CN103196159B - Annular grading trapped vortex combustor - Google Patents
Annular grading trapped vortex combustor Download PDFInfo
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- CN103196159B CN103196159B CN201310086067.7A CN201310086067A CN103196159B CN 103196159 B CN103196159 B CN 103196159B CN 201310086067 A CN201310086067 A CN 201310086067A CN 103196159 B CN103196159 B CN 103196159B
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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, the specifically 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 large, lightweight and start the features such as fast, be widely used in the industrial core realms such as aviation, electric power, boats and ships and natural gas transport.Therefore, conventional combustion engine application technology is undergone technological transformation and performance optimization, become the important topic solving energy crisis and problem of environmental pollution.Chemical regenerative cycle is that combined cycle mode is steamed in the combustion of a kind of advanced person.The low side waste heat that it mainly utilizes combustion engine to be vented produces superheated vapor, utilize high-end waste heat to generate the high heating value fuel gas such as methane, hydrogen and carbon monoxide to impel the cracking under catalyst action of part fuel oil-steam, thus improve the average combustion low heat value of fuel.The working method of chemical regenerative cycle gas turbine (CRGT) determines that its entry of combustion chamber often has higher air velocity, therefore, requires that chemical recuperation cycle combustion chamber can have broad stable operation range.
The external existing advanced combustion technology with broad working range at present mainly contains VRT(VariableResidebce Time), UCC(Ultra-Compact) and TVC(Trapped Vortex Combustor) several types.
VRT combustion technology strengthens tangential admission speed in full toroidal combustion chamber, allows all air and fuel oil all tangentially enter annular flame tube to strengthen eddy flow circumferentially.Circumference eddy flow nozzle is injected fuel oil comparatively larger oil droplet under centrifugal action, rotate along burner inner liner outer periphery, have the long period to carry out evaporation mixing, until burning totally or replaced position by more larger oil droplet and enter internal layer burning, comparatively light oil mist then remains on the burning of internal layer circumference.Different for the oil droplet residence time in a combustion chamber of different size, thus improve the efficiency of combustion of whole combustion chamber, the origin of this also variable residence time VRT combustion technology just.This technology can reduce NO
xdischarge, circumferential blending eddy flow reduces combustor exit radial symmetry gradient.Owing to allowing air-flow with larger tangential velocity turnover combustion chamber, the effect of the guiding stator blade before blower outlet and turbine reduces, and the dimension and weight of engine is reduced to some extent.But circumferential eddy flow produces in whole burner inner liner in VRT, less stable, and be not suitable for the burning tissues under strong rotational flow inlet condition.
UCC combustion technology is mainly applied on constant temperature circulation (CT) and turbine inner burner (ITB), object drives the thrust loss of compressor to compensate combustion gas expansion work in turbine, its structure manufactures a circumferential cavity on Turbomachinery casing outer shroud, fuel oil and air is supplied in cavity, produce the circumferential flow air-flow that rotates around engine axis, and by the radial cavities on turbo blade by flame propagation in axial main flow.Produce large rotational flow around axis in 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 main flow by radial cavities, and extinguishing in radial cavities, main flow Zhong Zai poor oil firing, reduces disposal of pollutants.In very little space, combustion gas residence time is longer, and burning completely.Therefore UCC Flame Propagation speed, efficiency of combustion, heat liberation rate, heat release rate improve, and disposal of pollutants reduces, and the length of flame shortens, and enhances combustion stability.In addition, UCC is a kind of compensatory combustion technology being similar to after-burner, can not directly apply to main chamber.
TVC relies on the cavity frame for movement be located away from outside 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 is that main flow area provides a continuous and stable flame on duty and incendiary source in whirlpool.Cavity and primary zone form fractional combustion, and combustion system can adopt rich oil-extinguishing-poor oil firing's mode (RQL) decreasing pollution.Compared with traditional cyclone smooth combustion room, light a fire in TVC ground, light a fire in high-altitude and fuel-lean blowout performance all makes moderate progress again, and disposal of pollutants also reduces to some extent.But a kind of ancillary technique of TVC just to conventional combustion room, to the not any effect of the burning under strong rotational flow inlet condition.
Summary of the invention
The object of the present invention is to provide at reinforcement spray combustion, improve while efficiency of combustion, expand the classification toroidal combustion chamber in whirlpool be applicable under high speed condition for import of stable operation range.
The object of the present invention is achieved like this:
Classification of the present invention toroidal combustion chamber in whirlpool, 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 form combustor exit, the osculum end of outer casing and the osculum end of interior casing form air intlet, install combustion head in burner inner liner, burning head comprises fuel nozzle and three grades of axial swirlers, outer casing is arranged fuel duct import, fuel duct inlet communication fuel nozzle, burner inner liner arranges primary holes, blending hole, cooling effusion wall, primary holes is located at fuel nozzle downstream position, the center line of primary holes and the inclination angle of burner inner liner tangent to periphery are 15 °-75 °.
The present invention can also comprise:
1, three grades of described axial swirlers comprise a secondary wheel hub and three grades of wheel hubs, one secondary wheel hub is arranged on three grades of wheel hubs, level swirl vane and intergrade swirl vane in one secondary wheel hub is installed, interior level swirl vane is positioned in intergrade swirl vane, outer level swirl vane installed by three grades of wheel hubs, in three grades of wheel hubs, interior level Venturi tube and intergrade Venturi tube are set, level Venturi tube in interior level swirl vane connects, intergrade swirl vane connects intergrade Venturi tube, and interior level Venturi tube is positioned in intergrade Venturi tube.
2, blending hole is positioned at the position before combustor exit, and quantity is 10-100, and the inclination angle between the center line of blending hole and burning head is 15 °-75 °.
3, cooling effusion wall pore size is 0.5-1.2mm, on unit are flame tube wall, perforate number is 3000-12000, have the drift angle of 0 °-90 ° between cooling effusion wall and primary holes, the inclination angle between the center line of cooling effusion wall and burning head is 20 °-60 °.
4, air intlet place arranges diffuser, before fuel nozzle is positioned at three grades of axial swirlers, air-flow enters 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 effusion wall.
Advantage of the present invention is:
(1) there is the burning tissues form be more suitable for than conventional annular combustion chamber under high-speed rotational flow inlet condition, solve conventional annular combustion chamber technically and cut sth. askew that the smooth combustion scope only having single or symmetrical recirculating zone to cause that radial double cyclone, twin-stage axial swirler, radial two or the three grades of axial swirlers of one-level cause is narrower, low density problem of burning;
(2) swirl atomizer that adopts of head or air atomizer spray nozzle have extraordinary atomizing effect and local flame stabilization effect;
(3) have employed three grades of axial swirlers with new structure form, the multiple effect in whirlpool of generation can improve flame holding, has expanded smooth combustion working range.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is Longitudinal cross section schematic of the present invention;
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 whirlpool.
Detailed description of the invention
Below in conjunction with accompanying drawing citing, the present invention is described in more detail:
Composition graphs 1 ~ 4, classification of the present invention toroidal combustion chamber in whirlpool, have employed loopful shape flame tube structure, primarily of inside and outside casing and position in the inner inside and outside burner inner liner form, burner inner liner is circumferentially provided with the structures such as head, primary holes 6 and blending hole 5 outside.Wherein head comprises fuel nozzle 7 and three grades of axial swirlers 9, the outer level cyclone 23 of three grades of axial swirlers 9 and distant between interior level 13 and intergrade cyclone 20, ensure that the flow field between three swirler device can not interfere with each other, thereafter can produce multistage vortex structure, for stabilize the flame and the more fuel that burns very favourable; There is angle in primary holes 6 center line and tangent to periphery; Inside and outside blending hole 5 lays respectively at the position before inside and outside burner inner liner combustor exit, ensure that good Exit temperature distribution.
High velocity air enters after in combustion chamber, flows in the ring cavity that casing and burner inner liner are formed.Burner inner liner surface outside, multiple head and primary holes 6 are circumferentially set, primary holes 6 is arranged in head downstream position, head comprises fuel nozzle 7 and three grades of axial swirlers 9, different nozzles can be adopted under different charge oil pressures and flow, optionally there are swirl atomizer and air atomizer spray nozzle two kinds at present, the outer level cyclone 23 of three grades of axial swirlers and distant between interior level 19 and intergrade cyclone 20, ensure that the flow field between three swirler device 9 can not interfere with each other, thereafter multistage vortex structure can produced, for stabilize the flame and the more fuel that burns very favourable.Primary holes 6 provides sufficient air for rich oil flame jet, and air-flow enters the cavity that inside and outside burner inner liner circumferentially formed and tangentially flows, and forms annular maelstrom.In order to make the air-flow in cavity produce around the secondary micro cyclone of tangential maelstrom, the cooling effusion wall on burner inner liner and there is certain drift angle between primary holes 6 and tangential maelstrom, namely forms so-called orthogonal dual vortex.Whole burner inner liner 11 all adopts the effusion wall type of cooling, and the main purpose of cooling effusion wall utilizes cold air cooling flame cylinder 11, protects it not by combustion gas ablation.Fuel oil is by entering three swirler device 9 after the atomization of nozzle, low speed recirculating zone, local ignition after three swirler device 9, then enter in the vortex in cavity 12, circumferentially and radial propagation, high-temperature fuel gas is in blending hole place and the quick blending of cold air, and last eddy flow discharges combustion chamber 12.Blending hole 5 is arranged in the appropriate location before the outlet of combustion chamber 12, ensures its good Exit temperature distribution.
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 is formed, casing 4 is circumferentially evenly provided with fuel duct import 1 outside, according to different import tolerance, eddy flow degree and physical dimension requirement, the quantity of fuel feeding head is generally between 2-20, different nozzles can be adopted under different charge oil pressures and flow, optionally there are swirl atomizer and air atomizer spray nozzle two kinds at present, primary holes 6 is located at fuel nozzle 7 downstream position, 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 combustor exit 13, ensure its good Exit temperature distribution, mainly determine the blending hole perforate gross area according to blending hole tolerance, simultaneously according to the perforate size of the penetration depth design blending hole of blending jet, thus blending hole number can be determined, its quantity is roughly 10-100, and the inclination angle between the center line of blending hole 5 and head is 15 °-75 °, the barrel of burner inner liner has multiple cooling effusion wall, its aperture is 0.5-1.2mm to size, its perforate gross area is determined according to cooling tolerance, perforate number 3000-12000 on unit are cooling wall, in order to produce the secondary micro cyclone of some strength, the drift angle having 0 °-90 ° between hole and primary holes is trembled in cooling more, the inclination angle of cooling effusion wall 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 whirlpool being formed thereafter, and then forms multiple recirculating zone and be used for steady air flow, makes to realize smooth combustion in combustion chamber.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 by interior level swirl vane 14, intergrade swirl vane 15, one secondary wheel hub 16, 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 forms.Air-flow, after cyclone effect, multistagely stays whirlpool being formed thereafter, and then forms multiple recirculating zone and be used for steady air flow, makes to realize smooth combustion in combustion chamber.
As shown in Figure 5, outside after level cyclone, define two little formula in whirlpool recirculating zones, after intergrade and interior level cyclone, define a pair Central backflow area.The classification formula in volute that these recirculating zones are formed can make the high velocity air speed entered from import be reduced to the velocity amplitude being enough to realize flame stabilization.
Claims (5)
1. classification toroidal combustion chamber in whirlpool, 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 form combustor exit, the osculum end of outer casing and the osculum end of interior casing form air intlet, install combustion head in burner inner liner, burning head comprises fuel nozzle and three grades of axial swirlers, outer casing is arranged fuel duct import, fuel duct inlet communication fuel nozzle, burner inner liner arranges primary holes, blending hole, cooling effusion wall, primary holes is located at fuel nozzle downstream position, the center line of primary holes and the inclination angle of burner inner liner tangent to periphery are 15 °-75 °,
Three grades of described axial swirlers comprise a secondary wheel hub and three grades of wheel hubs, one secondary wheel hub is arranged on three grades of wheel hubs, level swirl vane and intergrade swirl vane in one secondary wheel hub is installed, interior level swirl vane is positioned in intergrade swirl vane, outer level swirl vane installed by three grades of wheel hubs, in three grades of wheel hubs, interior level Venturi tube and intergrade Venturi tube are set, level Venturi tube in interior level swirl vane connects, intergrade swirl vane connects intergrade Venturi tube, and interior level Venturi tube is positioned in intergrade Venturi tube.
2. classification according to claim 1 toroidal combustion chamber in whirlpool, is characterized in that: blending hole is positioned at the position before combustor exit, and quantity is 10-100, and the inclination angle between the center line of blending hole and burning head is 15 °-75 °.
3. classification according to claim 1 and 2 toroidal combustion chamber in whirlpool, it is characterized in that: cooling effusion wall pore size is 0.5-1.2mm, on unit are flame tube wall, perforate number is 3000-12000, have the drift angle of 0 °-90 ° between cooling effusion wall and primary holes, the inclination angle between the center line of cooling effusion wall and burning head is 20 °-60 °.
4. classification according to claim 1 and 2 toroidal combustion chamber in whirlpool, it is characterized in that: air intlet place arranges diffuser, before fuel nozzle is positioned at three grades of axial swirlers, air-flow enters 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 effusion wall.
5. classification according to claim 3 toroidal combustion chamber in whirlpool, it is characterized in that: air intlet place arranges diffuser, before fuel nozzle is positioned at three grades of axial swirlers, air-flow enters 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 effusion wall.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310086067.7A CN103196159B (en) | 2013-03-18 | 2013-03-18 | Annular grading trapped vortex combustor |
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| CN201310086067.7A CN103196159B (en) | 2013-03-18 | 2013-03-18 | Annular grading trapped vortex combustor |
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| CN103196159A CN103196159A (en) | 2013-07-10 |
| CN103196159B true CN103196159B (en) | 2015-03-11 |
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| CN115355540B (en) * | 2022-08-05 | 2023-06-20 | 中国航发沈阳发动机研究所 | Three-swirl main combustion chamber of aero-engine |
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