oxygen supply combustion chamber (1) through a main nozzle (12), a secondary carbon dioxide nozzle (132) and a mixing hole (14) to respectively form primary carbon dioxide, secondary carbon dioxide and tertiary carbon dioxide injection;
feeding a proper amount of fuel into a main combustion zone (15) through a main nozzle (12) of a staged oxygen supply combustion chamber (1) of a gas turbine;
setting the chemical equivalence ratio phi of the fuel and the total oxygen amount to be more than or equal to 0.9 and less than or equal to 1, calculating the total oxygen flow according to the chemical equivalence ratio, and comparing the total oxygen flow with the maximum oxygen receiving amount of the main combustion area (15);
when the total oxygen flow is less than or equal to the maximum oxygen content of the main combustion area (15), the oxygen is sprayed into the main combustion area (15) through the main nozzle (12); fuel, oxygen and carbon dioxide entering through the main nozzle (12) are mixed and the fuel is ignited, and the fuel and oxygen are formed in the main combustion zone (15) with a phi of 0.9 ≤ phiPZLean combustion of less than or equal to 1 to generate high-temperature fuel gas; mixing high-temperature fuel gas from the main combustion area (15) with secondary carbon dioxide introduced through a secondary nozzle (13) to form high-temperature flue gas;
when the total oxygen flow is larger than the maximum oxygen content of the main combustion area (15), oxygen enters the main combustion area (15) and the secondary combustion area (16) through the main nozzle (12) and the secondary oxygen nozzle (132) respectively to form primary oxygen supply and secondary oxygen supply; the primary oxygen quantity entering the main combustion area (15) through the main nozzle (12) is the maximum oxygen receiving quantity of the main combustion area; mixing fuel, oxygen and carbon dioxide entering through the main nozzle (12) and igniting the fuel, and enabling the fuel and the oxygen to form rich combustion in the main combustion area (15) to generate high-temperature fuel gas; mixing high-temperature fuel gas from the main combustion zone (15) with secondary oxygen and secondary carbon dioxide introduced through the secondary nozzle (13) in the secondary combustion zone (16) and enabling incomplete combustion in the high-temperature fuel gas to be completely combusted to generate high-temperature flue gas;
three-stage carbon dioxide is sprayed through the mixing holes (14) and is mixed with high-temperature flue gas from the secondary combustion area (16) to reduce the temperature of the high-temperature flue gas, and the high-temperature flue gas enters the turbine (2) to do work; the temperature of the flue gas is reduced to form waste gas after the flue gas works through the turbine (2), and the main components of the waste gas are carbon dioxide and water vapor;
the waste gas is separated to respectively obtain dry flue gas and condensed water which take carbon dioxide as main components, part of the dry flue gas is used as recycle gas, is mixed and regulated, then is sent into a gas compressor (7) to be compressed and boosted, and is used as a working medium to be sent into a working medium gas channel formed between a combustion chamber outer sleeve and a flame tube (11).
5. The staged oxygen supply combustion method for a gas turbine according to claim 4, wherein the gas turbine further comprises a condenser (4), a separation valve (5) and a mixing valve (6), and a carbon dioxide storage tank connected to the mixing valve (6), the method further comprising:
waste gas enters a condenser (4) to recover waste heat, and enters a separation valve (5) to carry out steam-water separation, and gas with carbon dioxide as a main component is separated from water to obtain dry flue gas; and a part of the separated dry flue gas is used as recycle gas, enters a mixing valve (6), enters an air compressor (7) after the flow is regulated by a carbon dioxide storage tank, is compressed and raised in pressure, and is used as a working medium to be sent into a working medium gas channel formed between the outer sleeve of the combustion chamber and the flame tube (11).
6. The combustion method of the gas turbine staged oxygen supply for the combustion as claimed in claim 4 or 5, wherein the carbon dioxide enters the main combustion zone (15), the secondary combustion zone (16) and the blending zone (17) of the staged oxygen supply combustion chamber (1) through the main nozzle (12), the secondary carbon dioxide nozzle (132) and the blending hole (14), and the injection ratio of the formed primary carbon dioxide, secondary carbon dioxide and tertiary carbon dioxide is (50-60): 5-20): 20-45.
7. The gas turbine staged oxygen supply combustion method as claimed in claim 4 or 5, wherein the staged oxygen supply combustion method further comprises a staged adjustment method, the staged adjustment method comprising:
the load of the gas turbine is gradually increased, so that the fuel supplied to a main combustion area (15) through a main nozzle (12) of the staged oxygen supply combustion chamber (1) is gradually increased;
adjusting the total oxygen flow according to the stoichiometric ratio phi of the fuel to the oxygen, and adjusting the oxygen to be sprayed into a main combustion area (15) through a main nozzle (12) of a staged oxygen supply combustion chamber (1) when the total oxygen flow is less than or equal to the maximum oxygen receiving amount of the main combustion area so as to ensure that the primary oxygen ratio is 100%; and when the oxygen flow rate is continuously increased and is larger than the maximum oxygen storage amount of the main combustion area, part of the oxygen exceeding the maximum oxygen storage amount of the main combustion area is sprayed into the secondary combustion area (16) as secondary oxygen through a secondary oxygen nozzle (132).
8. The gas turbine staged oxygen supply combustion method as set forth in claim 7, wherein said staged adjusting method further comprises:
the load of the gas turbine is gradually reduced, so that the fuel supplied to a main combustion area (15) through a main nozzle (12) of the staged oxygen supply combustion chamber (1) is gradually reduced;
adjusting the total oxygen flow according to the stoichiometric ratio phi of the fuel to the oxygen, and when the total oxygen flow is larger than the maximum oxygen receiving amount of the main combustion area, sequentially adjusting the total oxygen flow according to the sequence of adjusting the secondary oxygen supply first and then adjusting the primary oxygen supply; when the total oxygen flow is less than or equal to the maximum oxygen receiving amount of the main combustion area, the primary oxygen amount of the main combustion area is reduced.
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| CN101235752A (en) * | 2006-11-07 | 2008-08-06 | 通用电气公司 | Power plants that utilize gas turbines for power generation and processes for lowering co2 emissions |
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