CN115355536A - Oxyhydrogen micro-mixed combustion device suitable for gas turbine and use method thereof - Google Patents
Oxyhydrogen micro-mixed combustion device suitable for gas turbine and use method thereof Download PDFInfo
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 119
- 238000000034 method Methods 0.000 title claims abstract description 12
- 239000000446 fuel Substances 0.000 claims abstract description 55
- 239000007800 oxidant agent Substances 0.000 claims abstract description 48
- 230000001590 oxidative effect Effects 0.000 claims abstract description 48
- 239000003085 diluting agent Substances 0.000 claims abstract description 41
- 238000002156 mixing Methods 0.000 claims abstract description 36
- 238000005496 tempering Methods 0.000 claims abstract description 8
- 239000000203 mixture Substances 0.000 claims abstract description 7
- 239000007795 chemical reaction product Substances 0.000 claims abstract description 6
- 230000000171 quenching effect Effects 0.000 claims abstract description 6
- 238000001816 cooling Methods 0.000 claims abstract description 5
- 230000009471 action Effects 0.000 claims abstract description 4
- 239000007789 gas Substances 0.000 claims description 37
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 20
- 239000001257 hydrogen Substances 0.000 claims description 20
- 229910052739 hydrogen Inorganic materials 0.000 claims description 20
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 16
- 238000002679 ablation Methods 0.000 claims description 8
- 230000002093 peripheral effect Effects 0.000 claims description 7
- 239000000376 reactant Substances 0.000 claims description 7
- 239000000047 product Substances 0.000 claims description 6
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 230000001276 controlling effect Effects 0.000 claims description 3
- 238000009792 diffusion process Methods 0.000 claims description 3
- 230000014759 maintenance of location Effects 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 238000007865 diluting Methods 0.000 claims description 2
- 230000002035 prolonged effect Effects 0.000 claims description 2
- 230000002708 enhancing effect Effects 0.000 claims 1
- 238000010791 quenching Methods 0.000 abstract description 3
- 239000003570 air Substances 0.000 description 26
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 9
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 7
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 239000001301 oxygen Substances 0.000 description 4
- 229910052760 oxygen Inorganic materials 0.000 description 4
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910021529 ammonia Inorganic materials 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000003345 natural gas Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005868 electrolysis reaction Methods 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000035484 reaction time Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Images
Classifications
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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
- F23R3/28—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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
-
- 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
-
- 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 oxyhydrogen micro-mixed combustion device suitable for a gas turbine and a using method thereof, and belongs to the field of micro-mixed combustion. The invention includes a combustion chamber and an array of nozzles. The single nozzle mainly comprises an air inlet cavity and a rotational flow generating device. The air inlet cavity comprises an oxidant inlet, a diluent inlet, an air inlet convergence section, a circumferential seam section and a mixing section. The combustion chamber is of a cylindrical cavity structure. According to the invention, the diluent inlet is additionally arranged at the central axis of the nozzle, the introduction of the diluent can dilute reaction products and control the flame temperature, and after the diluent is introduced from the nozzle array, a plurality of beams of diluent are radially diffused in the combustion chamber to extrude a fuel/oxidant mixture, so that the fuel/oxidant mixture can be more fully reacted, and the combustion efficiency is improved. In addition, the invention can greatly reduce the tempering risk by respectively introducing fuel and oxidant from different inlets, isolating the inner wall surface of the combustion chamber from the flame layer and simultaneously assisting the quenching and cooling action of the wall surface of the circular seam section.
Description
Technical Field
The invention belongs to the field of micro-mixed combustion, and particularly relates to an oxyhydrogen micro-mixed combustion device suitable for a gas turbine.
Background
The current gas turbine power generation and power field faces the transformation challenge of low carbon and even zero carbon emission, and development of flexible fuel blending combustion technologies such as hydrogen-ammonia and hydrogen-rich synthetic gas is expected to greatly improve the working interval of a gas turbine. In addition, oxygen-enriched or even pure oxygen in industrial production or renewable energy electrolysis hydrogen production is used as an oxidant, so that the generation of nitrogen oxides can be fundamentally avoided, and the energy conservation and emission reduction are further promoted.
On one hand, however, hydrogen is high in burning speed and easy to temper, and the ablation risk is increased due to the high flame temperature, the dry premixing rotational flow stable burning method adopted by the existing natural gas combustion engine cannot adapt to pure hydrogen fuel, and the problem becomes more serious under the condition of pure oxygen; on the other hand, the ammonia gas has low burning rate and narrow combustible limit, the stability of premixed flame is poor, and high nitrogen oxide emission is easy to generate. Therefore, the existing swirl lean-burn premixing technology cannot meet the combustion requirements of low-carbon fuels such as hydrogen and ammonia, and a novel combustion organization mode needs to be developed to improve the adaptability and the operation range of the gas turbine.
The micro-mixed combustion is a novel combustion technology developed for hydrogen-rich fuel, air and fuel are premixed and reacted completely in a micro space scale to reduce the emission of nitrogen oxides, and the tempering resistance is improved by utilizing the quenching effect of a small pipe diameter. However, due to the lack of a backflow zone, the micro-mixing combustor has poor combustion stability under a low load condition, thermoacoustic oscillation may be induced, and currently adopted on-duty flame and axial staging technologies are not enough to eliminate the risk of combustion instability under a condition of higher oxygen concentration. Compared with the combustion of natural gas or hydrogen in the air, the combustion speed of oxyhydrogen combustion is greatly increased, the chemical reaction time is quickly shortened, and the existing micro-mixed combustion mode is difficult to meet the requirement of stable combustion.
Disclosure of Invention
The method aims to solve the problems of mixing uniformity and combustion stability in the pure hydrogen and pure oxygen micro-mixing combustion chamber, wall surface high-temperature flame ablation and easy tempering. The invention mainly aims to provide an oxyhydrogen micro-mixing combustion device suitable for a gas turbine and a use method thereof, which can improve the mixing uniformity in a micro-mixing combustion chamber, further improve the combustion sufficiency and the combustion stability of pure hydrogen and pure oxygen, and reduce the ablation of high-temperature flame on the wall surface. In addition, the invention can greatly reduce the tempering risk by respectively introducing fuel and oxidant from different inlets and simultaneously assisting the quenching and cooling effect of the wall surface of the circular seam section.
The purpose of the invention is realized by the following technical scheme:
the invention discloses an oxyhydrogen micro-mixing combustion device suitable for a gas turbine, which comprises a combustion chamber and an array nozzle.
The combustion chamber is of a cylindrical cavity structure.
The array nozzle is composed of a central nozzle and a peripheral nozzle. The central nozzle and the surrounding nozzles are identical in structure. The central nozzles are one in number, the central axes of the central nozzles coincide with the central axis of the combustion chamber, the central nozzles are arranged along the axial direction of the combustion chamber and are arranged in the center of the front end wall surface of the combustion chamber. The peripheral nozzles are at least two and symmetrical about the central nozzle. The central nozzle and the surrounding nozzles form a nozzle array of a micro-hybrid combustion device, and fuel, oxidant, and diluent are axially injected into the combustion chamber through the array nozzles. The central nozzle and the surrounding nozzles are identical in structure.
The single nozzle mainly comprises an air inlet cavity and a rotational flow generating device. The air inlet cavity comprises an oxidant inlet, a diluent inlet, an air inlet convergence section, a circumferential seam section and a mixing section. The air inlet cavity is of a cylindrical cavity structure, openings are formed in the axial direction and the cylindrical wall surface, the axial openings are diluent inlets, and diluent is injected along a channel of the central axis of the air inlet cavity; the radial opening on the wall surface of the cylinder is an oxidant inlet, and the inner space of the cylinder is divided into three parts, namely an air inlet convergence section, a circular seam section and a mixing section from left to right in sequence along the axial direction according to the molded surface; at the axial opening, a central axis channel of the air inlet cavity extends to a mixing section of the inner space of the oxidant inlet, and an outer wall surface of the central axis channel and a small inner diameter wall surface of the inner space of the oxidant inlet form a circular seam section; the swirl generating device comprises a fuel inlet and a swirl. The center of the rotational flow generating device is of a hollow cylindrical structure and comprises a plurality of tangential fuel inlets and an outlet, the tangential fuel inlets are uniformly distributed along the circumference of the hollow cylinder, and the outlet is circular along the axial direction. The air inlet cavity, the rotational flow generating device and the combustion chamber are coaxially matched; the inner diameters of the mixing section and the rotational flow generating device are the same, and the outer diameter of a central axis channel of the air inlet cavity is slightly smaller than the first two so as to form a circular seam section.
The invention discloses a use method of an oxyhydrogen micro-mixed combustion device suitable for a gas turbine, which comprises the following steps:
the oxidant is introduced from a radial oxidant inlet, passes through an air inlet convergence section, enters a mixing section from an annular seam section, and is mixed with the diluent introduced from a central axial channel of the nozzle to form diluent/oxidant mixed gas introduced axially; the fuel is introduced from a tangential fuel inlet of the rotational flow generating device, is rapidly mixed with diluent/oxidant mixed gas which is axially introduced, and forms axial tangential rotational flow flame after being ignited; the diluent injected axially from the center of the nozzle enters the combustion chamber and then radially diffuses, so that the diluent is used for diluting reaction products and controlling flame temperature, and under the diffusion action of the diluent introduced from the adjacent nozzle, the fuel/oxidant mixture is extruded to the gap between the adjacent nozzles to react for a sufficient time. The diluent is injected axially through the center of the array nozzle, so that the mixing uniformity in the micro-mixing combustion chamber can be improved, the combustion sufficiency is further improved, the reaction temperature can be regulated and controlled, and the risk of high-temperature ablation of the wall surface is reduced.
Since the oxidant is introduced from the radial oxidant inlet and the fuel is introduced from the tangential fuel inlet of the swirl generating device, the risk of backfire can be reduced. But considering the extremely high burning speed of the pure hydrogen and pure oxygen, the annular seam section is further added, so that the wall surface cooling quenching effect is enhanced, the anti-tempering performance is improved, and the direct mixed combustion of the pure hydrogen and pure oxygen can be adapted.
The fuel at the tangential fuel inlet forms a rotational flow at the outlet of the rotational flow generating device, the internal stroke is longer, the fuel has longer residence time, the strong rotational flow is helpful for mixing the oxidant and the fuel, the fuel and the oxidant are rapidly mixed in the longer residence time, the fuel and the oxidant are spirally injected into the combustion chamber under the rotational flow effect, and axial tangential rotational flow flame is formed after the fuel is ignited.
The axial tangential swirl flame is of a three-layer flame structure, and the three-layer flame structure sequentially comprises from inside to outside: a combustion product layer consisting of reaction products formed by combustion; a flame layer; the reactant layer is formed by a layer of gas film surrounding the inner wall of the combustion chamber, the temperature of the gas film is low, and the inner wall surface of the combustion chamber is isolated from the flame layer, so that the inner wall surface of the combustion chamber is well cooled, the service life of the combustion chamber is effectively prolonged, the heat loss of the flame layer on the inner wall surface of the combustion chamber is reduced, and the combustion stability of flame is improved. In addition, when the tangential rotational flow enters air, a backflow area is formed in the combustion chamber, the temperature of combustion products in the backflow area is high, the retention time is long, a stable heat source is formed, and the flame stability of the combustion chamber can be effectively improved.
Has the advantages that:
1. the invention discloses an oxyhydrogen micro-mixing combustion device suitable for a gas turbine and a working method thereof.A diluent inlet is additionally arranged at the central axis of a nozzle, the introduction of the diluent can dilute reaction products and control the flame temperature, and after the diluent is introduced from a nozzle array, a plurality of beams of diluent are radially diffused in a combustion chamber to extrude a fuel/oxidant mixture, so that the fuel/oxidant mixture can be more fully reacted, and the combustion efficiency is improved.
2. The invention discloses an oxyhydrogen micro-mixing combustion device suitable for a gas turbine and a working method thereof.
3. The invention discloses an oxyhydrogen micro-mixing combustion device suitable for a gas turbine and a working method thereof.A tangential rotational flow is added at a fuel end, an axial tangential rotational flow flame is formed after ignition, a reactant layer of the flame structure surrounds the inner wall surface of a combustion chamber to form a layer of gas film, the inner wall surface of the combustion chamber is isolated from the flame layer, the inner wall surface of the combustion chamber is well cooled, meanwhile, the temperature of the flame is controlled by a diluent in an auxiliary manner, and the risk of high-temperature ablation of the inner wall surface of the combustion chamber can be reduced.
Drawings
FIG. 1 is a schematic longitudinal cross-sectional view of a micro-hybrid combustion device;
wherein: 1-combustion chamber, 2-array nozzle, 3-axial tangential swirl flame and 4-fuel/oxidant mixture.
FIG. 2 is a schematic longitudinal cross-sectional view of a nozzle;
wherein: 2.1-an air inlet cavity, 2.2-a rotational flow generating device, 2.1.1-an oxidant inlet, 2.1.2-a diluent inlet, 2.1.3-an air inlet convergence section, 2.1.4-a circular seam section and 2.1.5-a mixing section.
FIG. 3 is a schematic view of a structure of a swirling flow generating device;
wherein: 2.2.1-fuel inlet, 2.2.2-rotational flow.
Detailed Description
For a better understanding of the objects and advantages of the present invention, reference should be made to the following detailed description taken in conjunction with the accompanying drawings and examples.
Example 1:
FIG. 1 illustrates an exemplary block diagram of a micro-hybrid combustion device in which the flow paths of the diluent, oxidant, fuel and axial tangential swirl flame 3 are depicted, according to one embodiment of the invention. Fig. 3 shows a schematic structural diagram of the swirl generating device 2.2, wherein arrows represent the flow path of the fuel entering the combustion chamber 1 through the fuel inlet 2.2.1 of the swirl generating device 2.2 to form a swirl 2.2.2.
The embodiment discloses an oxyhydrogen micro-mixing combustion device suitable for a gas turbine, which comprises a combustion chamber 1 and an array nozzle 2.
The combustion chamber 1 is a cylindrical cavity structure.
The array nozzle 2 consists of a central nozzle and a peripheral nozzle. The central nozzle and the surrounding nozzles are identical in structure. The number of the central nozzles is one, the central axis of the central nozzles coincides with the central axis of the combustion chamber 1, the central nozzles are axially arranged along the combustion chamber 1 and are arranged in the center of the front end wall surface of the combustion chamber 1. The peripheral nozzles are at least two and symmetrical with respect to the central nozzle. The central and peripheral nozzles form a nozzle array of a micro-hybrid combustion device, with fuel, oxidant and diluent being injected axially into the combustion chamber 1 through the array nozzles 2. The central nozzle and the surrounding nozzles are identical in structure.
The single nozzle 2 mainly comprises an air inlet cavity 2.1 and a rotational flow generating device 2.2. The air inlet cavity 2.1 comprises an oxidant inlet 2.1.1, a diluent inlet 2.1.2, an air inlet convergence section 2.1.3, an annular seam section 2.1.4 and a mixing section 2.1.5. The air inlet cavity 2.1 is of a cylindrical cavity structure, openings are formed in the axial direction and the cylindrical wall surface, the axial openings are diluent inlets 2.1.2, and diluent is injected along a channel of the central axis of the air inlet cavity 2.1; the radial opening on the wall surface of the cylinder is an oxidant inlet 2.1.1, the inner space of the cylinder is divided into three parts from left to right along the axial direction according to the molded surface, and the three parts comprise an air inlet convergence section 2.1.3, a circular seam section 2.1.4 and a mixing section 2.1.5; at the axial opening, a central axis channel of the air inlet cavity 2.1 extends to a mixing section 2.1.5 of the inner space of the oxidant inlet 2.1.1, and the outer wall surface of the central axis channel and the small inner diameter wall surface of the inner space of the oxidant inlet 2.1.1 form a circular seam section 2.1.4; the swirl generating device 2.2 comprises a fuel inlet 2.2.1 and a swirl 2.2.2. The center of the rotational flow generating device 2.2 is of a hollow cylindrical structure and comprises a plurality of tangential fuel inlets 2.2.1 and an outlet, the tangential fuel inlets 2.2.1 are uniformly distributed along the hollow circumference, and the outlet is circular along the axial direction. The air inlet cavity 2.1, the rotational flow generating device 2.2 and the combustion chamber 1 are coaxially matched; the inner diameters of the mixing section 2.1.5 and the rotational flow generating device 2.2 are the same, and the outer diameter of a central axis channel of the air inlet cavity 2.1 is slightly smaller than the outer diameter of the first two so as to form an annular seam section 2.1.4.
The use method of the oxyhydrogen micro-mixed combustion device suitable for the gas turbine disclosed by the embodiment comprises the following steps:
in this example, pure hydrogen was used as the fuel, pure oxygen as the oxidant, and steam as the diluent, and the mass flow ratio of the three (hydrogen: oxygen: steam) was 1:8:40, hydrogen and oxygen are fed in a stoichiometric ratio, and the flow rate of the diluent is far greater than the total flow rate of oxyhydrogen. Pure oxygen introduced from the oxidant inlet 2.1.1 enters the mixing section 2.1.5 through the air inlet convergence section 2.1.3 and the circular seam section 2.1.4 and is mixed with water vapor introduced from the diluent inlet 2.1.2 to form pure oxygen/water vapor mixed gas axially introduced; pure hydrogen is introduced from a tangential fuel inlet 2.2.1 of a rotational flow generating device 2.2 to form a rotational flow 2.2, and the rotational flow is quickly mixed with pure oxygen/steam mixed gas which is axially introduced to form the pure oxygen/pure hydrogen/steam mixed gas. Because the mixed gas of the three gases not only has larger swirl circumferential speed, but also has certain axial speed, the mixed gas of the three gases can be spirally propelled in the combustion chamber 1, and after ignition, axial tangential swirl flame 3 is formed.
The flow of the water vapor introduced through the array nozzle 2 is far larger than the total flow of the oxyhydrogen, and the momentum of the water vapor is dominant in the pure oxygen/pure hydrogen/water vapor mixed gas. After entering the combustion chamber 1, the water vapor will, due to radial diffusion, squeeze the reactant layer of the axial tangential swirl flame 3 into the gap of the nozzle array, as shown at 4 in fig. 1, and thereby fully react. In addition, by controlling the flow rate of the water vapor, the flame temperature in the combustion chamber 1 can be effectively regulated.
The axial tangential swirling flame 3 has a long stroke in the combustion chamber 1, a long residence time and a high combustion temperature, and is beneficial to ignition and full combustion, so that the ignition performance and the flame stability can be improved. The problems of high combustion speed of oxyhydrogen, high flame temperature, easy tempering and ablation risk initiation become more serious under the condition of pure oxygen. Therefore, in the embodiment, the tempering risk can be greatly reduced by distributing the injection of pure oxygen and pure hydrogen from different inlets and increasing the wall quenching cooling effect of the annular seam section. The axial tangential swirling flame 3 is divided into a combustion product layer, a flame layer and a reactant layer from inside to outside, the reactant layer separates the flame layer from the inner wall surface of the combustion chamber 1, the inner wall surface of the combustion chamber 1 is well cooled, the temperature of the flame is adjusted and controlled by steam in an auxiliary manner, the risk of wall ablation can be reduced, the heat loss of the flame layer at the inner wall surface is reduced, and the flame stability of the combustion chamber under low load is improved. Under the strong swirl air inlet condition, a backflow area can be formed in the combustion chamber, the temperature of combustion products in the backflow area is higher, the retention time is longer, a stable heat source is formed, and the flame stability of the combustion chamber can be effectively improved.
The above detailed description is intended to illustrate the objects, aspects and advantages of the present invention, and it should be understood that the above detailed description is only exemplary of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (3)
1. The utility model provides a little mixed burner of oxyhydrogen suitable for gas turbine which characterized in that: comprises a combustion chamber (1) and an array nozzle (2);
the combustion chamber (1) is of a cylindrical cavity structure;
the array nozzle (2) consists of a central nozzle and peripheral nozzles; the central nozzle and the surrounding nozzles have the same structure; the number of the central nozzles is one, the central axis of each central nozzle is superposed with the central axis of the combustion chamber (1), and the central nozzles are axially arranged along the combustion chamber (1) and arranged at the center of the front end wall surface of the combustion chamber (1); the peripheral nozzles are at least two and symmetrical about the central nozzle; the central nozzle and the surrounding nozzles form a nozzle array of a micro-hybrid combustion device, and fuel, oxidant and diluent are axially injected into the combustion chamber (1) through the array nozzles (2); the central nozzle and the surrounding nozzles have the same structure;
the single nozzle (2) mainly comprises an air inlet cavity (2.1) and a rotational flow generating device (2.2); the gas inlet cavity (2.1) comprises an oxidant inlet (2.1.1), a diluent inlet (2.1.2), a gas inlet convergence section (2.1.3), a circular seam section (2.1.4) and a mixing section (2.1.5); the air inlet cavity (2.1) is of a cylindrical cavity structure, openings are formed in the axial direction and the cylindrical wall surface, the axial openings are diluent inlets (2.1.2), and diluent is injected along a central axis channel of the air inlet cavity (2.1); the radial opening on the wall surface of the cylinder is an oxidant inlet (2.1.1), the inner space of the cylinder is divided into three parts from left to right along the axial direction according to the molded surface, and the three parts comprise an air inlet convergence section (2.1.3), a circular seam section (2.1.4) and a mixing section (2.1.5); at the axial opening, a central axis channel of the air inlet cavity (2.1) extends to a mixing section (2.1.5) of the inner space of the oxidant inlet (2.1.1), and the outer wall surface of the central axis channel and the small inner diameter wall surface of the inner space of the oxidant inlet (2.1.1) form a circular seam section (2.1.4); the swirl generating device (2.2) comprises a fuel inlet (2.2.1) and a swirl (2.2.2); the center of the rotational flow generating device (2.2) is of a hollow cylindrical structure and comprises a plurality of tangential fuel inlets (2.2.1) and an outlet, the tangential fuel inlets (2.2.1) are uniformly distributed along the hollow circumference, and the outlet is circular along the axial direction; the air inlet cavity (2.1), the rotational flow generating device (2.2) and the combustion chamber (1) are coaxially matched; the inner diameters of the mixing section (2.1.5) and the rotational flow generating device (2.2) are the same, and the outer diameter of a central axis channel of the air inlet cavity (2.1) is slightly smaller than the outer diameter of the central axis channel of the air inlet cavity and the rotational flow generating device so as to form a circular seam section (2.1.4).
2. The oxyhydrogen micro-mixing combustion device suitable for a gas turbine according to claim 1, wherein: the using method comprises the following steps:
the oxidant is introduced from a radial oxidant inlet (2.1.1), passes through an air inlet convergence section (2.1.3), enters a mixing section (2.1.5) from a circular seam section (2.1.4), and is mixed with the diluent introduced from a central axial channel of the nozzle to form diluent/oxidant mixed gas introduced axially; fuel is introduced from a tangential fuel inlet (2.2.1) of a rotational flow generating device (2.2), is rapidly mixed with diluent/oxidant mixed gas which is axially introduced, and forms axial tangential rotational flow flame (3) after being ignited; the diluent injected axially from the center of the nozzle enters the combustion chamber (1) and then radially diffuses, so that the diluent is used for diluting reaction products and controlling the flame temperature, and the fuel/oxidant mixture (4) is extruded to a gap between adjacent nozzles to react for a sufficient time under the diffusion action of the diluent introduced into the adjacent nozzles; the diluent is injected axially through the center of the array nozzle (2), so that the mixing uniformity in the micro-mixed combustion chamber can be improved, the combustion sufficiency is further improved, the reaction temperature can be regulated and controlled, and the risk of high-temperature ablation of the wall surface is reduced;
since the oxidant is introduced from the radial oxidant inlet (2.1.1) and the fuel is introduced from the tangential fuel inlet (2.2.1) of the rotational flow generating device (2.2), the risk of backfire can be reduced; but considering the extremely high burning speed of pure hydrogen and pure oxygen, the circular seam section (2.1.4) is further added, thereby enhancing the cooling and quenching effects of the wall surface, improving the anti-tempering performance and further being capable of adapting to the direct mixed combustion of the pure hydrogen and the pure oxygen;
the fuel at the tangential fuel inlet (2.2.1) forms a rotational flow (2.2.2) at the outlet of the rotational flow generating device (2.2), the internal stroke is longer, so that the fuel has longer residence time, the strong rotational flow is helpful for mixing the oxidant and the fuel, the fuel and the oxidant are quickly mixed in the longer residence time, the fuel and the oxidant are spirally injected into the combustion chamber (1) under the action of the rotational flow, and an axial tangential rotational flow flame (3) is formed after the fuel is ignited.
3. The oxyhydrogen micro-mixing combustion device suitable for a gas turbine according to claim 2, wherein: the axial tangential swirl flame (3) is of a three-layer flame structure, and the three-layer flame structure sequentially comprises from inside to outside: a combustion product layer consisting of reaction products formed by combustion; a flame layer; the reactant layer is composed of unburned gas, a gas film is formed around the inner wall of the combustion chamber (1) by the reactant layer, the temperature of the gas film is low, and the inner wall surface of the combustion chamber (1) is isolated from the flame layer, so that the inner wall surface of the combustion chamber (1) is well cooled, the service life of the combustion chamber is effectively prolonged, the heat loss of the flame layer at the inner wall surface of the combustion chamber (1) is reduced, and the combustion stability of flame is improved; in addition, when the tangential rotational flow enters air, a backflow area is formed in the combustion chamber (1), the temperature of combustion products in the backflow area is high, the retention time is long, a stable heat source is formed, and the flame stability of the combustion chamber (1) can be effectively improved.
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