CN116221781A - Ammonia oxygen-enriched staged combustion chamber and combustion method - Google Patents

Ammonia oxygen-enriched staged combustion chamber and combustion method Download PDF

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Publication number
CN116221781A
CN116221781A CN202310301067.8A CN202310301067A CN116221781A CN 116221781 A CN116221781 A CN 116221781A CN 202310301067 A CN202310301067 A CN 202310301067A CN 116221781 A CN116221781 A CN 116221781A
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combustion
oxygen
fuel
main
amount
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李昭兴
张海
张扬
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Tsinghua University
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Tsinghua University
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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/58—Cyclone or vortex type combustion chambers
    • 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 an ammonia oxygen-enriched staged combustion chamber and a combustion method. According to the invention, the combustion chamber is divided into the main combustion area and the secondary combustion area, oxygen is supplied through the main combustion area at one stage, air is supplied through the main combustion area and the secondary combustion area at two stages, so that the ammonia burning speed is improved, the combustion stability is improved, and the NOx emission in a wide load range is reduced through adjustable rich combustion-lean combustion staged combustion, so that the operating condition range of the oxygen-enriched combustion chamber is widened. In addition, the oxygen-enriched combustion condition is provided only in the main combustion area of the combustion chamber, so that the effect of reducing NOx, which is similar to that of oxygen enrichment in all air, can be achieved, and the oxygen consumption is reduced.

Description

Ammonia oxygen-enriched staged combustion chamber and combustion method
Technical Field
The invention relates to the technical field of ammonia combustion, in particular to an ammonia oxygen-enriched staged combustion chamber and a combustion method.
Background
Due to the recent need to reduce carbon dioxide emissions, the use of ammonia as a fuel to replace fossil fuels that were originally widely used in gas turbine plants has received attention. The combustion of ammonia does not produce carbon dioxide, and meanwhile, the volume energy density of ammonia is higher than that of hydrogen, the boiling point of ammonia is far higher than that of hydrogen and natural gas, the storage and transportation difficulty is low, the existing industrial production and transportation infrastructure is mature, and the wide use of ammonia fuel can obviously reduce carbon dioxide emission. However, ammonia fuel combustion has problems of low combustion speed and high NOx pollutant emissions. Under the same working condition, the combustion speed of ammonia is only one fifth of the combustion speed of natural gas, so that flame of ammonia is more easy to extinguish, and the combustion intensity of a combustion chamber is lower. In addition, ammonia is fuel nitrogen, is easily oxidized into NOx during combustion, and the maximum amount of NOx generated by direct combustion can reach thousands ppm, which is far higher than the general environmental protection requirement, and can not be directly discharged.
The oxygen-enriched combustion can effectively improve the combustion speed of ammonia, and the rich-lean staged combustion chamber can effectively reduce the NOx emission of ammonia combustion, and the combination of the two can simultaneously improve the problems of low combustion speed of ammonia and high NOx emission. However, staged combustion only within a specific optimum equivalence ratio range can ensure significant NOx reduction. The change in load or oxygen enrichment of the combustion chamber will change the optimum equivalence ratio for staged combustion, the change in ammonia fuel input or air oxygen will deviate from the optimum equivalence ratio, and significant NOx emissions will result. In addition, in the conventional combustion chamber, the air required for combustion and the air mixed with the temperature reduction are supplied by the same compressor, and if the oxygen-enriched air is used completely, the cost will be high.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems in the related art to some extent.
For this purpose, the embodiment of the invention provides an ammonia oxygen-enriched staged combustion chamber and a combustion method.
In one aspect, the invention provides an ammonia oxygen-enriched staged combustion chamber comprising:
a combustion chamber housing;
the flame tube is sleeved in the combustion chamber shell, an air channel is formed between the combustion chamber shell and the flame tube, and the inner area of the flame tube is divided into a main combustion area and a secondary combustion area positioned at the downstream of the main combustion area;
the main nozzle is arranged at the inlet end of the main combustion area and comprises a fuel channel, an oxygen channel and a main air channel, the main air channel is communicated with the air channel, an oxygen flow control valve is arranged on an oxygen channel pipeline, and a fuel flowmeter is arranged on the fuel channel pipeline;
and the secondary nozzles are symmetrically arranged on the wall surface of the secondary combustion zone.
In some embodiments, one end of the oxygen channel is connected to an oxygen source and the other end of the oxygen channel extends into the primary air channel.
In some embodiments, the oxygen source is separated by an air separator.
In some embodiments, the fuel passage is located at a position intermediate the primary nozzles.
In some embodiments, the front end of the main nozzle is provided with a cyclone, the inner side of the cyclone is fixedly connected to the outer wall of the fuel channel, and the outer side of the cyclone is fixedly connected to the inner wall of the main air channel.
In some embodiments, an ignition device is disposed at the forward end of the primary combustion zone.
On the other hand, the invention provides a combustion method, and the ammonia oxygen-enriched staged combustion chamber comprises the following steps:
according to the pressure of the combustion chamber and the average temperature of the main combustion area, calculating to obtain the optimal equivalence ratio for enabling NOx to be discharged to the lowest under different oxygen concentrations of the main combustion area;
according to the relation of the oxygen amount, the air amount and the oxygen concentration of the main combustion area and the optimal equivalence ratio, calculating to obtain the optimal fuel amount-oxygen amount relation of the lowest NOx emission;
when the combustion power is adjusted, the required oxygen amount is calculated according to the relation between the fuel amount and the optimal fuel amount and oxygen amount.
In some embodiments, the pressure of the combustion chamber is the average pressure before the outlet after the inlet of the combustion chamber, and the average temperature of the main combustion zone is the average temperature of the high temperature fuel gas after ignition in the main combustion zone of the combustion chamber.
In some embodiments, as the combustion load increases gradually, the amount of fuel supplied to the primary combustion zone through the primary nozzles increases gradually, increasing the oxygen flow rate according to the fuel amount and the optimal fuel amount-oxygen amount relationship.
In some embodiments, as the combustion load gradually decreases, the fuel supplied to the primary combustion zone through the primary nozzles gradually decreases, decreasing the oxygen flow rate according to the fuel amount and the optimal fuel amount-oxygen amount relationship until the oxygen flow rate decreases to zero; when the oxygen flow rate decreases to zero, if the load of combustion further decreases, the air flow rate is controlled to decrease in proportion to the fuel amount until the shutdown.
Compared with the prior art, the invention has the beneficial effects that:
all of the fuel and oxygen of the present invention is supplied to the primary combustion zone from the primary nozzles of the primary stage, with oxygen being blended with only the primary air and not with the secondary air. The fuel is subjected to rich combustion in a main combustion area in a specific equivalent ratio, so that the generation of NOx is reduced, and the residual combustible gas and secondary air are mixed for combustion and are burnt out. The invention has the advantages of low NOx emission, low oxygen consumption and the like in wider ammonia combustion.
According to the invention, the combustion chamber is divided into the main combustion area and the secondary combustion area, oxygen is supplied through the main combustion area at one stage, air is supplied through the main combustion area and the secondary combustion area at two stages, so that the ammonia burning speed is improved, the combustion stability is improved, and the NOx emission in a wide load range is reduced through adjustable rich combustion-lean combustion staged combustion, so that the operating condition range of the oxygen-enriched combustion chamber is widened. In addition, only the oxygen-enriched combustion condition is provided in the main combustion area of the combustion chamber, so that the effect of reducing NOx, which is similar to that of oxygen enrichment in all air, can be achieved, and the oxygen consumption is reduced.
Drawings
The foregoing and/or additional aspects and advantages of the invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings, in which:
FIG. 1 is a schematic diagram of an ammonia-rich staged combustor of the present invention;
FIG. 2 is a schematic view of a gas turbine engine according to the present invention;
reference numerals illustrate:
the burner comprises a combustion chamber shell 1, a flame tube 2, a main nozzle 3, a secondary nozzle 4, a fuel channel 5, an oxygen channel 6, an oxygen flow control valve 7, a fuel flowmeter 8, a cyclone 9, a main combustion zone 10, a secondary combustion zone 11, an air channel 12, a main air channel 13, an ammonia oxygen-enriched staged combustion chamber 14, a compressor 15, an air flow regulating device 16, a turbine 17, a generator 18, a connecting shaft 19 and an air separator 20.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
The ammonia oxygen-enriched staged combustion chamber and the combustion method according to the embodiments of the present invention are described below with reference to the accompanying drawings.
As shown in fig. 1-2, the ammonia-rich staged combustion chamber of the present invention includes a combustion chamber housing 1, a flame tube 2, a primary nozzle 3, and a secondary nozzle 4. The staged oxygen-enriched combustor can be used in an oxygen-enriched gas turbine that burns pure ammonia or a fuel containing ammonia as a main component.
The combustion chamber shell 1 is sleeved outside the flame tube 2, the flame tube 2 is of a cylindrical structure with one end in a circular arc shrinkage shape, and an air channel 12 is formed between the combustion chamber shell 1 and the flame tube 2. The inner area of the flame tube 2 is divided into a main combustion area 10 and a secondary combustion area 11 positioned downstream of the main combustion area 10, and air flows through the main combustion area 10 and the secondary combustion area 11 after entering through the inlet of the flame tube 2. The main combustion zone 10 is arranged in front of the secondary combustion zone 11 according to the direction of the air flow entering and exiting the flame tube 2 as the front-back direction, and an ignition device is arranged at the front end of the main combustion zone 10.
The main nozzle 3 is arranged at the inlet end of the main combustion zone 10, i.e. the main nozzle 3 is arranged at the front end position of the main combustion zone 10. The main nozzle 3 comprises a fuel channel 5, an oxygen channel 6 and a main air channel 13, wherein the main air channel 13 is communicated with an air channel 12 formed between the combustion chamber shell 1 and the flame tube 2, the fuel channel 5 is positioned in the middle of the main nozzle 3, one end of the oxygen channel 6 is connected with an air separator 20, and the other end of the oxygen channel 6 extends into the main air channel 13. In operation, oxygen injected through the oxygen passage 6 is mixed with air injected through the main air passage 13 and then with fuel injected through the fuel passage 5. The oxygen required for the ammonia-enriched staged combustion chamber is separated by an air separator 20, it being understood that in some embodiments the source of oxygen may also be an oxygen cylinder, an oxygen tank, or the like.
The front end of the main nozzle 3 is provided with a swirler 9, the swirler 9 is arranged at the front part of the main nozzle 3 by taking the fuel channel 5 as a central shaft, the swirler 9 is used for carrying out swirling mixing on oxygen injected through the oxygen channel 6 and air injected through the main air channel 13, the inner side of the swirler 9 is fixedly connected to the outer wall of the fuel channel 5, and the outer side of the swirler 9 is fixedly connected to the inner wall of the main air channel 13.
An oxygen flow control valve 7 is arranged on the pipeline of the oxygen channel 6, and the oxygen flow control valve 7 is used for regulating and controlling the oxygen flow through the oxygen channel 6; a fuel flow meter 8 is provided in the fuel passage 5 line, and the fuel flow meter 8 is used to meter the amount of fuel flowing through the fuel passage 5.
The secondary nozzles 4 are symmetrically arranged on the wall surface of the secondary combustion zone 11, i.e. the secondary nozzles 4 are uniformly arranged around the secondary combustion zone 11, and the number of the secondary nozzles 4 is at least two.
In the ammonia oxygen-enriched staged combustion chamber shown in fig. 1, air flows reversely through the secondary nozzle 4 through an air passage 12 formed between the combustion chamber shell 1 and the flame tube 2, and a part of the air flows through a main air passage 13 after being split to form primary air. It will be appreciated that in other embodiments, where the air is split upstream adjacent the primary nozzle 3, it may be desirable to split the air to form primary air prior to mixing the primary air with oxygen. Meanwhile, the oxygen used in the ammonia-rich staged combustion chamber may be pure oxygen (e.g., O 2 Concentration greater than 99%) or oxygen enriched air containing a significant amount of other components (e.g., O) 2 The concentration is more than 50 percent), and when oxygen-enriched air is used, the equivalent ratio is calculated according to the amount of oxygen actually contained.
As shown in fig. 2, the gas turbine of the present invention comprises a compressor 15, an ammonia-rich staged combustion chamber 14 and a turbine 17 which are sequentially connected upstream and downstream, wherein at least one ammonia-rich staged combustion chamber 14 is arranged. An air flow regulator 16 is disposed at the air inlet end of the compressor 15, and the air flow regulator 16 is used for regulating the air amount entering the compressor 15. Downstream of the turbine 17 is connected a generator 18 via a connecting shaft 19. The gas turbine further comprises a controller, to which the oxygen flow control valve 7, the fuel flow meter 8 and the air flow regulating device 16 are electrically connected.
When the gas turbine is used for graded oxygen-enriched combustion, air is compressed by the gas compressor 15 and then is taken as an oxidant and a working medium to be sent into the air channel 12 formed between the combustion chamber shell 1 and the flame tube 2, so that the air enters the main combustion zone 10 and the secondary combustion zone 11 of the graded oxygen-enriched combustion chamber through the main nozzle 3 and the secondary nozzle 4 respectively to form primary air and secondary air for spraying. The ratio of the primary air to the secondary air is (20-35): (80-65), and in actual situations, the ratio of the primary air to the secondary air can be adaptively adjusted according to the power range, the highest temperature tolerance of equipment and other conditions. In addition, it is understood that the air injected through the primary nozzles 3 is primary air, i.e., primary air, and the air injected through the secondary nozzles 4 is secondary air, i.e., secondary air.
An amount of fuel corresponding to the gas turbine load is fed all through the main nozzles 3 of the staged oxyfuel combustor of the gas turbine into the main combustion zone 10. All oxygen is sprayed into the main combustion zone 10 through the main nozzle 3 of the graded oxygen-enriched combustion chamber, fuel, oxygen and air entering through the main nozzle 3 are mixed, the fuel is ignited, and the fuel and the mixed oxygen-enriched air form rich combustion in the main combustion zone 10 to generate high-temperature fuel gas. The hot gas from the primary combustion zone 10 is mixed with secondary air introduced through the secondary nozzle 4, and the unburned components (e.g., H 2 Etc.) is completely burned to form high temperature flue gas. The high-temperature flue gas is diluted to a certain temperature, enters the turbine 17 to do work, and drives the generator 18 to generate electricity through the connecting shaft 19. The high temperature flue gas is cooled after the turbine 17 performs work, and is discharged out of the turbine 17 as waste gas.
A method of combustion in a gas turbine comprising the steps of: according to the pressure of the combustion chamber and the average temperature of the main combustion zone, calculating to obtain the optimal equivalence ratio for minimizing the NOx emission under different oxygen concentrations of the main combustion zone 10; according to the relation of the oxygen amount, the air amount and the oxygen concentration-optimal equivalence ratio of the main combustion zone 10, calculating to obtain the optimal fuel amount-oxygen amount relation of the lowest NOx emission; when the combustion power is adjusted, the required oxygen amount is calculated according to the relation between the fuel amount and the optimal fuel amount and oxygen amount. The pressure of the combustion chamber is the average pressure before the outlet of the combustion chamber after the inlet, and the average temperature of the main combustion area is the average temperature of high-temperature fuel gas after ignition in the main combustion area of the combustion chamber.
When the load of the gas turbine gradually increases, the amount of fuel supplied to the main combustion zone 10 through the main nozzle 3 gradually increases, increasing the oxygen flow rate according to the fuel amount and the optimum fuel amount-oxygen amount relationship; when the load of the gas turbine is gradually reduced, the fuel supplied to the main combustion zone 10 through the main nozzle 3 is gradually reduced, and the oxygen flow rate is reduced according to the relation between the fuel amount and the optimal fuel amount-oxygen amount until the oxygen flow rate is reduced to zero; when the oxygen flow rate decreases to zero, if the load of the gas turbine is further reduced, the air flow rate is controlled by the flow rate adjusting means to decrease in proportion to the fuel amount until shutdown.
Specifically, the gas turbine of the present invention is operated under oxygen-enriched combustion conditions in which combustion is performed in an oxygen-containing gas having an oxygen content higher than that of air (20.947%). At this time, there are three combustion states, i.e., rich combustion (Φ > 1), equivalent combustion (Φ=1), and lean combustion (Φ < 1), analyzed in terms of the stoichiometric ratio of fuel to oxygen (Φ). Equivalent combustion is to burn fuel and oxygen according to the ratio of the chemical equivalent ratio of complete combustion. The combustion state of the fuel with respect to the oxygen is rich combustion, whereas the combustion state of the fuel with respect to the oxygen deficiency is lean combustion.
When the gas turbine load changes, the oxygen amount change needs to be adjusted according to the change in fuel amount to ensure that the equivalence ratio of the main combustion zone 10 is optimal. Reducing NOx emissions due to staged combustion requires controlling the primary combustion zone 10 to an optimal equivalence ratio φ op Under the condition that the optimal equivalence ratio is approximately proportional to the oxygen concentration of the oxidant (mixture of primary air and oxygen) in the primary combustion zone 10, the oxygen concentration is determined by the ratio of the amount of oxygen to the amount of primary air, thereby
Figure BDA0004145106250000051
Wherein k is 1 The unit is 1 for the proportionality coefficient; phi (phi) op Is the optimal equivalence ratio, and the unit is 1; phi (phi) 0 For the reference equivalence ratio, the unit is 1; />
Figure BDA0004145106250000052
Is oxygen flow, unit is Nm 3 /s；/>
Figure BDA0004145106250000053
Is the main air flow rate in Nm 3 /s。k 1 And phi 0 Related to the pressure of the combustion chamber and the average temperature of the gas after combustion in the main combustion zone, and is generally k 1 About 2, phi 0 1.1-1.3, the fuel is also related to the proportion of ammonia in the fuel when pure ammonia is not used. After the optimal equivalence ratio-oxygen amount relation is obtained, the fuel amount-oxygen amount relation ensuring low NOx emission, namely +.>
Figure BDA0004145106250000061
Figure BDA0004145106250000062
Wherein Q is f Fuel flow in kg/s; k (k) 2 The fuel factor for mass flow and stoichiometric conversion is in kg/Nm 3 ；Ω 0 The oxygen concentration in the air was 21%. When the combustion power needs to be adjusted, the required oxygen amount is calculated according to the fuel amount and the optimal fuel amount-oxygen amount relation.
When the load of the gas turbine is gradually increased, the amount of fuel supplied to the main combustion zone 10 through the main nozzle 3 of the staged oxyfuel combustor is gradually increased, and the oxygen-enriched air flow is adjusted according to the fuel amount and the optimal relation until the maximum load is reached, at which time the fuel amount and the oxygen amount are maximum, and the temperature of the combustor is the highest. The main combustion zone 10 has higher oxygen concentration and lower optimal NOx at high load, and achieves better NOx reduction effect than non-oxygen-enriched staged combustion. During a specific adjustment, as the gas turbine load increases gradually, the measured value of the fuel flow meter 8 increases, and the fuel flow meter 8 transmits test data to the controller, which controls the oxygen flow control valve 7 to increase the oxygen amount according to the optimum fuel amount-oxygen amount relationship.
As the gas turbine load gradually decreases, the amount of fuel supplied to the main combustion zone 10 through the main nozzle 3 of the staged oxyfuel combustor gradually decreases; and reducing the oxygen flow according to the fuel quantity and the optimal fuel quantity-oxygen quantity relation until oxygen is not required to be introduced. When the oxygen amount decreases to zero, if the load is further reduced, the air amount is adjusted by the air flow control means of the compressor 15 so that the air flow is reduced in proportion to the fuel amount until the shutdown. During the specific adjustment, as the gas turbine load gradually decreases, the measured value of the fuel flow meter 8 decreases, and the fuel flow meter 8 transmits test data to the controller, which controls the oxygen flow control valve 7 to decrease the oxygen amount according to the optimum fuel amount-oxygen amount relationship until the oxygen amount is zero. When the amount of oxygen decreases to zero, if it is necessary to further decrease the load of the gas turbine, the air flow control device is controlled by the controller to decrease the air flow so that the air flow decreases in proportion to the amount of fuel until shutdown.
The air flow rate is typically unchanged when the gas turbine operating load is not too low (e.g., greater than 30% load). At this time, the oxygen concentration in the main combustion zone 10 decreases with load, and the effect of reducing NOx emissions is slightly deteriorated. When the load is reduced even lower (e.g. less than 30%), the main fuel equivalence ratio will deviate from optimum and NOx will increase substantially because the required working fluid has been reduced significantly, if only fuel is reduced without a corresponding reduction in air flow, and therefore the air flow control means of the compressor 15 need to be turned off, reducing air flow until shut down. In the case where the air flow rate control device of the compressor 15 adjusts the air flow rate in the full load range, the air amount may affect the above-described optimum fuel amount-oxygen amount relationship, and at this time, a new optimum fuel amount-oxygen amount relationship may be calculated from the changed air amount. When the air amount increases or decreases together with the oxygen amount according to the fuel amount and the oxygen content of the main combustion zone 10 is kept high, a better low NOx emission effect in a wide load range can be obtained.
The invention improves the combustion speed and the combustion stability of the ammonia-burning gas turbine by supplying oxygen through the primary combustion zone 10 at one stage. Meanwhile, through the rich combustion-lean combustion staged combustion with adjustable oxygen content, lower NOx emission in a wide load range is ensured, and NOx emission in a high load is reduced, so that the operating condition range of the oxygen-enriched combustion gas turbine is widened. In addition, by providing oxygen-enriched combustion conditions only in the main combustion zone 10 of the combustor, a NOx reduction effect similar to that of oxygen enrichment in all air can be achieved, and oxygen consumption is reduced.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms may be directed to different embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: many changes, modifications, substitutions and variations may be made to the embodiments without departing from the spirit and principles of the invention, the scope of which is defined by the claims and their equivalents.

Claims (10)

1. An ammonia-rich staged combustion chamber comprising:
a combustion chamber housing;
the flame tube is sleeved in the combustion chamber shell, an air channel is formed between the combustion chamber shell and the flame tube, and the inner area of the flame tube is divided into a main combustion area and a secondary combustion area positioned at the downstream of the main combustion area;
the main nozzle is arranged at the inlet end of the main combustion area and comprises a fuel channel, an oxygen channel and a main air channel, the main air channel is communicated with the air channel, an oxygen flow control valve is arranged on an oxygen channel pipeline, and a fuel flowmeter is arranged on the fuel channel pipeline;
and the secondary nozzles are symmetrically arranged on the wall surface of the secondary combustion zone.
2. The ammonia-rich staged combustion chamber of claim 1, wherein one end of the oxygen passage is connected to an oxygen source and the other end of the oxygen passage extends into the primary air passage.
3. The ammonia-rich staged combustor as defined in claim 2, wherein the oxygen source is separated by an air separator.
4. The ammonia-rich staged combustor as defined in claim 1, wherein the fuel passage is centrally located in the primary nozzle.
5. The ammonia-rich staged combustion chamber as defined in claim 1, wherein a swirler is disposed at the front end of the main nozzle, the inner side of the swirler is fixedly connected to the outer wall of the fuel passage, and the outer side of the swirler is fixedly connected to the inner wall of the main air passage.
6. The ammonia-rich staged combustor as defined in claim 1, wherein an ignition device is disposed at the forward end of the primary combustion zone.
7. A combustion method characterized by using the ammonia-rich staged combustion chamber as defined in any one of claims 1-6, comprising the steps of:
according to the pressure of the combustion chamber and the average temperature of the main combustion area, calculating to obtain the optimal equivalence ratio for enabling NOx to be discharged to the lowest under different oxygen concentrations of the main combustion area;
according to the relation of the oxygen amount, the air amount and the oxygen concentration of the main combustion area and the optimal equivalence ratio, calculating to obtain the optimal fuel amount-oxygen amount relation of the lowest NOx emission;
when the combustion power is adjusted, the required oxygen amount is calculated according to the relation between the fuel amount and the optimal fuel amount and oxygen amount.
8. The combustion method as set forth in claim 7, wherein the pressure of the combustion chamber is an average pressure before the inlet and the outlet of the combustion chamber, and the average temperature of the main combustion zone is an average temperature of high-temperature fuel gas after ignition in the main combustion zone of the combustion chamber.
9. The combustion method as set forth in claim 7, wherein the amount of fuel supplied to the main combustion zone through the main nozzle is gradually increased as the combustion load is gradually increased, and the oxygen flow rate is increased according to the fuel amount and the optimum fuel amount-oxygen amount relationship.
10. The combustion method as claimed in claim 9, wherein as the combustion load gradually decreases, the fuel supplied to the main combustion zone through the main nozzle gradually decreases, and the oxygen flow rate is decreased according to the fuel amount and the optimum fuel amount-oxygen amount relationship until the oxygen flow rate decreases to zero; when the oxygen flow rate decreases to zero, if the load of combustion further decreases, the air flow rate is controlled to decrease in proportion to the fuel amount until the shutdown.
CN202310301067.8A 2023-03-24 2023-03-24 Ammonia oxygen-enriched staged combustion chamber and combustion method Pending CN116221781A (en)

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