CN115059917A - High-speed multiphase jet combustor with contraction section - Google Patents
High-speed multiphase jet combustor with contraction section Download PDFInfo
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- CN115059917A CN115059917A CN202210731223.XA CN202210731223A CN115059917A CN 115059917 A CN115059917 A CN 115059917A CN 202210731223 A CN202210731223 A CN 202210731223A CN 115059917 A CN115059917 A CN 115059917A
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- 230000008602 contraction Effects 0.000 title claims abstract description 77
- 238000002485 combustion reaction Methods 0.000 claims abstract description 90
- 239000007789 gas Substances 0.000 claims abstract description 72
- 239000000446 fuel Substances 0.000 claims abstract description 70
- 230000009467 reduction Effects 0.000 claims abstract description 16
- 238000001816 cooling Methods 0.000 claims abstract description 11
- 239000002737 fuel gas Substances 0.000 claims abstract description 6
- 239000007787 solid Substances 0.000 claims description 24
- 239000000498 cooling water Substances 0.000 claims description 18
- 230000007704 transition Effects 0.000 claims description 8
- 238000000034 method Methods 0.000 claims description 7
- 239000000126 substance Substances 0.000 claims description 7
- 230000008021 deposition Effects 0.000 claims description 4
- 230000001590 oxidative effect Effects 0.000 claims description 4
- 239000007800 oxidant agent Substances 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 230000002035 prolonged effect Effects 0.000 claims description 2
- 230000014759 maintenance of location Effects 0.000 claims 1
- 239000012071 phase Substances 0.000 abstract description 18
- 238000002156 mixing Methods 0.000 abstract description 6
- 239000007790 solid phase Substances 0.000 abstract description 5
- 239000008247 solid mixture Substances 0.000 abstract description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 34
- 239000002245 particle Substances 0.000 description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 8
- 229910052799 carbon Inorganic materials 0.000 description 8
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 229910052760 oxygen Inorganic materials 0.000 description 5
- 239000001301 oxygen Substances 0.000 description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 238000004939 coking Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000005514 two-phase flow Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
- F23D17/005—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or pulverulent fuel
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Abstract
The invention discloses a high-speed multiphase jet combustor with a contraction section, and belongs to the field of combustors. The invention comprises an upper cover, a gasket, a contraction cavity, a burner frame and a base. The burner frame is composed of an outer frame, a rectifying medium and a porous medium. The lean premixed gas is introduced from a gas flow inlet on the outer frame and flows through the rectification medium and the porous medium to form stable radial jet flows uniformly distributed on the periphery in the combustor; the fuel jet of gas-solid mixture is introduced from an axial jet inlet on the base; the contraction cavity is used as a contraction section of the combustor. High-temperature multi-phase fuel gas generated after the radial jet flow and the axial jet flow are combusted in the combustor is accelerated by the contraction section and then is discharged from the combustor. The annular cavity is used as a water-cooling flow channel of the combustor to cool the contraction cavity. The invention can realize the rapid mixing and the efficient combustion of gas-phase and solid-phase fuels, has good adjustable controllability, can achieve the purposes of pollution reduction and emission reduction, and can generate high-speed multiphase fuel gas jet flow.
Description
Technical Field
The invention relates to a high-speed multiphase jet combustor with a contraction section, and belongs to the field of combustors.
Background
The high-speed jet flame has a large flow field speed, so that the residence time of the fuel is limited, and the fuel is difficult to be fully combusted due to a high-pressure area generated by combustion reaction in the high-speed flame, and the combustion efficiency is not high. The problem of low combustion efficiency in high velocity jet flames is more pronounced with pulverized fuels than with gaseous and liquid fuels.
At present, a common method for improving the combustion efficiency of high-speed jet flame is to arrange flame tracing in the same direction as the high-speed jet flame around the high-speed jet flame, so that the high-speed jet flame is isolated from the outside cold air to reduce the heat loss of the high-speed jet flame, thereby improving the temperature and the combustion efficiency of the high-speed jet flame. However, under the injection effect of the central high-speed jet flame, the surrounding flame can be gathered towards the central high-speed jet flame, so that the flame can only cover a partial section of the lower part of the high-speed jet flame, and the combustion efficiency of the flame is limited.
A typical staged burner has an axial staged combustion mode in which a main combustion zone, a reburning zone and a burnout zone are sequentially arranged in a vertical direction; there are also radial staged combustion modes, such as a double tangential circle combustion mode in which primary air pulverized coal flows are formed in the furnace with inner air and secondary air outside. Part of NO produced in the main combustion zone X Is reduced to N in the reburning zone 2 (ii) a The fuel burnout degree, the reburning zone temperature, the amount of secondary fuel, the feeding mode of air flow and fuel and the like of the main burning zone have the fuel combustion efficiency andNO X has an effect on emissions of; the higher the temperature in the reburning zone, the lower the NO X The more pronounced the effect of the discharge. The radial staged combustion mode of the double tangent circles can further improve the effects of pollution reduction and emission reduction, but has the problems of large combustion temperature deviation in the furnace, easy coking of a hearth and the like.
Disclosure of Invention
The invention aims to provide a high-speed multiphase jet combustor with a contraction section, which can realize the rapid mixing and efficient combustion of gas-phase and solid-phase fuels, has good adjustability and controllability, can achieve the purposes of pollution reduction and emission reduction, and can generate high-speed multiphase gas jet.
The purpose of the invention is realized by the following technical scheme:
the invention discloses a high-speed multiphase jet combustor with a contraction section, which comprises an upper cover, a gasket, a contraction cavity, a combustor frame and a base. The burner frame is composed of an outer frame, a rectifying medium and a porous medium; a plurality of airflow inlets are formed in the periphery of the outer frame and used for introducing premixed lean-burn gas; the porous medium is an annular structure provided with a plurality of radial parallel air inlets; a gap is reserved between the outer frame and the porous medium to form an annular chamber; the rectifying medium is arranged in the annular cavity and fixedly arranged on the porous medium, and lean premixed gas introduced from the airflow inlets around the outer frame is firstly diffused in the annular cavity between the outer frame and the rectifying medium and then passes through the rectifying medium and the porous medium to form radial jet flow which is uniformly distributed around, stable and points to the axis of the combustion chamber in the combustion chamber. The base is installed to the below of combustor frame, and shrink chamber and upper cover are installed to the top. Gaskets are arranged between the base and the burner frame, between the burner frame and the contraction cavity, and between the contraction cavity and the upper cover. The inner cavity formed by the base, the porous medium and the contraction cavity forms a combustion chamber of the combustor. The base is provided with an axial jet inlet which can introduce multiphase fuel jet into the combustor. Because the inner diameter of the combustion chamber (namely the inner diameter of the annular porous medium) is larger than the inner diameter of the inlet of the axial fuel jet, the speed of the axial fuel jet is reduced after the axial fuel jet is introduced into the combustion chamber, and the residence time is prolonged. The cross section of the inner cavity of the contraction cavity is circular, the end with the larger inner diameter is equal to the inner diameter of the annular porous medium, the inner diameter of the contraction cavity is gradually reduced and smoothly transited, the end with the smaller inner diameter is used as a fuel gas outlet of the combustor, and the contraction cavity is the contraction section of the combustor. The contraction cavity is provided with a groove and forms an annular cavity after being sealed with the upper cover; and a cooling water inlet and outlet is arranged on the outer side of the contraction cavity, cooling water can be injected into the annular cavity, and the annular cavity is used as a water-cooling flow channel of the combustor to cool the contraction cavity.
Preferably, the base is in a boss shape and can be matched with the annular porous medium, so that the coaxiality of the jet inlet on the base and the combustion chamber is improved.
Preferably, the outer contour of the cross section of the outer frame is square, and the inner contour of the cross section of the outer frame is circular.
Preferably, the number of the air flows arranged around the outer frame is 4, and the air flows are uniformly distributed around and point to the central axis of the combustion chamber.
Preferably, the number of cooling water inlets and outlets provided in the contraction cavity is 1.
Preferably, the outer frame, the base, the contraction cavity and the upper cover can be fixed by fastening bolts through bolt hole positions uniformly distributed on the periphery, and gaskets are arranged between every two parts to ensure sealing.
The invention discloses a working method of a high-speed multiphase jet combustor with a contraction section, which comprises the following steps: and introducing lean premixed gas from the gas flow inlets around the outer frame, wherein the premixed gas is firstly diffused in the annular cavity between the outer frame and the rectifying medium, and after passing through the rectifying medium and the porous medium, radial jet flows uniformly distributed from outside to inside and around are formed in the combustion chamber. After the radial jet flow is ignited, gas-phase tubular flame is formed in the combustion chamber, the axis of the tubular flame is superposed with the axis of the combustion chamber, and the internal temperature distribution is uniform. And introducing a gas-solid mixed fuel jet formed by carrying the pulverized fuel by the gas fuel into the axial jet inlet at the bottom, wherein the axis of the axial jet inlet is superposed with the axis of the combustion chamber. The premixed gas which is introduced into the combustion chamber in the radial direction and the gas-solid mixed fuel which is introduced in the axial direction are introduced into the combustion chamber in a jet flow mode, so that the generation of turbulence and backflow can be effectively reduced, and the flame has good adjustable controllability. The axial gas-solid mixed fuel jet flow and the surplus oxidant after the radial premixed lean-burn jet flow which is uniformly distributed from outside to inside and around are combusted are quickly mixed and efficiently combusted. Because the premixed gas introduced along the radial direction is lean gas, the gas-solid mixed fuel is injected into the combustion chamber through the axial jet flow inlet, the global equivalence ratio is regulated to be 1, the staged combustion of the fuel is realized, the combustion efficiency is improved, and the NO is obviously reduced at the same time X The purposes of pollution reduction and emission reduction are achieved. The diameters of the inner cavities of the cross sections of the contraction cavity are determined by a Witosins curve equation, so that the smooth transition of the contraction cavity and the combustion chamber and the smooth transition of the contraction cavity are ensured, the deposition of condensed phase substances is reduced, high-temperature multi-phase gas has uniform and stable speed distribution when being sprayed out of the combustor, and stable high-speed multi-phase jet flame is formed at a gas outlet of the combustor. The contraction cavity is provided with an annular water-cooling runner, and cooling water flows in/out of a cold runner of the cooling water from a cooling water inlet/outlet on the outer side of the contraction cavity, so that the contraction cavity can be cooled and protected.
Has the advantages that:
1. the invention discloses a high-speed multiphase jet combustor with a contraction section, which makes full use of the combustion characteristics of tubular flame. Introducing the lean premixed gas into a combustion chamber by utilizing an annular rectifying medium and a porous medium to generate radial inflow with uniformly distributed speeds and flow rates from outside to inside and around in the combustion chamber; igniting the radially uniformly distributed lean premixed gas to flow, and then forming a tubular flame zone in the combustion chamber to generate a uniformly distributed temperature zone; gas-solid mixed fuel is axially introduced, the global equivalence ratio is regulated to be 1, the axial gas-solid mixed fuel jet flow is mixed and reacted with the lean fuel gas at the center of the tubular flame, and the axial fuel forms a reducing atmosphere at the initial stage of the reaction with the fuel gas at the center of the tubular flame, so that the staged combustion of the fuel is realized; in addition, the tubular flame is favorable for reducing the heat loss of axial fuel jet combustion, improving the temperature of a reduction region, effectively improving the combustion efficiency and reducing NO X The purposes of pollution reduction and emission reduction are achieved.
2. The invention discloses a high-speed multiphase jet combustor with a contraction section, which makes full use of the flow characteristics of radial premixed lean-burn gas incoming flow and axial fuel jet flow. The radial and axial airflows adopt a jet flow mode, the generation of turbulence and backflow can be reduced, and the control on the airflow and particle flow speed, the residence time of fuel in a combustion chamber and the gas temperature is facilitated. The axial fuel jet flow of gas-solid mixture and the combustion product of the lean-burn tubular flame are quickly and fully mixed by means of the impact and the flow characteristics of the axial jet flow and the radial jet flow, so that the axial fuel jet flow of gas-solid mixture and the combustion product of the radial premixed lean-burn tubular flame can fully react, the combustion efficiency is improved, and simultaneously, the reduction of NO is facilitated X And (4) discharging.
3. According to the high-speed multiphase jet combustor with the contraction section, disclosed by the invention, the axial fuel jet can utilize the gas-phase fuel jet to carry solid-phase fuel particles, so that a gas-solid two-phase flow with good adjustable controllability is formed, and the stable injection of the gas-solid mixed fuel jet can be realized through regulation and control. The gas-solid proportion and the powder flow of the gas-solid mixed fuel jet can be controlled by changing the flow and the flow speed of the axial jet. By changing the flow rate and speed of the radial inflow and the axial jet, the residence time of the particles in the combustion chamber can be controlled. The mutual impact action of the radial incoming flow and the axial fuel jet flow of gas-solid mixing is beneficial to the full mixing of the fuel and the oxidant, the combustion efficiency of the fuel can be effectively improved (particularly, the combustion efficiency of solid-phase fuel particles with higher melting point and difficult ignition and combustion is obviously improved), and then high-temperature multi-phase gas with high-efficiency combustion is formed.
4. The invention discloses a high-speed multiphase jet burner with a contraction section, wherein a large amount of high-temperature multiphase gas is generated by burning gas-solid mixed fuel in a combustion chamber; the high-temperature multi-phase gas generated by combustion of the gas-solid mixed fuel is accelerated by utilizing the contraction cavity, the diameters of inner cavities of all cross sections of the contraction cavity are determined by a Vitosynes curve equation, smooth transition of the contraction cavity and the combustion chamber and smooth transition of the contraction cavity are ensured, the high-temperature multi-phase gas has uniform air flow velocity distribution and a straight flowing direction when being sprayed out of the combustor, and jet flame at a gas outlet can reach required and stable flow velocity to form stable high-speed multi-phase jet flame. The premixed gas with lean combustion is uniformly introduced from the periphery of the combustion chamber, and an oxidizing atmosphere is formed near the wall surface of the combustion chamber, so that slagging in the combustor is favorably inhibited; the smoothly transitioning constricting chambers also have the effect of reducing condensed phase material deposition. The water cooling runner is arranged outside the contraction cavity, and cooling protection of the contraction cavity can be realized by cooling water when the combustor works.
Drawings
FIG. 1 is a longitudinal cross-sectional view of a high-velocity multi-phase jet combustor with a constriction;
FIG. 2 is a transverse cross-sectional view of the burner at the water-cooled runner;
fig. 3 is a transverse cross-sectional view of the burner at the burner frame.
The device comprises a top cover 1, a gasket 2, a contraction cavity 3, a burner frame 4, an outer frame 4.1, a rectification medium 4.2, a porous medium 4.3, a base 5, a gas outlet 6, an axial jet inlet 7, a cooling water inlet and outlet 8, a water-cooling flow channel 9 and an airflow inlet 10.
Detailed Description
The high-speed multiphase jet combustor with the contraction section disclosed by the embodiment comprises an upper cover 1, a gasket 2, a contraction cavity 3, a combustor frame 4 and a base 5; the burner frame 4 is composed of an outer frame 4.1, a flow-straightening medium 4.2 and a porous medium 4.3.
The base 5 is of a square structure, a round axial jet inlet 7 is arranged at the center of the base 5, a round boss is arranged at the upper end of the base 5, and the round boss structure on the base 5 is overlapped with the axis of the round axial jet inlet 7; an outer frame 4.1 is arranged above the base 5, the outer frame 4.1 is of an outer square inner circle structure, and 4 radial airflow inlets 10 are uniformly distributed on the periphery. The annular rectifying medium 4.2 and the annular porous medium 4.3 are sequentially arranged in the outer frame 4.1 from outside to inside, the heights of the rectifying medium 4.2 and the porous medium 4.3 are the same as that of the outer frame 4.1, and the axes of the rectifying medium 4.2 and the porous medium are coincident. A certain interval is reserved between the rectifying medium 4.2 and the outer frame 4.1 to form an annular cavity. The rectifying medium 4.2 is tightly attached to the porous medium 4.3, and the inner diameter of the porous medium 4.3 is equal to the diameter of the circular boss on the base 5, so that the base 5 and the porous medium 4.3 can be matched with each other, and the axial jet inlet 7 on the base 5 is ensured to be coincident with the axis of the porous medium 4.3. The shrink cavity 3 is installed to frame 4.1 top, and the arbitrary cross section of the inner chamber in shrink cavity 3 is circular, and the entry diameter in shrink cavity 3 is the same with cyclic annular porous medium 4.3's internal diameter, and the inner chamber cross-sectional diameter in shrink cavity 3 is followed the axial distribution and is confirmed by the vitosins curvilinear equation:
in the formula, R 0 、R 1 Respectively, the radius of an outlet and the radius of an inlet of the contraction cavity 3, l is the total length of the contraction cavity 3, R is the radius of any point, and x is the vertical distance between any point and the inlet end.
An annular groove is reserved on the contraction cavity 3, the upper cover 1 is installed on the contraction cavity 3 to seal the annular groove, and cooling water can be injected into the annular groove through a cooling water inlet and outlet 8 on the outer side of the contraction cavity 3 to form a water cooling flow channel 9.
Bolt hole sites are arranged around the upper cover 1, the contraction cavity 3, the outer frame 4.1 and the base 5 and are fixed through fastening bolts.
The working method of the high-speed multiphase jet combustor with the contraction section disclosed by the embodiment comprises the following steps: the lean premixed gas is introduced from the gas flow inlets 10 around the outer frame 4.1, the premixed gas firstly diffuses in the annular chamber between the outer frame 4.1 and the rectification medium 4.2, and after passing through the rectification medium 4.2 and the porous medium 4.3, radial gas flows with uniformly distributed flow velocity from outside to inside and around are formed in the combustion chamber. After ignition of this radial gas flow, a tubular flame zone is formed in the combustion chamber, the axis of the tubular flame zone coinciding with the axis of the combustion chamber. Gas-solid mixed fuel jet formed by the powder fuel carried by the gas fuel is introduced from the axial jet inlet 7 on the base 5, and the axial line of the axial jet inlet 7 is superposed with the axial line of the combustion chamber. The premixed gas which is introduced into the combustion chamber in the radial direction and the gas-solid mixed fuel which is introduced in the axial direction are introduced into the combustion chamber in a jet flow mode, so that the premixed gas and the gas-solid mixed fuel can be effectively introduced into the combustion chamberThe generation of turbulence and backflow is reduced, and the burner has good adjustable controllability. The lean-burning tubular flame is ignited by axially introducing gas-solid mixed fuel jet flow, so that rapid mixing and efficient combustion are carried out. The premixed gas introduced from outside to inside in the radial direction is lean gas; then the gas-solid mixed fuel jet flow is introduced from the axis of the combustion chamber to make the equivalence ratio be 1, so that the flame temperature is raised, the staged combustion of the fuel is realized, and the NO can be obviously reduced X The purposes of pollution reduction and emission reduction are achieved. The diameters of the inner cavities of the cross sections of the contraction cavity 3 are determined by a Witosins curve equation, so that the smooth transition of the contraction cavity 3 and the combustion chamber and the smooth transition of the contraction cavity 3 are ensured, the deposition of condensed phase substances is reduced, and when high-temperature multi-phase gas is sprayed out from the gas outlet 6 of the combustor, the high-temperature multi-phase gas has uniform and stable gas velocity distribution and a straight flowing direction, so that jet flame at the gas outlet of the combustor can reach the required and stable flow velocity, and stable high-speed multi-phase jet flame is formed. An annular water cooling runner 9 is arranged on the contraction cavity 3, and cooling water flows in/out of the water cooling runner 9 from a cooling water inlet/outlet 8 at the outer side of the contraction cavity, so that the contraction cavity 3 can be cooled and protected.
In the embodiment, the gas radially introduced into the combustion chamber from the periphery of the outer frame 4.1 is premixed gas of air and methane, and is in a lean combustion state with the air-fuel ratio less than 1; the gas fuel in the gas-solid mixed fuel jet which is introduced into the combustion chamber from the axial jet inlet 7 on the base 5 is methane, and carbon particles are used as solid phase fuel in the gas-solid mixed axial fuel jet.
The working method of the high-speed multiphase jet combustor with the contraction section disclosed by the embodiment comprises the following concrete implementation steps:
the method comprises the following steps: calculating the flow of fuel and air which needs to be introduced finally at each inlet when the global equivalence ratio of the combustor is 1: the chemical equation for complete combustion of methane and oxygen is: CH (CH) 4 +2O 2 ＝CO 2 +2H 2 O; the chemical equation for complete combustion of carbon and oxygen is: c + O 2 ＝CO 2 (ii) a Calculated as the oxygen content in air is one fifth. When the burner is in stable operation, the gas is introduced from the gas inlet 10The flow rate of the mixed gas is 24m 3 H, wherein the ratio of methane to air is 1: 15; the flow of methane introduced into the axial jet inlet 7 is 0.5m 3 The flow rate of carbon particles carried in the axially introduced methane gas stream was, after rectification, 268 g/h. According to the chemical equation of complete combustion of methane and oxygen and the chemical equation of complete combustion of carbon and oxygen, the global equivalence ratio of the combustor under the conditions is 1 through calculation.
Step two: and (3) mounting pipelines, wherein premixing lean-burn gas pipelines of methane and air are connected to each gas flow inlet 10 arranged around the outer frame 4.1, and fuel pipelines for mixing methane and carbon particles are connected to the axial jet flow inlet 7 of the burner base 5.
Step three: introducing a small amount of a premixed gas of methane and air from the gas stream inlet 10, wherein the total flow rate of the premixed gas introduced from the gas stream inlet 10 is 1.6m 3 The methane to air ratio was 1:15, and the premixed gas of methane and air in the burner was ignited.
Step four: introducing a gas-solid mixed fuel jet of methane and carbon particles from an axial jet inlet 7 on a base 5, wherein the flow rate of methane in the step is 0.05m 3 The flow rate of carbon particles was 27 g/h.
Step five: gradually increasing the flow rate of the radial premixed lean-burn gas jet to increase the flow rate of the premixed gas of each gas flow inlet 10 to 24m 3 H, wherein the ratio of methane to air is 1: 15; the flow of methane introduced into the axial jet inlet 7 was increased to 0.5m 3 The flow rate of carbon particles is increased to 268g/h, and finally a stable high-speed multiphase jet flame is formed.
Step six: when the combustor stops working, firstly, the flow rate of the axial fuel jet flow is gradually reduced to zero, and then the flow rate of methane gas and air gas in the radial premixed lean-burn gas is reduced to zero, so that the combustor stops working.
The above description is further intended to illustrate the objects, methods, apparatus, solutions and advantages of the present invention, and it should be understood that the above description is only illustrative of the specific implementation 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 (7)
1. A high-speed heterogeneous jet burner of area shrink section which characterized in that: comprises an upper cover, a gasket, a contraction cavity, a burner frame and a base; the burner frame is composed of an outer frame, a rectifying medium and a porous medium; a plurality of airflow inlets are formed in the periphery of the outer frame and used for introducing premixed lean-burn gas; the porous medium is an annular structure provided with a plurality of radial parallel air inlets; a gap is reserved between the outer frame and the porous medium to form an annular chamber; the rectifying medium is arranged in the annular chamber and fixedly arranged on the porous medium, and lean premixed gas introduced from the airflow inlets around the outer frame is firstly diffused in the annular chamber between the outer frame and the rectifying medium and then passes through the rectifying medium and the porous medium to form radial jet flow which is uniformly distributed around and stable and points to the axis of the combustion chamber in the combustion chamber; a base is arranged below the combustor frame, and a contraction cavity and an upper cover are arranged above the combustor frame; gaskets are arranged between the base and the burner frame, between the outer frame and the contraction cavity, and between the contraction cavity and the upper cover; an internal cavity formed by the base, the porous medium and the contraction cavity forms a combustion chamber of the combustor; the base is provided with an axial jet inlet which can introduce multiphase fuel jet into the combustor; because the inner diameter of the annular porous medium of the combustor is larger than the inner diameter of the axial fuel jet inlet, the speed of the axial fuel jet is reduced after the axial fuel jet is introduced into the combustion chamber, and the retention time is prolonged; the cross section of the inner cavity of the contraction cavity is circular, the end with the larger inner diameter is equal to the inner diameter of the annular porous medium, the inner diameter of the contraction cavity is gradually reduced and smoothly transited, the end with the smaller inner diameter is used as a fuel gas outlet of the combustor, and the contraction cavity is the contraction section of the combustor; the shrinkage cavity is provided with a groove and is sealed with the upper cover to form an annular cavity, the outer side of the shrinkage cavity is provided with a cooling water inlet and outlet, cooling water can be injected into the annular cavity, and the annular cavity is used as a water-cooling flow channel of the combustor to cool the shrinkage cavity.
2. The method of claim 1, wherein: the base is boss-shaped and can be matched with annular porous media, so that the coaxiality of a jet inlet on the base and the combustion chamber is improved.
3. A high-velocity multi-phase jet combustor with a convergent section according to claim 1, wherein: the outer contour of the cross section of the outer frame is square, and the inner contour of the cross section of the outer frame is circular.
4. A high-velocity multi-phase jet combustor with a convergent section according to claim 1, wherein: the number of the air flows arranged around the outer frame is 4, and the air flows are uniformly distributed around and point to the central axis of the combustion chamber.
5. A high-velocity multi-phase jet combustor with a convergent section according to claim 1, wherein: and 1 cooling water inlet and outlet are respectively arranged on the contraction cavity.
6. A high-velocity multi-phase jet combustor with a convergent section according to claim 1, wherein: the outer frame, the base, the contraction cavity and the upper cover can be fixed by fastening bolts through bolt hole positions uniformly distributed on the periphery, and gaskets are arranged between every two parts to ensure sealing.
7. A high velocity multi-phase jet combustor with a constriction as claimed in claim 1, 2, 3, 4, 5 or 6 wherein: introducing lean premixed gas from gas flow inlets around the outer frame, diffusing the premixed gas in an annular cavity between the outer frame and a rectifying medium, and forming radial jet flows uniformly distributed from outside to inside and around in the combustion chamber after the premixed gas passes through the rectifying medium and the porous medium; after the radial jet flow is ignited, gas-phase tubular flame is formed in the combustion chamber, the axis of the tubular flame is superposed with the axis of the combustion chamber, and the internal temperature distribution is uniform. Introducing a gas-solid mixed fuel jet formed by carrying powdered fuel with gas fuel into the axial jet inlet at the bottom, wherein the axis of the axial jet inlet is superposed with the axis of the combustion chamber; premixed gas radially introduced into combustion chamber and axially introduced gas-solidThe mixed fuel is introduced into the combustion chamber in a jet flow mode, so that the generation of turbulence and backflow can be effectively reduced, and flame has good adjustable controllability; the axial gas-solid mixed fuel jet flow and the surplus oxidant after the combustion of the radial premixed lean-burn jet flow which is uniformly distributed from outside to inside and around are quickly mixed and efficiently combusted; because the premixed gas introduced along the radial direction is lean gas, the gas-solid mixed fuel is injected into the combustion chamber through the axial jet flow inlet, the global equivalence ratio is regulated to be 1, the staged combustion of the fuel is realized, the combustion efficiency is improved, and the NO is obviously reduced at the same time X The purposes of pollution reduction and emission reduction are achieved; the diameters of inner cavities of all cross sections of the contraction cavity are determined by a Witosins curve equation, so that the smooth transition of the contraction cavity and the combustion chamber and the smooth transition of the contraction cavity are ensured, the deposition of condensed phase substances is reduced, high-temperature multi-phase gas has uniform and stable speed distribution when being sprayed out of the combustor, and stable high-speed multi-phase jet flame is formed at a gas outlet of the combustor; the contraction cavity is provided with an annular water-cooling runner, and cooling water flows in/out of a cold runner of the cooling water from a cooling water inlet/outlet on the outer side of the contraction cavity, so that the contraction cavity can be cooled and protected.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210731223.XA CN115059917B (en) | 2022-06-24 | 2022-06-24 | High-speed multiphase jet burner with contraction section |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210731223.XA CN115059917B (en) | 2022-06-24 | 2022-06-24 | High-speed multiphase jet burner with contraction section |
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| Publication Number | Publication Date |
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| CN115059917A true CN115059917A (en) | 2022-09-16 |
| CN115059917B CN115059917B (en) | 2024-06-18 |
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| CN202210731223.XA Active CN115059917B (en) | 2022-06-24 | 2022-06-24 | High-speed multiphase jet burner with contraction section |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1185559A (en) * | 1996-09-25 | 1998-06-24 | Abb研究有限公司 | Burner of controlling combustion chamber |
| CN1198518A (en) * | 1997-04-25 | 1998-11-11 | 英国氧气集团有限公司 | Granule jetting burner |
| CN1918431A (en) * | 2004-02-10 | 2007-02-21 | 株式会社荏原制作所 | Combustion apparatus and combustion method |
| CN102086415A (en) * | 2009-12-03 | 2011-06-08 | 通用电气公司 | Feeding device and feeding method |
| CN104964281A (en) * | 2015-07-02 | 2015-10-07 | 周海波 | Fuel-gas-catalyzed flameless near-infrared indirect heating porous medium burner |
| CN112443838A (en) * | 2020-12-11 | 2021-03-05 | 杭州电子科技大学 | Blast air premixing porous medium combustion radiator with secondary air and combustion method thereof |
| CN112594689A (en) * | 2020-12-15 | 2021-04-02 | 北京理工大学 | High-temperature high-speed stable combustion method and device based on multistage jet flow and rotational flow |
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2022
- 2022-06-24 CN CN202210731223.XA patent/CN115059917B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1185559A (en) * | 1996-09-25 | 1998-06-24 | Abb研究有限公司 | Burner of controlling combustion chamber |
| CN1198518A (en) * | 1997-04-25 | 1998-11-11 | 英国氧气集团有限公司 | Granule jetting burner |
| CN1918431A (en) * | 2004-02-10 | 2007-02-21 | 株式会社荏原制作所 | Combustion apparatus and combustion method |
| CN102086415A (en) * | 2009-12-03 | 2011-06-08 | 通用电气公司 | Feeding device and feeding method |
| CN104964281A (en) * | 2015-07-02 | 2015-10-07 | 周海波 | Fuel-gas-catalyzed flameless near-infrared indirect heating porous medium burner |
| CN112443838A (en) * | 2020-12-11 | 2021-03-05 | 杭州电子科技大学 | Blast air premixing porous medium combustion radiator with secondary air and combustion method thereof |
| CN112594689A (en) * | 2020-12-15 | 2021-04-02 | 北京理工大学 | High-temperature high-speed stable combustion method and device based on multistage jet flow and rotational flow |
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| CN115059917B (en) | 2024-06-18 |
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