CN103196159A - Annular grading trapped vortex combustor - Google Patents
Annular grading trapped vortex combustor Download PDFInfo
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- CN103196159A CN103196159A CN2013100860677A CN201310086067A CN103196159A CN 103196159 A CN103196159 A CN 103196159A CN 2013100860677 A CN2013100860677 A CN 2013100860677A CN 201310086067 A CN201310086067 A CN 201310086067A CN 103196159 A CN103196159 A CN 103196159A
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Abstract
The invention aims to provide an annular grading trapped vortex combustor which comprises an outer casing and an inner casing. Both the outer casing and the inner casing adopt annular structures with large opening ends and small opening ends; inner walls of the outer casing and the inner casing form a flame tube; the large opening ends of the outer casing and the inner casing form a combustor outlet, and the small opening ends of the outer casing and the inner casing form an air inlet; a combustion head part is mounted in the flame tube and comprises a fuel nozzle and a three-level axial hydrocyclone; a fuel duct inlet is formed in the outer casing and communicated with the fuel nozzle; main combustion holes, mixing holes and a plurality of inclined cooling holes are formed in the flame tube; the main combustion holes are formed in the downstream position of the fuel nozzle, and the inclined angles formed by the center lines of the main combustion holes and the circumferential tangent line of the flame tube are in a range from 15 degrees to 75 degrees. Compared with a conventional annular combustor, the annular grading trapped vortex combustor is more suitable for combustion under the condition of a high-speed swirling flow inlet, produces multiple trapped vortex effects, and can improve the stability of flame and enlarge the working range of stable combustion.
Description
Technical field
What the present invention relates to is a kind of gas turbine, specifically the combustion chamber of gas turbine.
Background technology
Gas turbine is a kind of typical conventional fuel power set.It has that volume is little, power is big, in light weight and start characteristics such as fast, be widely used in the industrial core realms such as aviation, electric power, boats and ships and natural gas transport.Therefore, routine combustion machine application technology is undergone technological transformation and performance optimization, become the important topic that solves energy crisis and problem of environmental pollution.The chemical back heating circulation is that the combined cycle mode is steamed in a kind of advanced person's combustion.It mainly utilizes the low side waste heat of combustion machine exhaust to produce superheated vapor, utilize high-end waste heat to impel the cracking under catalyst action of part fuel oil-steam to generate high heating value fuel gas such as methane, hydrogen and carbon monoxide, thereby improve the average lower heat of combustion of fuel.The working method of chemical back heating cycle combustion turbine (CRGT) determines its entry of combustion chamber often to have higher air velocity, therefore, requires the chemical back heating gas-turbine combustion chamber can have broad stable operation range.
External existing advanced combustion technology with broad working range at present mainly contains VRT(Variable Residebce Time), UCC(Ultra-Compact) and TVC(Trapped Vortex Combustor) several types.
The VRT combustion technology strengthens tangential admission speed in loopful shape combustion chamber, allow all air and fuel oil all tangentially enter annular flame tube to strengthen along circumferential eddy flow.Circumferentially eddy flow make fuel oil that nozzle injects than larger oil droplet under centrifugal action, rotate along the burner inner liner outer periphery, there is the long period to carry out evaporation mixing, totally or by larger oil droplet more replaces the position and enter the internal layer burning up to burning, then remain on the burning of internal layer circumference than the light oil mist.For the residence times of oil droplet in the combustion chamber of different sizes and different, thereby improve the efficiency of combustion of whole combustion chamber, this is the origin of variable residence time VRT combustion technology just also.This technology can reduce NO
XDischarging, circumferentially the blending eddy flow reduces the combustor exit radial symmetry gradient.Because allow air-flow with big tangential velocity turnover combustion chamber, the effect of the guiding stator blade before blower outlet and the turbine reduces, and the dimension and weight of engine is reduced to some extent.But among the VRT circumferentially eddy flow in whole burner inner liner, produce less stable, and be not suitable for burning tissue under the strong eddy flow condition for import.
The UCC combustion technology mainly is to be applied on constant temperature circulation (CT) and the turbine inner burner (ITB), purpose is to drive the thrust loss of compressor in order to compensate the combustion gas acting of expanding in turbine, its structure is to make a circumferential cavity at turbine stator blade casing outer shroud, supply fuel oil and air in cavity, the circumferential flow air-flow that generation is rotated around engine axis, and by the radial cavities on the turbo blade with flame propagation in axial main flow.Produce big rotational flow around axis in the cavity, strengthen the blending of oil gas and combustion gas.Fuel-rich combustion in circumferential cavity, and as stable incendiary source, combustion product is transferred in the main flow by radial cavities, extinguishing in radial cavities, poor oil firing again in the main flow has reduced disposal of pollutants.The combustion gas residence time is longer in very little space, and burning fully.Therefore flame propagation velocity, efficiency of combustion, heat liberation rate, heat release rate improve among the UCC, and disposal of pollutants reduces, and the length of flame shortens, and has strengthened combustion stability.In addition, UCC is a kind of compensatory combustion technology that is similar to after-burner, can not directly apply to main chamber.
TVC relies on the cavity frame for movement that is located away from outside the main flow chamber to stablize swirling air stream, and sprays into fuel in cavity, and main flow area is by high-speed air, and its import also has fuel to spray into, and stays the whirlpool and provides continuous and stable flame on duty and an incendiary source for main flow area.Cavity and primary zone form fractional combustion, and combustion system can adopt rich oil-extinguishing-poor oil firing's mode (RQL) to reduce pollution.Compare with traditional cyclone smooth combustion chamber, light a fire in TVC ground, light a fire in the high-altitude and the fuel-lean blowout performance all makes moderate progress again, and disposal of pollutants also reduces to some extent.But TVC just to a kind of ancillary technique of conventional combustion chamber, does not have any effect to the burning under the strong eddy flow condition for import.
Summary of the invention
The object of the present invention is to provide when strengthening spray combustion, improving efficiency of combustion, expand classification shape in the collar vortex combustion chamber under the high speed condition for import of being applicable to of stable operation range.
The object of the present invention is achieved like this:
Classification of the present invention shape in collar vortex combustion chamber, it is characterized in that: comprise outer casing and interior casing, outer casing and interior casing are the loop configuration with big opening end and osculum end, the inwall of outer casing and the inwall of interior casing form burner inner liner, the big opening end of outer casing and the big opening end of interior casing constitute combustor exit, the osculum end of outer casing and the osculum end of interior casing constitute air intlet, install combustion head in the burner inner liner, the burning head comprises fuel nozzle and three grades of axial swirlers, the fuel duct import is set on the outer casing, the fuel duct import is communicated with fuel nozzle, primary holes is set on the burner inner liner, blending hole, cool off many inclined holes, primary holes is located at the fuel nozzle downstream position, and the inclination angle of the center line of primary holes and burner inner liner tangent to periphery is 15 °-75 °.
The present invention can also comprise:
1, described three grades of axial swirlers comprise a secondary wheel hub and three grades of wheel hubs, one secondary wheel hub is installed on three grades of wheel hubs, level swirl vane and intergrade swirl vane in installing on the one secondary wheel hub, an interior level swirl vane is positioned in the intergrade swirl vane, outer level swirl vane is installed on three grades of wheel hubs, level Venturi tube and intergrade Venturi tube in arranging in three grades of wheel hubs, level Venturi tube in interior level swirl vane connects, the intergrade swirl vane connects the intergrade Venturi tube, and interior level Venturi tube is positioned in the intergrade Venturi tube.
2, blending hole is positioned at the preceding position of combustor exit, and quantity is 10-100, and the inclination angle between the center line of blending hole and the burning head is 15 °-75 °.
3, many inclined holes of cooling pore size is 0.5-1.2mm, the perforate number is 3000-12000 on the unit are flame tube wall, cooling off has 0 °-90 ° drift angle between many inclined holes and the primary holes, cooling off the center line of many inclined holes and the inclination angle between the burning head is 20 °-60 °.
4, the air intlet place arranges diffuser, before fuel nozzle is positioned at three grades of axial swirlers, air-flow enters the burning head from air intlet through diffuser, the tolerance of 2%-20% enters burner inner liner from three grades of axial swirlers, the tolerance of 2%-25% enters burner inner liner from primary holes, the tolerance of 20%-70% enters burner inner liner from blending hole, and the tolerance of 20%-60% enters burner inner liner from cooling off many inclined holes.
Advantage of the present invention is:
(1) has than conventional toroidal combustion chamber and be more suitable for burning organizational form under high-speed eddy flow condition for import, solved conventional toroidal combustion chamber radially two or three grades of narrower, the low density problems of burning of the smooth combustion scope that only has single or symmetrical recirculating zone to cause that axial swirler causes of twin-stage cyclone, twin-stage axial swirler, one-level of cutting sth. askew radially technically;
(2) swirl atomizer or the air atomizer spray nozzle that adopt of head has extraordinary atomizing effect and local flame stabilization effect;
(3) adopted three grades of axial swirlers with new structure form, the multiple effect in the whirlpool of generation can improve flame holding, has expanded the smooth combustion working range.
Description of drawings
Fig. 1 is structural representation of the present invention;
Fig. 2 is longitudinal section of the present invention schematic diagram;
Fig. 3 is three grades of axial swirler structural representations of the present invention;
Fig. 4 is three grades of axial swirler cross sectional representation of the present invention;
Fig. 5 is classification of the present invention schematic diagram in the whirlpool.
The specific embodiment
For example the present invention is done description in more detail below in conjunction with accompanying drawing:
In conjunction with Fig. 1～4, loopful shape burner inner liner structure has been adopted in classification of the present invention shape in collar vortex combustion chamber, mainly is made of inside and outside casing and the inside and outside burner inner liner that is positioned at it, and burner inner liner is along structures such as head, primary holes 6 and blending hole 5 circumferentially are installed outside.Wherein head comprises fuel feeding nozzle 7 and three grades of axial swirlers 9, distance is far away between the outer level cyclone 23 of three grades of axial swirlers 9 and interior level 13 and the intergrade cyclone 20, guaranteed that the flow field between the three swirler device can not interfere with each other, can produce multistage vortex structure thereafter, very favourable for the retention flame and the more fuel of burning; There are angle in primary holes 6 center lines and tangent to periphery; Inside and outside blending hole 5 lays respectively at the position before the inside and outside burner inner liner combustor exit, has guaranteed that good outlet temperature distributes.
After high velocity air enters in the combustion chamber, in the ring cavity of casing and burner inner liner formation, flow.Burner inner liner surface outside, along circumference a plurality of heads and primary holes 6 are set, primary holes 6 is arranged in the head downstream position, head comprises fuel feeding nozzle 7 and three grades of axial swirlers 9, under different charge oil pressures and flow, can adopt different nozzles, two kinds of swirl atomizer and air atomizer spray nozzles are optionally arranged at present, distance is far away between the outer level cyclone 23 of three grades of axial swirlers and interior level 19 and the intergrade cyclone 20, guaranteed that the flow field between the three swirler device 9 can not interfere with each other, can produce multistage vortex structure thereafter, very favourable for the retention flame and the more fuel of burning.Primary holes 6 provides sufficient air for the rich oil flame jet, and air-flow enters inside and outside burner inner liner and tangentially flows along the cavity that circumferentially forms, and forms annular maelstrom.In order to make air-flow in the cavity produce secondary micro cyclone around tangential maelstrom, the many inclined holes of the cooling on the burner inner liner and primary holes 6 with tangentially have certain drift angle between the maelstrom, namely form the dual vortex of so-called quadrature.Whole burner inner liner 11 all adopts many inclined holes type of cooling, and the main purpose of cooling off many inclined holes is to utilize cold air cooling burner inner liner 11, protects it not ablated by combustion gas.Enter three swirler device 9 after the atomizing of fuel oil by nozzle, local low speed recirculating zone ignition behind three swirler device 9 enters in the vortex in the cavity 12, along circumferential and radial propagation again, high-temperature fuel gas is in blending hole place and the quick blending of cold air, and last eddy flow is discharged combustion chamber 12.Blending hole 5 is arranged in the appropriate location before 12 outlets of combustion chamber, guarantees that its good outlet temperature distributes.
The present invention is by fuel duct import 1, air intlet 2, interior casing 3, outer casing 4, blending hole 5, primary holes 6, fuel nozzle 7, diffuser 8, three grades of axial swirlers 9, fuel duct 10, burner inner liner 11, combustion chamber 12, combustor exit 13, interior level swirl vane 14, intergrade swirl vane 15,1 one secondary wheel hubs 6, outer level swirl vane 17, three grades of wheel hubs 18, interior level axial swirler 19, intergrade axial swirler 20, intergrade Venturi tube 21, interior level Venturi tube 22, outer level axial swirler 23 constitutes, casing 4 is along fuel duct import 1 circumferentially evenly is installed outside, according to different import tolerance, eddy flow degree and physical dimension requirement, the quantity of fuel feeding head is generally between 2-20, under different charge oil pressures and flow, can adopt different nozzles, two kinds of swirl atomizer and air atomizer spray nozzles are optionally arranged at present; Primary holes 6 is located at fuel nozzle 7 downstream positions, and the center line of primary holes 6 and the inclination angle of tangent to periphery are 15 °-75 °; Head comprises fuel nozzle 7 and three grades of axial swirlers 9; Blending hole 5 is positioned at the position before the combustor exit 13, guarantee that its good outlet temperature distributes, mainly determine the blending hole perforate gross area according to blending hole tolerance, design the perforate size of blending hole simultaneously according to the penetration depth of blending jet, thereby can determine the blending hole number, its quantity is roughly 10-100, and the center line of blending hole 5 and the inclination angle between the head are 15 °-75 °; Have the many inclined holes of a plurality of coolings on the barrel of burner inner liner, its aperture is 0.5-1.2mm to size, determine its perforate gross area according to cooling tolerance, perforate number 3000-12000 on the unit are cooling wall, in order to produce the secondary micro cyclone of certain intensity, cooling is trembled more 0 °-90 ° drift angle between hole and the primary holes; The inclination angle of cooling off many inclined holes is 20 °-60 °.Air-flow enters head of combustion chamber from air intlet 2 through diffuser 8, and the tolerance of about 2%-20% enters from three grades of axial swirlers 9, and multistagely stays the whirlpool forming thereafter, and then forms a plurality of recirculating zones and be used for steady air flow, makes the realization smooth combustion combustion chamber in.Its residual volume allocation rule is: primary holes tolerance 2%-25%, blending hole tolerance 20%-70%, cooling tolerance 20%-60%.
As Fig. 3, shown in 4, cyclone is by interior level swirl vane 14, intergrade swirl vane 15, one secondary wheel hub 16,17, three grades of wheel hubs 18 of outer level swirl vane, interior level axial swirler 19, intergrade axial swirler 20, intergrade Venturi tube 21, interior level Venturi tube 22, outer level axial swirler 23 is formed.Air-flow is multistagely stayed the whirlpool forming thereafter after the cyclone effect, and then forms a plurality of recirculating zones and be used for steady air flow, makes the realization smooth combustion combustion chamber in.
As shown in Figure 5, behind the level cyclone, form two little formula in whirlpool recirculating zones outside, behind intergrade and interior level cyclone, formed recirculating zone, a pair of center.Classification formula in the volute that these several recirculating zones form can make the high velocity air speed that enters from import be reduced to the velocity amplitude that is enough to realize flame stabilization.
Claims (9)
1. classification shape in collar vortex combustion chamber, it is characterized in that: comprise outer casing and interior casing, outer casing and interior casing are the loop configuration with big opening end and osculum end, the inwall of outer casing and the inwall of interior casing form burner inner liner, the big opening end of outer casing and the big opening end of interior casing constitute combustor exit, the osculum end of outer casing and the osculum end of interior casing constitute air intlet, install combustion head in the burner inner liner, the burning head comprises fuel nozzle and three grades of axial swirlers, the fuel duct import is set on the outer casing, the fuel duct import is communicated with fuel nozzle, primary holes is set on the burner inner liner, blending hole, cool off many inclined holes, primary holes is located at the fuel nozzle downstream position, and the inclination angle of the center line of primary holes and burner inner liner tangent to periphery is 15 °-75 °.
2. classification according to claim 1 shape in collar vortex combustion chamber, it is characterized in that: described three grades of axial swirlers comprise a secondary wheel hub and three grades of wheel hubs, one secondary wheel hub is installed on three grades of wheel hubs, level swirl vane and intergrade swirl vane in installing on the one secondary wheel hub, an interior level swirl vane is positioned in the intergrade swirl vane, outer level swirl vane is installed on three grades of wheel hubs, level Venturi tube and intergrade Venturi tube in arranging in three grades of wheel hubs, level Venturi tube in interior level swirl vane connects, the intergrade swirl vane connects the intergrade Venturi tube, and interior level Venturi tube is positioned in the intergrade Venturi tube.
3. classification according to claim 1 and 2 shape in collar vortex combustion chamber is characterized in that: blending hole is positioned at the position before the combustor exit, and quantity is 10-100, and the center line of blending hole is 15 °-75 ° with the inclination angle of burning between the head.
4. classification according to claim 1 and 2 shape in collar vortex combustion chamber, it is characterized in that: cooling off many inclined holes pore size is 0.5-1.2mm, the perforate number is 3000-12000 on the unit are flame tube wall, cooling off has 0 °-90 ° drift angle between many inclined holes and the primary holes, cooling off the center line of many inclined holes and the inclination angle between the burning head is 20 °-60 °.
5. classification according to claim 3 shape in collar vortex combustion chamber, it is characterized in that: cooling off many inclined holes pore size is 0.5-1.2mm, the perforate number is 3000-12000 on the unit are flame tube wall, cooling off has 0 °-90 ° drift angle between many inclined holes and the primary holes, cooling off the center line of many inclined holes and the inclination angle between the burning head is 20 °-60 °.
6. classification according to claim 1 and 2 shape in collar vortex combustion chamber, it is characterized in that: the air intlet place arranges diffuser, before fuel nozzle is positioned at three grades of axial swirlers, air-flow enters the burning head from air intlet through diffuser, the tolerance of 2%-20% enters burner inner liner from three grades of axial swirlers, the tolerance of 2%-25% enters burner inner liner from primary holes, and the tolerance of 20%-70% enters burner inner liner from blending hole, and the tolerance of 20%-60% enters burner inner liner from cooling off many inclined holes.
7. classification according to claim 3 shape in collar vortex combustion chamber, it is characterized in that: the air intlet place arranges diffuser, before fuel nozzle is positioned at three grades of axial swirlers, air-flow enters the burning head from air intlet through diffuser, the tolerance of 2%-20% enters burner inner liner from three grades of axial swirlers, the tolerance of 2%-25% enters burner inner liner from primary holes, and the tolerance of 20%-70% enters burner inner liner from blending hole, and the tolerance of 20%-60% enters burner inner liner from cooling off many inclined holes.
8. classification according to claim 4 shape in collar vortex combustion chamber, it is characterized in that: the air intlet place arranges diffuser, before fuel nozzle is positioned at three grades of axial swirlers, air-flow enters the burning head from air intlet through diffuser, the tolerance of 2%-20% enters burner inner liner from three grades of axial swirlers, the tolerance of 2%-25% enters burner inner liner from primary holes, and the tolerance of 20%-70% enters burner inner liner from blending hole, and the tolerance of 20%-60% enters burner inner liner from cooling off many inclined holes.
9. classification according to claim 5 shape in collar vortex combustion chamber, it is characterized in that: the air intlet place arranges diffuser, before fuel nozzle is positioned at three grades of axial swirlers, air-flow enters the burning head from air intlet through diffuser, the tolerance of 2%-20% enters burner inner liner from three grades of axial swirlers, the tolerance of 2%-25% enters burner inner liner from primary holes, and the tolerance of 20%-70% enters burner inner liner from blending hole, and the tolerance of 20%-60% enters burner inner liner from cooling off many inclined holes.
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| CN201310086067.7A CN103196159B (en) | 2013-03-18 | 2013-03-18 | Annular grading trapped vortex combustor |
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| CN104930689A (en) * | 2015-06-30 | 2015-09-23 | 孔令斌 | Oil and gas fired boiler having annular combustion chamber |
| CN105020744A (en) * | 2015-07-06 | 2015-11-04 | 南京航空航天大学 | Inclined-flow trapped-vortex combustor |
| CN106051826A (en) * | 2016-06-12 | 2016-10-26 | 哈尔滨工程大学 | Pyrolysis fuel gas and air rapid mixing device |
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| CN111649354B (en) * | 2020-06-15 | 2022-03-29 | 江苏科技大学 | Three-cyclone classification cyclone and combustion chamber thereof |
| CN111649354A (en) * | 2020-06-15 | 2020-09-11 | 江苏科技大学 | Three-cyclone classification cyclone and combustion chamber thereof |
| CN113310071A (en) * | 2021-06-16 | 2021-08-27 | 哈尔滨工程大学 | Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine |
| CN113324262A (en) * | 2021-06-16 | 2021-08-31 | 哈尔滨工程大学 | Coaxial staged gas fuel combustor head for low emission gas turbine |
| CN113803743A (en) * | 2021-09-15 | 2021-12-17 | 中国联合重型燃气轮机技术有限公司 | Secondary combustion device and combustion chamber and gas turbine with same |
| 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 |
| CN114526497B (en) * | 2022-01-07 | 2023-02-07 | 清华大学 | Double-necking combined spiral-flow type center-grading high-temperature-rise combustion chamber |
| CN114777161A (en) * | 2022-04-11 | 2022-07-22 | 南京航空航天大学 | Inclined combustion chamber scheme for integrated design of coupling compressor and turbine |
| CN115095885A (en) * | 2022-06-06 | 2022-09-23 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI oblique-feeding combustion chamber |
| CN115095885B (en) * | 2022-06-06 | 2024-02-09 | 中国船舶集团有限公司系统工程研究院 | Combined multi-point LDI inclined combustion chamber |
| CN115143489A (en) * | 2022-06-15 | 2022-10-04 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale cyclone air intake |
| CN115143489B (en) * | 2022-06-15 | 2023-08-11 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale rotational flow air intake |
| CN115355540A (en) * | 2022-08-05 | 2022-11-18 | 中国航发沈阳发动机研究所 | Three-cyclone main combustion chamber of aero-engine |
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