CN104776451A - Multistage swirl combustion chamber with double-path backflow - Google Patents
Multistage swirl combustion chamber with double-path backflow Download PDFInfo
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- CN104776451A CN104776451A CN201510176794.1A CN201510176794A CN104776451A CN 104776451 A CN104776451 A CN 104776451A CN 201510176794 A CN201510176794 A CN 201510176794A CN 104776451 A CN104776451 A CN 104776451A
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Abstract
The invention relates to a multistage swirl combustion chamber with double-path backflow. A combustion head part is provided with a fuel spray nozzle and a plurality of swirlers in concentric radial arrangement, wherein a spray opening of the fuel spray nozzle and the swirlers are in separated arrangement, the adjacent radial swirlers are in opposite rotating direction arrangement, a plurality of exhaust holes are formed in the wall of a flame tube, an upstream ring cavity and a downstream ring cavity which are connected in series along the axial direction are arranged between the flame tube and the combustion chamber wall through a flow separation plate, the upstream ring cavity is a first ring cavity, the first ring cavity is communicated with an inner cavity of the flame tube through air holes formed in the flame tube wall and a combustor arranged at the combustion head part, the downstream ring cavity of the flow separation plate is a second ring cavity, and the second ring cavity is communicated with the inner cavity of the flame tube through the air holes formed in the flame tube wall; a flame tube outlet is connected with a heat exchanger through a smoke gas pipeline and is then respectively connected with a first ring cavity connector, a second ring cavity connector and a combustion chamber downstream part.
Description
Technical field
The present invention relates to submarine dynamic combustion field, relate to a kind of Multi-stage spiral combustion chamber with two-way backflow particularly.
Background technology
The burning head of known submarine dynamic combustion room is single turbulent burner, i.e. central fuel nozzle, and single-stage cyclone is offered in the outer ring of fuel nozzle.In fuel combination and oxidant, there is the problem that mixing is uneven, blending performance is not good in single-stage cyclone.The mixing inequality of fuel and oxidant causes the service behaviour of combustion chamber not good.In addition, between the burner inner liner of known this kind of combustion chamber and chamber wall, adopt radial dicyclo chamber form, the interior ring cavity flowing of this form be flue gas, what outer ring cavity flowed is oxidant, under this configuration, there is not afterburning oxidant in combustion chamber, causes the problem occurring that efficiency of combustion is on the low side.Also have between the burner inner liner of known this kind of combustion chamber and chamber wall and adopt monocycle chamber form, under this configuration, what ring cavity flowed is oxidant, and a large amount of oxidant is used for the afterbody blending of combustion chamber, causes combustion chamber to occur the problem that oxidant utilization is on the low side.
Summary of the invention
The object of this invention is to provide a kind of Multi-stage spiral combustion chamber with two-way backflow, to solve known technology Problems existing.
For achieving the above object, the Multi-stage spiral combustion chamber of band two-way backflow provided by the invention, comprises burning head, burner inner liner, cutoff board, chamber wall, heat exchanger and blender.Wherein:
Burning head offers the cyclone of fuel nozzle and multiple concentric radial arrangement;
The spout of fuel nozzle layout alternate with cyclone;
Radially adjoining cyclone is set to derotation to layout;
The wall of burner inner liner offers many steam vents, between burner inner liner and chamber wall, cutoff board is provided with in-line upstream and downstream two ring cavities vertically, upstream ring cavity is the first ring cavity, and the first ring cavity is by pore on flame tube wall and the burning burner of head and burner inner liner intracavity inter-connection;
Cutoff board downstream ring cavity is the second ring cavity, and the second ring cavity is by pore on flame tube wall and burner inner liner intracavity inter-connection;
Burner inner liner outlet connects heat exchanger by a flue, and be then divided into three passages, first passage is connected to blender by flow valve, is connected the first ring cavity interface of the first ring cavity by this blender; Second channel connects the second ring cavity interface of the second ring cavity by flow valve; Third channel connects downstream, combustion chamber.
Introduce the gaseous mixture being through the mixed flue gas of blender and oxidant of the first ring cavity, rear adverse current is entered to the head that burns in the middle part of burner inner liner, part gaseous mixture enters burner inner liner inner chamber by the fuel supplementing type pore on flame tube wall and cooling type pore on the way, and the burner of residue gaseous mixture on burning head enters burner inner liner inner chamber.Introduce after flue gas enters ring cavity in the second ring cavity, enter burner inner liner inner chamber by the mix type pore on flame tube wall and cooling type pore.
The Multi-stage spiral combustion chamber of described band two-way backflow, wherein, one or more fuel nozzle ports radially offered by fuel nozzle.
The Multi-stage spiral combustion chamber of described band two-way backflow, wherein, progression >=2 of cyclone.
The Multi-stage spiral combustion chamber of described band two-way backflow, wherein, cyclone is axial blade formula structure, radial blade formula structure, axially cut sth. askew cellular type structure or radial direction are cut sth. askew cellular type structure.
The Multi-stage spiral combustion chamber of described band two-way backflow, wherein, the outlet of cyclone connects mixing section.
The Multi-stage spiral combustion chamber of described band two-way backflow, wherein, cyclone outlet mixing section is expansion segment or Wen's pipeline section.
The Multi-stage spiral combustion chamber of described band two-way backflow, wherein, the type of cooling of burner inner liner is gaseous film control, disperses cooling or Compound cooling mode.
The advantage of the present invention compared with existing known technology is as follows:
(1) the present invention offers multiple cyclone at the burning head of combustion chamber body, radially adjoining cyclone adopts derotation to layout, cyclone layout alternate with fuel nozzle spout, to strengthen the rotational-flow shearing effect of burning head, strengthen mixing intensity, improve the mixing uniformity of fuel and oxidant.Solve the fuel of known technology existence and the uneven problem causing service behaviour not good of mixing of oxidant.
(2) smoke evacuation of combustion chamber of the present invention has two loops, after wherein a road flue gas mixes in a mixer with the oxidant of combustion chamber, be back to the first ring cavity, then to head of combustion chamber adverse current, wherein part gaseous mixture enters burner inner liner inner chamber by the fuel supplementing type pore on flame tube wall on the way, for aftercombustion still unburnt fuel herein, part gaseous mixture enters burner inner liner inner chamber by the cooling type pore on flame tube wall on the way, for cooling flame tube wall surface, the final adverse current of residue gaseous mixture is to the head that burns, burner inner liner inner chamber is entered by burner, for mixed fuel firing.This loop functions as follows: (a) backflow flue gas dilutes oxidant; reduce the combustion intensity in burner inner liner; protection burner inner liner is not burnt; extend the service life of combustion chamber; b () backflow flue gas preheating oxidant, improves the temperature of oxidant, thus reduce available energy loss; c () by head and the air inlet of fuel supplementing type pore reasonable distribution, can realize the object of abundant after-flame containing oxygen gas mixture.This loop utilizes flue gas to reduce ignition temperature, reduces irreversible loss, and reasonable distribution oxidant realizes the efficient burning of fuel simultaneously.
Another loop smoke backflow to the second ring cavity, partial fume enters burner inner liner inner chamber by the mix type pore on flame tube wall, for regulating burner inner liner Exit temperature distribution, residue flue gas enters burner inner liner inner chamber, for cooling flame tube wall surface by the cooling type pore on flame tube wall.This loop achieve when not oxygen consumed agent burner inner liner outlet temperature regulate and and the cooling of wall, saved the oxidant use amount of combustion chamber, improve the utilization rate of the oxidant of combustion chamber.
The dicyclo cavity configuration of the two-way smoke backflow that the present invention adopts and axial series, solves the problem that efficiency of combustion is on the low side and oxidant utilization is on the low side that known technology exists.
The Multi-stage spiral combustion chamber of band two-way backflow of the present invention, can improve the mixing uniformity of fuel and oxidant, enhanced burning performance, reduce Fuel Consumption; Can ignition temperature be reduced, extend burner inner liner service life; Oxidant initial temperature can be improved, reduce combustion chamber irreversible loss; Can reasonable distribution head and afterburning tolerance, realize efficient combustion; Can achieve when not oxygen consumed agent burner inner liner Exit temperature distribution regulate and and the cooling of wall, improve the utilization rate of combustion chamber inner oxidizing agent.
Accompanying drawing explanation
Fig. 1 is Multi-stage spiral chamber structure schematic diagram of the present invention.
Fig. 2 is the burning head figure of the embodiment of the present invention one;
Fig. 3 is the burning head figure of the embodiment of the present invention two.
Symbol description in accompanying drawing:
1 burning head; 2 burner inner liners; 3 cutoff boards; 4 chamber walls; 5 burners; 6 fuel nozzles; 7 cyclones; 8 first ring cavities; 9 second ring cavities; 10 first ring cavity interfaces; 11 second ring cavity interfaces; 12 heat exchangers; The flue gas that 13 burner inner liners are discharged; 14,15,16 flue gases; The blender of 17 oxidants and flue gas; 18 igniters; 19 first order cyclones; 20 second level cyclones; 21 mixing sections; 22,23,24 fuel nozzle ports; 25 fuel supplementing type pores; 26 mix type pores; 27 cooling type pores.
Detailed description of the invention
The Multi-stage spiral combustion chamber of band two-way backflow of the present invention, is made up of burning head, burner inner liner, cutoff board, chamber wall, heat exchanger and blender.Wherein, burning head offers the cyclone of fuel nozzle and multiple concentric radial arrangement, radially adjoining cyclone is set to derotation to layout, the alternate layout of spout of cyclone and fuel nozzle, to strengthen the rotational-flow shearing effect of burning head, strengthen mixing intensity, improve the mixing uniformity of fuel and oxidant.
The wall of burner inner liner offers many steam vents, between burner inner liner and chamber wall, cutoff board is provided with in-line upstream and downstream two ring cavities vertically, upstream ring cavity is the first ring cavity, and the first ring cavity is by pore on flame tube wall and the burning burner of head and burner inner liner intracavity inter-connection; Cutoff board downstream ring cavity is the second ring cavity, and the second ring cavity is by pore on flame tube wall and burner inner liner intracavity inter-connection.Burner inner liner outlet connects heat exchanger by a flue, and be then divided into three passages, first passage is connected to blender by flow valve, is connected the first ring cavity interface of the first ring cavity by this blender; Second channel connects the second ring cavity interface of the second ring cavity by flow valve; Third channel connects downstream, combustion chamber.Introduce the gaseous mixture being through the mixed flue gas of blender and oxidant of the first ring cavity, backward head of combustion chamber adverse current is entered in the middle part of burner inner liner, part gaseous mixture enters burner inner liner inner chamber by the fuel supplementing type pore on flame tube wall on the way, for aftercombustion still unburnt fuel herein, part gaseous mixture enters burner inner liner inner chamber by the cooling type pore on flame tube wall on the way, for cooling flame tube wall surface, the final adverse current of residue gaseous mixture is to the head that burns, burner inner liner inner chamber is entered, for mixed fuel firing by burner.What introduce the second ring cavity is pure flue gas, after flue gas enters ring cavity, partial fume enters burner inner liner inner chamber by the mix type pore on flame tube wall, for regulating burner inner liner Exit temperature distribution, residue flue gas enters burner inner liner inner chamber, for cooling flame tube wall surface by the cooling type pore on flame tube wall.The flue gas circuit being back to the first ring cavity dilutes oxidant; reduce the combustion intensity in burner inner liner; protection burner inner liner is not burnt; extend the service life of combustion chamber; simultaneously preheating oxidant, improves the temperature of oxidant, decreases combustion chamber available energy loss; in addition the gaseous mixture of oxidant and flue gas is by the reasonable distribution air inlet of head and fuel supplementing type pore, achieves the object of the abundant after-flame of fuel.The flue gas circuit being back to the second ring cavity achieve when not oxygen consumed agent burner inner liner Exit temperature distribution regulate and and the cooling of wall, saved the oxidant use amount of combustion chamber, improve the utilization rate of the oxidant of combustion chamber.
Below in conjunction with drawings and Examples, the present invention is further illustrated.
Embodiment one
Refer to Fig. 1 and Fig. 2, the structure of the embodiment of the present invention one is as follows:
Combustion chamber is single tube structure, is made up of burning head 1, burner inner liner 2, cutoff board 3, chamber wall 4, heat exchanger 12 and blender 17.Ring cavity between burner inner liner 2 and chamber wall 4 is divided into upstream and downstream two ring cavities by cutoff board 3, and cutoff board 3 upstream ring cavity is for being the first ring cavity 8, and cutoff board 3 downstream ring cavity is the second ring cavity 9.The air inlet of the first ring cavity 8 is the air inlet of the first ring cavity interface 10, second ring cavity 9 is the second ring cavity interface 11.Burning head 1 is made up of a burner 5, and burner 5 is made up of the cyclone 7 of the fuel nozzle 6 and outer ring that are arranged in its center, and wherein, fuel nozzle 6 arranges a spout; Cyclone 7 is made up of first order cyclone 19, second level cyclone 20 and mixing section 21, and mixing section 21 is connected with second level cyclone 20.First order cyclone 19 and second level cyclone 20 can be all axial blade formula structures, radial blade formula structure, axially cut sth. askew cellular type structure or radial direction are cut sth. askew cellular type structure.First order cyclone 19 is that derotation is to layout with the rotation direction of second level cyclone 20.The eddy flow progression of cyclone 7 is 2.Mixing section 21 can be expansion segment or Wen's pipeline section.After the flue gas 13 of discharging in burner inner liner 2 is cooled by pipeline and heat exchanger 12 heat exchange, be divided into three strands: one flue gas 14 is drained to blender 17 by exhaust gases passes, rear inflow first ring cavity interface 10 is being mixed with oxidant (pure oxygen), then the first ring cavity 8 is entered, and vertically to burning head 1 direction adverse current, part gaseous mixture enters the inner chamber of burner inner liner 2 by the fuel supplementing type pore 25 on burner inner liner 2 wall on the way, for aftercombustion still unburnt fuel herein, part gaseous mixture enters the inner chamber of burner inner liner 2 by the cooling type pore 27 on burner inner liner 2 wall, for cooling flame cylinder 2 wall, the final adverse current of residue gaseous mixture is to burning head 1, the inner chamber of burner inner liner 2 is entered by burner 5, again with fuel mix after by igniter 18 ignition.The flow of this strand of flue gas 14 is controlled by flow valve.Flue gas 14 1 aspect serves the effect of dilution oxidant (pure oxygen), reduces the combustion intensity in burner inner liner 2, and protection burner inner liner 2 is not burnt, and extends the service life of combustion chamber; Flue gas 14 plays the effect of preheated oxidant on the other hand, improves the temperature of oxidant, thus reduces available energy loss, and the gaseous mixture of flue gas 14 and oxidant is by the reasonable distribution air inlet of burn head 1 and fuel supplementing type pore 25 in addition, can realize the abundant after-flame of fuel.Another strand of flue gas 15 is back to the second ring cavity interface 11 by exhaust gases passes, enter the second ring cavity 9, then partial fume enters the inner chamber of burner inner liner 2 by the mix type pore 26 on burner inner liner 2 wall, play and regulate the effect of burner inner liner 2 Exit temperature distribution, residue flue gas enters the inner chamber of burner inner liner 2 by the cooling type pore 27 on burner inner liner 2 wall, reach the object of the wall of cooling flame cylinder 2, the flow of this strand of flue gas 15 is controlled by flow valve.One flue gas 16 last is directly discharged into downstream, combustion chamber.
The type of cooling of burner inner liner 2 can be gaseous film control, disperse cooling or Compound cooling mode.
Embodiment two
Refer to Fig. 1 and Fig. 3, be the structural representation of the embodiment of the present invention two, be that fuel nozzle 6 comprises the spout of multiple quantity with embodiment one difference, fuel nozzle ports layout alternate with cyclone.Illustrate three fuel nozzle ports 22,23,24 in figure 3, fuel nozzle ports 22,23,24 and the alternate layout of cyclone 19,20.All the other are with embodiment 1.
Claims (7)
1. the Multi-stage spiral combustion chamber with two-way backflow, comprises burning head, burner inner liner, cutoff board, chamber wall, heat exchanger and blender; Wherein:
Burning head offers the cyclone of fuel nozzle and multiple concentric radial arrangement;
The spout of fuel nozzle layout alternate with cyclone;
Radially adjoining cyclone is set to derotation to layout;
The wall of burner inner liner offers many steam vents, between burner inner liner and chamber wall, cutoff board is provided with in-line upstream and downstream two ring cavities vertically, upstream ring cavity is the first ring cavity, and the first ring cavity is by pore on flame tube wall and the burning burner of head and burner inner liner intracavity inter-connection;
Cutoff board downstream ring cavity is the second ring cavity, and the second ring cavity is by pore on flame tube wall and burner inner liner intracavity inter-connection;
Burner inner liner outlet connects heat exchanger by a flue, and be then divided into three passages, first passage is connected to blender by flow valve, is connected the first ring cavity interface of the first ring cavity by this blender; Second channel connects the second ring cavity interface of the second ring cavity by flow valve; Third channel connects downstream, combustion chamber.
Introduce the gaseous mixture being through the mixed flue gas of blender and oxidant of the first ring cavity, rear adverse current is entered to the head that burns in the middle part of burner inner liner, part gaseous mixture enters burner inner liner inner chamber by the fuel supplementing type pore on flame tube wall and cooling type pore on the way, and the burner of residue gaseous mixture on burning head enters burner inner liner inner chamber.Introduce after flue gas enters ring cavity in the second ring cavity, enter burner inner liner inner chamber by the mix type pore on flame tube wall and cooling type pore.
2. the Multi-stage spiral combustion chamber of band two-way backflow according to claim 1, wherein, one or more fuel nozzle ports radially offered by fuel nozzle.
3. the Multi-stage spiral combustion chamber of band two-way backflow according to claim 1, wherein, progression >=2 of cyclone.
4. the Multi-stage spiral combustion chamber of band two-way according to claim 1 backflow, wherein, cyclone is axial blade formula structure, radial blade formula structure, axially cut sth. askew cellular type structure or radial direction are cut sth. askew cellular type structure.
5. the Multi-stage spiral combustion chamber of band two-way backflow according to claim 1, wherein, the outlet of cyclone connects mixing section.
6. be with the Multi-stage spiral combustion chamber of two-way backflow according to claim 1 or 5, wherein, cyclone outlet mixing section is expansion segment or Wen's pipeline section.
7. the Multi-stage spiral combustion chamber of band two-way backflow according to claim 1, wherein, the type of cooling of burner inner liner is gaseous film control, disperses cooling or Compound cooling mode.
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| CN201510176794.1A CN104776451B (en) | 2015-04-14 | 2015-04-14 | A kind of Multi-stage spiral combustion chamber with two-way backflow |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108317541A (en) * | 2018-02-26 | 2018-07-24 | 中国科学院力学研究所 | A kind of punching engine |
| CN110836383A (en) * | 2019-11-15 | 2020-02-25 | 中国科学院工程热物理研究所 | High-temperature flue gas generator and control method thereof |
| CN113663419A (en) * | 2021-09-08 | 2021-11-19 | 四川金汇能新材料股份有限公司 | Tail gas treatment equipment |
| CN114188578A (en) * | 2021-12-14 | 2022-03-15 | 北京有恒能动科技有限公司 | Method for feeding gas into flame tube of solid oxide fuel cell system and combustion chamber thereof |
| CN114413283A (en) * | 2021-12-28 | 2022-04-29 | 北京动力机械研究所 | Integrated structure of cyclone sleeve and head plate |
| CN114526497A (en) * | 2022-01-07 | 2022-05-24 | 清华大学 | Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber |
| WO2023030467A1 (en) * | 2021-09-03 | 2023-03-09 | 永旭腾风新能源动力科技（北京）有限公司 | Combustion chamber having double fuel pipes and gas turbine |
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| CN204923078U (en) * | 2015-04-14 | 2015-12-30 | 中国科学院工程热物理研究所 | Multistage swirl flow combustion room based on flue gas circulating combustion |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108317541A (en) * | 2018-02-26 | 2018-07-24 | 中国科学院力学研究所 | A kind of punching engine |
| CN108317541B (en) * | 2018-02-26 | 2020-07-07 | 中国科学院力学研究所 | Ramjet engine |
| CN110836383A (en) * | 2019-11-15 | 2020-02-25 | 中国科学院工程热物理研究所 | High-temperature flue gas generator and control method thereof |
| CN110836383B (en) * | 2019-11-15 | 2021-10-26 | 中国科学院工程热物理研究所 | High-temperature flue gas generator and control method thereof |
| WO2023030467A1 (en) * | 2021-09-03 | 2023-03-09 | 永旭腾风新能源动力科技（北京）有限公司 | Combustion chamber having double fuel pipes and gas turbine |
| CN113663419A (en) * | 2021-09-08 | 2021-11-19 | 四川金汇能新材料股份有限公司 | Tail gas treatment equipment |
| CN114188578A (en) * | 2021-12-14 | 2022-03-15 | 北京有恒能动科技有限公司 | Method for feeding gas into flame tube of solid oxide fuel cell system and combustion chamber thereof |
| CN114188578B (en) * | 2021-12-14 | 2023-10-03 | 北京有恒能动科技有限公司 | Flame tube air inlet method of solid oxide fuel cell system and combustion chamber thereof |
| CN114413283A (en) * | 2021-12-28 | 2022-04-29 | 北京动力机械研究所 | Integrated structure of cyclone sleeve and head plate |
| CN114526497A (en) * | 2022-01-07 | 2022-05-24 | 清华大学 | Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber |
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