CN106705122A - Nozzle with inner and outer mixing zones, nozzle array and burner - Google Patents
Nozzle with inner and outer mixing zones, nozzle array and burner Download PDFInfo
- Publication number
- CN106705122A CN106705122A CN201611136457.0A CN201611136457A CN106705122A CN 106705122 A CN106705122 A CN 106705122A CN 201611136457 A CN201611136457 A CN 201611136457A CN 106705122 A CN106705122 A CN 106705122A
- Authority
- CN
- China
- Prior art keywords
- nozzle
- wave
- cylinder
- wall
- nozzles
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000002156 mixing Methods 0.000 title claims abstract description 60
- 238000002485 combustion reaction Methods 0.000 claims abstract description 50
- 239000000446 fuel Substances 0.000 claims abstract description 34
- 239000000203 mixture Substances 0.000 claims abstract description 29
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000009792 diffusion process Methods 0.000 claims description 11
- 230000007704 transition Effects 0.000 claims description 4
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 claims description 2
- 239000003344 environmental pollutant Substances 0.000 abstract description 9
- 231100000719 pollutant Toxicity 0.000 abstract description 9
- 230000009471 action Effects 0.000 abstract description 4
- 238000010992 reflux Methods 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 8
- 239000007789 gas Substances 0.000 description 5
- 230000007547 defect Effects 0.000 description 4
- 238000009966 trimming Methods 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000001704 evaporation Methods 0.000 description 2
- 230000008020 evaporation Effects 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000005496 tempering Methods 0.000 description 2
- 238000007084 catalytic combustion reaction Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000036632 reaction speed Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention provides a nozzle with inner and outer mixing zones. The nozzle is characterized in that wave cyclones are coaxially arranged in an outer wall cylinder; a middle cylinder is embedded in the wave cyclones; the wave cyclones are cut into inner ring cyclone structures and outer ring cyclone structures; the inner ring cyclone structures, the outer ring cyclone structures and the middle cylinder and the outer wall cylinder define an inner runner and an outer runner, and the inner mixing zone and the outer mixing zone are formed; and combustible mixtures of the inner runner and the outer runner are mixed in an outlet mixing zone. According to the nozzle, fuel and air are not mixed before entering the nozzle, the combustible mixture of the outer mixing zone performs rotational motion, the combustible mixture can form expanded flames at a nozzle outlet under the action of centrifugal force, and combustion stability is improved; and combustible objects flowing from a middle cylinder outlet zone performs irrotational axial motion, a strong reflux zone can be prevented from forming at the outlet of the nozzle, flow loss is reduced, pollutant discharge is reduced, the nozzle has good combustion stability, and low pollutant discharge is achieved.
Description
Technical Field
The invention relates to the technical field of combustion devices, in particular to a nozzle, a nozzle array and a combustor with an internal and external mixing area, which are particularly suitable for various industrial combustors such as gas turbines, boilers, chemical furnaces and the like.
Background
The gas turbine is widely applied to industries such as electric power, aviation, petrochemical industry and the like due to the characteristics of small single machine volume, large output power and the like. Due to energy crisis and environmental deterioration, there is an urgent need to develop efficient and clean combustion chambers, which are required to have the characteristics of reliable ignition, stable combustion, high efficiency, low emission, etc. At present, the environmental pollution problem in China is very serious, and the development of clean combustion technology of a gas turbine is very urgent. Gas turbine manufacturers have developed various clean combustion technologies, such as lean premixed combustion technology, dilute premixed pre-evaporation technology, lean direct injection technology, catalytic combustion technology, etc., which are effective in reducing pollutant emissions but are all confronted with the problem of unstable combustion. A radial staged combustion technique for liquid fuel combustion, as developed by the united states general company, is effective in reducing nitric oxide emissions. However, since the main flame is stabilized at the low-speed edge of the shear layer, periodic vortex shedding occurs near the low-speed region of the shear layer, oscillation occurs easily near the stable point, and unstable combustion occurs easily when the fuel tank is operated under off-design conditions. Similar to gas turbine combustors, other types of industrial combustors also face the contradiction between stable combustion and reduced pollutant emissions.
The diffusion combustion has the advantages of no backfire phenomenon in operation, high safety coefficient, stable and reliable operation, easy ignition, heat load adjustment, wider heat load adjustable range and the like, and has the defects that the diffusion combustor has longer flame length and low heat release intensity per unit volume because air and fuel gas are contacted with each other to generate chemical reaction only by diffusion during combustion. The premixed combustion has the advantages that pollutant emission can be reduced through technologies such as lean premixed combustion, dilute phase premixed pre-evaporation and the like, due to the fact that fuel and oxidant are premixed, the influence of mixing time scale on combustion reaction is basically negligible, the combustion reaction speed and flame propagation speed are greatly improved, the defects are that flame stability is poor, and potential safety hazards are caused by tempering, particularly the tempering problem is more prominent when the flame propagation speed of the fuel is high, such as combustion of hydrogen or hydrogen-rich fuel.
Thus, a need exists for a combustor that combines the advantages of diffusion combustion and premixed combustion.
Disclosure of Invention
Technical problem to be solved
In order to solve the above problems in the prior art, the present invention provides a nozzle, a nozzle array and a burner having both an internal and external mixing region.
(II) technical scheme
The invention provides a nozzle with an internal and external mixing area, which comprises: the device comprises a middle cylinder, an outer wall cylinder, a mesh plate and a wave cyclone; wherein the wave swirler is coaxially arranged in the outer wall cylinder; the middle cylinder is embedded into the wave cyclone from the outlet end of the wave cyclone along the axial direction of the wave cyclone, and the wave cyclone is divided into an inner ring cyclone structure and an outer ring cyclone structure; the outer ring rotational flow structure, the middle cylinder and the outer wall cylinder enclose an outer flow passage, and the inner ring rotational flow structure and the middle cylinder enclose an inner flow passage; the mesh plate is arranged in the middle cylinder, an inner blending area is formed between the mesh plate and the outlet end of the wave cyclone, and the inner blending area is communicated with the inner flow passage; the outer wall cylinder, the outlet ends of the wave cyclones and the middle cylinder form an outer mixing area in a surrounding mode, the outer mixing area is communicated with the outer flow channel, and the part, protruding out of the middle cylinder, of the outer wall cylinder forms an outlet mixing area; the fuel and the air flowing into the inner flow passage enter the inner mixing area to be mixed into a first zone-swirl combustible mixture, the fuel and the air flowing into the outer flow passage enter the outer mixing area to be mixed into a second zone-swirl combustible mixture, the first zone-swirl combustible mixture passes through the mesh plate to become a non-swirl combustible mixture, and the non-swirl combustible mixture is mixed with the second zone-swirl combustible mixture in the outlet mixing area.
Preferably, the wave cyclone is formed by arranging a plurality of wave crests and a plurality of wave troughs which fluctuate along the radial direction at intervals along the circumferential direction, the wave troughs which are arranged along the circumferential direction enclose an inscribed circle, the wave crests which are arranged along the circumferential direction form an circumscribed circle, and the diameter of the middle cylinder is between the diameter of the inscribed circle and the diameter of the circumscribed circle.
Preferably, part or all of the inner ring swirl structures are trimmed off along the axial direction, the upstream side part of the wave cyclone forms a cavity, and an inner mixing area is formed between the bottom of the cavity and the mesh plate.
Preferably, the outlet end of the wave swirler is trimmed with a groove.
Preferably, the center shaft of the nozzle is provided with an on-duty flame flow channel, and the combustible mixture enters the on-duty flame flow channel from an on-duty flame fuel inlet.
Preferably, the outer wall cylinder comprises an outer wall inner cylinder and an outer wall sleeve sleeved outside the outer wall inner cylinder, the outer wall sleeve can move along the axial direction, and the transition between the diffusion combustion mode and the premix combustion mode is realized by adjusting the axial position of the outer wall sleeve.
Preferably, the nozzle central shaft is provided with a high-voltage electrode outer sleeve, the high-voltage electrode is positioned in the high-voltage electrode outer sleeve, and discharge is formed between the high-voltage electrode discharge tip and the nozzle outlet.
Preferably, the ratio of the open area of the mesh plate to the mesh plate area is 40-80%.
The invention also provides a nozzle array, which comprises a plurality of nozzles, wherein the nozzle array is a circular array, the circular array comprises P circles of nozzles, each circle of nozzles comprises Q nozzles, and the number of the nozzles is more than or equal to 1 and less than or equal to P, Q and less than or equal to 100; or the nozzle array is a rectangular array, the rectangular array comprises P rows of nozzles, each row of nozzles comprises Q nozzles, and the number of the nozzles is more than or equal to 1 and less than or equal to P, Q and less than or equal to 100.
The invention also provides a burner comprising the nozzle, or the nozzle array.
(III) advantageous effects
According to the technical scheme, the nozzle array and the combustor with the internal and external mixing regions have the following beneficial effects:
(1) according to the nozzle, fuel and air are not mixed before entering the nozzle, the combustible mixture in the outer mixing region has rotary motion, the combustible mixer forms expanding flame at the nozzle outlet under the action of centrifugal force, the combustion stability is improved, combustible flowing out of the outlet region of the middle cylinder has non-rotary axial motion, a strong backflow region can be prevented from being formed at the nozzle outlet, the flow loss is reduced, the pollutant emission is reduced, and meanwhile, the nozzle has good combustion stability and low pollutant emission;
(2) part or all of the structure of the inner ring rotational flow structure can be trimmed, so that the weight of the nozzle is reduced, and the flow friction loss is reduced;
(3) the outlet end of the wave cyclone can be trimmed to form a groove, so that the weight of the nozzle is further reduced, and the flow friction loss is reduced;
(4) the flame flow channel on duty is arranged on the middle shaft of the nozzle, so that a channel in the middle of the wave swirler can be blocked, air and fuel are mixed more uniformly, and the combustion performance of the nozzle is improved;
(5) the outer wall cylinder comprises an outer wall inner cylinder and an outer wall sleeve sleeved outside the outer wall inner cylinder, the outer wall sleeve can move along the axial direction, the nozzle can be switched between two combustion modes, the functions are various, the advantages of different modes can be fully utilized, the defects of different modes are avoided as much as possible, the nozzle is suitable for various working conditions and fuels, and the combustion performance is improved;
(6) the high-voltage electrode outer sleeve is arranged at the middle shaft of the nozzle, the high-voltage electrode is positioned in the high-voltage electrode outer sleeve, discharge is formed between the discharge tip of the high-voltage electrode and the outlet of the nozzle, the high-voltage electrode outer sleeve can be used for ignition of the nozzle and is beneficial to stable combustion, and the high-voltage electrode outer sleeve can block a channel in the middle of a wave swirl structure, so that air and fuel are mixed more uniformly, and the combustion performance of the nozzle is further improved.
Drawings
FIG. 1 is a half-sectional view of a nozzle having both an inner and outer blending region according to an embodiment of the present invention;
FIG. 2 is a top view of the nozzle shown in FIG. 1;
FIG. 3 is a three-dimensional view of the nozzle of FIG. 1 with the outer wall cylinder removed;
FIG. 4 is a fragmentary view of FIG. 3 taken at a location along the axial direction;
FIG. 5 is a dimensional schematic of the nozzle of FIG. 1;
FIG. 6 is a schematic axial dimension view of the nozzle of FIG. 1;
FIG. 7 is a schematic view of the nozzle of FIG. 1 with portions of the inner ring swirl flow trimmed away;
FIG. 8 is a schematic view of the nozzle of FIG. 1 with all inner rings of swirl flow trimmed away;
FIG. 9 is a three-dimensional schematic view of the wave swirler of FIG. 8 showing only the inner ring swirl structures trimmed away;
FIG. 10 is a schematic view of trimming a groove on a wave swirler;
FIG. 11 is a schematic view of a flow channel with an on-duty flame;
FIG. 12 is a schematic view of a diffusion combustion mode with an outer wall sleeve;
FIG. 13 is a schematic view of a premixed combustion mode with an outer wall sleeve;
fig. 14 is a nozzle with a plasma actuator.
[ notation ] to show
1-middle cylinder inlet; 2-outer wall cylinder inlet; 3-outer wall cylinder; 4-a support cylinder; 5-wave swirler; 6-middle cylinder; 7-an internal mixing region; 8-mesh plate; 9-an outer mixing region; 10-intermediate cylinder outlet zone; 11-an outlet blending zone; 12-nozzle outlet; 13-inner ring rotational flow structure; 14-outer ring rotational flow structure; 15-a groove; 16-on-duty flame fuel inlet; 17-on-duty flame flow channel; 18-an outer wall sleeve; 19-plasma power ground; 20-a plasma power supply; 21-plasma power high voltage terminal; 22-a high voltage electrode; 23-high voltage electrode jacket; 24-high voltage electrode discharge tip; 25-inner cylinder with outer wall.
A-outer wall cylinder diameter; b-diameter of the middle cylinder; c-the diameter of the inscribed circle of the wave cyclone; d, the depth of the middle cylinder embedded into the wave cyclone; e-mesh plate thickness; f-inner mixing area height; g-height of the outlet zone of the intermediate cylinder; h-outlet blending zone height.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to specific embodiments and the accompanying drawings.
Referring to fig. 1 to 4, an embodiment of the invention provides a nozzle with an inner and outer mixing regions, including: middle cylinder 6, outer wall cylinder 3, mesh plate 8 and wave whirl structure 5. The wave rotational flow structure is positioned in the outer wall cylinder 3 and is coaxially arranged with the outer wall cylinder 3; the wave cyclone structure comprises a wave cyclone 5 and a supporting cylinder 4, wherein the wave cyclone 5 is formed by arranging a plurality of wave crests and a plurality of wave troughs which fluctuate along the radial direction at intervals along the circumferential direction, the wave troughs which are arranged along the circumferential direction enclose an inscribed circle, an inscribed circle space is formed in the center of the wave cyclone 5, and the wave crests which are arranged along the circumferential direction form an circumscribed circle; the downstream side portion of the wave swirler 5 is transitionally connected to the support cylinder 4. The middle cylinder 6 is embedded into the wave cyclone 5 from the outlet end of the wave cyclone 5 along the axial direction of the wave cyclone 5, the diameter of the middle cylinder 6 is between the diameter of an inscribed circle and the diameter of an circumscribed circle, the wave cyclone 5 is divided into two parts, namely an inner circle cyclone structure 13 and an outer circle cyclone structure 14, the middle cylinder 6 and the outer wall cylinder 3 enclose an outer runner, and the inner circle cyclone structure 13 and the middle cylinder 6 enclose an inner runner. The mesh plate 8 is arranged in the middle cylinder 6, an inner blending area 7 is formed between the mesh plate 8 and the outlet end of the wave cyclone 5, the inner blending area 7 is communicated with an inner flow passage, the outer wall cylinder 3 protrudes out of the middle cylinder 6 along the downstream direction, the outlet ends of the outer wall cylinder 3 and the wave cyclone 5 and the middle cylinder 6 enclose an outer blending area 9, the outer blending area 9 is communicated with an outer flow passage, and the part of the outer wall cylinder 3 protruding out of the middle cylinder 6 forms an outlet blending area 11.
In the nozzle of this embodiment, the fuel and air are not mixed before entering the nozzle, the middle cylinder inlet 1 may be a fuel inlet or an air inlet, and the outer wall cylinder inlet 2 may be a fuel inlet or an air inlet. In order to achieve combustion, fuel and air must be blended together, and in this embodiment there are three blending zones, namely, an inner blending zone 7, an outer blending zone 9, and an outlet blending zone 11. Taking the example that fuel is introduced into the middle cylinder inlet 1 and air is introduced into the outer wall cylinder inlet 2, the fuel enters the nozzle from the middle cylinder inlet 1, enters the wave swirler 5 through the support cylinder 4, part of the fuel flows into the inner flow channel, part of the fuel flows into the outer flow channel, the air enters the nozzle from the outer wall cylinder inlet 2, part of the air flows into the inner flow channel, part of the air flows into the outer flow channel, and the fuel and the air flowing into the inner flow channel enter the inner blending zone 7 to be blended into the flammable mixture with swirling; the fuel and air flowing into the outer flow passage enter the outer mixing area 9 to be mixed into a combustible mixture with swirl, the mesh plate 8 plays a role of filtration, the combustible mixture with swirl of the inner mixing area 7 passes through the mesh plate 8, the rotary motion of the combustible mixture is filtered to form a combustible mixture without swirl, and the combustible mixture without swirl flows out of the middle cylinder outlet area 10, is mixed with the combustible mixture with swirl flowing out of the outer mixing area 9 in the outlet mixing area 11 and is sprayed out and combusted through the nozzle outlet 12. In the invention, because the combustible mixture in the outer mixing zone 9 has rotary motion, the combustible mixer forms expanding flame at the nozzle outlet 12 under the action of centrifugal force, the combustion stability is improved, the combustible flowing out of the outlet zone 10 of the middle cylinder has non-rotary axial motion, a strong backflow zone can be prevented from being formed at the nozzle outlet, the flow loss is reduced, and the pollutant emission is reduced, therefore, the nozzle has good combustion stability and low pollutant emission. When air is introduced into the middle cylinder inlet 1 and fuel is introduced into the outer wall cylinder inlet 2, the operation of the nozzle is similar to that described above and will not be described further.
The cross section profile of the inlet end of the cyclone wave device can be circular or polygonal ring, preferably circular; the cross section profile of the outlet end of the cyclone wave device can be sine wave, square wave, triangular wave and square wave with round chamfer; the guide line of the swirl wave device is a straight line or a curve. The inner flow channel and the outer flow channel are oblique flow channels, fuel and air respectively rotate on the two sides of the wave swirler along the circumference under the action of the oblique flow channels, and the fuel and the air are mixed at the outlet of the wave swirler. Preferably, in the case that the rotation direction of the oblique flow channel is anticlockwise rotation, the included angle between the oblique flow channel and the axial direction ranges from-90 degrees to 0 degrees, and preferably ranges from-30 degrees to-60 degrees; or the inclined flow channel has an included angle with the axial direction ranging from 0 degrees to 90 degrees, preferably from 30 degrees to 60 degrees under the condition that the rotation direction of the inclined flow channel is clockwise rotation.
In the present embodiment, referring to fig. 5, the diameter of the outer cylinder is a (i.e. the diameter of the circumscribed circle of the wave swirler 5), the diameter of the middle cylinder is B, the diameter of the inscribed circle of the wave swirler 5 is C, and a > B > C, preferably B ═ (a + C)/2. The cross-sectional profile of the intermediate cylinder 6 may be circular, triangular, polygonal, preferably circular.
Referring to fig. 6, the depth D of the middle cylinder 6 inserted into the wave swirler 5 is 1mm to 1000mm, preferably D is a/2; the thickness E of the mesh plate is 1 mm-1000 mm, preferably E is 5 mm; the height F of the internal mixing area is 1 mm-1000 mm, preferably F is A/2; the height G of the outlet area of the middle cylinder is 1 mm-1000 mm, preferably G is A/2; the height H of the outlet blending zone is 1 mm-1000 mm, and preferably H is between 1.5A-3A.
The ratio of the area of the openings on the mesh plate to the area of the mesh plate is 0-100%, that is, the mesh plate 8 can be not provided with openings, the fuel and the air are mixed only through the outer flow channel, and the ratio of the area of the openings on the mesh plate to the area of the mesh plate is 0 at this moment; the mesh plate 8 can be completely perforated, which is equivalent to no mesh plate, so that the combustible mixture in the outlet area 10 of the middle cylinder is also a combustible mixture area with rotation, and the ratio of the area of the perforated hole on the mesh plate to the area of the mesh plate is 100%. Preferably, the ratio of the area of the opening on the mesh plate to the area of the mesh plate is 40-80%. The diameter of the holes on the mesh plate is 0.1-10mm, and the sizes of the holes can be the same or different; the shape of the aperture may be circular, elliptical, triangular, polygonal or a combination of these shapes.
For the purpose of brief description, any technical features of the first embodiment that can be applied to the nozzle of the second embodiment are described herein, and the same description is not repeated.
In this embodiment, the inner ring of swirl structures 13 in the middle cylinder 6 is trimmed off in the axial direction (see fig. 7), and the upstream portion of the wave swirler 5 forms a cavity, and an inner mixing zone is formed between the bottom of the cavity and the mesh plate 8, which helps to reduce the weight of the nozzle and the flow friction loss. The height of the trimmed partial structure is between 0 and 100 percent D. After trimming, the position of the mesh plate is adjusted accordingly, so that the height F of the internal mixing area is 1 mm-1000 mm, preferably F is A/2.
Referring to fig. 8 and 9, in the present embodiment, the inner ring swirl structure 13 can be completely trimmed off, the swirl wave structure only includes the outer ring swirl structure 14, the upstream side portion of the wave swirler 5 forms a cavity, and an inner mixing area is formed between the bottom of the cavity and the mesh plate, which helps to further reduce the weight of the nozzle and reduce the flow friction loss. After trimming, the position of the mesh plate is adjusted accordingly, so that the height F of the internal mixing area is 1 mm-1000 mm, preferably F is A/2.
For the purpose of brief description, any technical features of any of the above embodiments that can be applied to the same purpose are described herein, and the same description need not be repeated.
Referring to fig. 10, in this embodiment, the outlet end of the wave swirler 5 is trimmed with a groove 15, which helps to further reduce the nozzle weight and flow friction losses.
For the purpose of brief description, any technical features of any of the above embodiments that can be applied to the same purpose are described herein, and the same description need not be repeated.
Referring to fig. 11, in this embodiment, an on-duty flame flow passage 17 is provided in the central axis of the nozzle, the on-duty flame flow passage 17 extends through the entire nozzle through the support cylinder 4, the inscribed circle space, the middle cylinder 6 and the mesh plate 8 therein, and the combustible mixture enters the on-duty flame flow passage 17 from the on-duty flame fuel inlet 16. The diameter of the flame channel on duty is 1 mm-1000 mm, preferably the diameter C of an inscribed circle of the wave cyclone structure, so that the flame channel on duty can block the channel in the middle of the wave cyclone 5, the air and fuel are mixed more uniformly, and the combustion performance of the nozzle is improved. The on-duty flame is preferably diffusion combustion.
For the purpose of brief description, any technical features of any of the above embodiments that can be applied to the same purpose are described herein, and the same description need not be repeated.
Referring to fig. 12 and 13, in this embodiment, the outer wall cylinder 3 includes an outer wall inner cylinder 25 and an outer wall sleeve 18 fitted over the outer wall inner cylinder 25, the wave swirl structure and the outlet end of the intermediate cylinder 6 are axially aligned, the outer wall sleeve 18 is axially movable, and the transition between the diffusion combustion mode and the premixed combustion mode can be achieved by adjusting the axial position of the outer wall sleeve 18. In fig. 12, the outer wall sleeve 18, the outer wall inner cylinder 25, the wave swirl structure and the outlet end of the middle cylinder 6 are all in the same plane, and at this time, the nozzle is in a diffusion combustion mode; FIG. 13 shows the outer wall sleeve exit end at a location downstream of the exit end of the intermediate cylinder 6, in this case either a premixed combustion mode or an intermediate mode where diffusion combustion transitions to premixed combustion. By arranging the outer wall sleeve 18, the nozzle of the invention can be switched between two combustion modes, has various functions, can fully utilize the advantages of different modes, avoids the defects of different modes as much as possible, can be suitable for various working conditions and fuels, and improves the combustion performance.
For the purpose of brief description, any technical features of any of the above embodiments that can be applied to the same purpose are described herein, and the same description need not be repeated.
Referring to fig. 14, in this embodiment, a high voltage electrode jacket 23 is disposed at a central axis of the nozzle, the high voltage electrode jacket 23 penetrates through the entire nozzle through the support cylinder 4, the inscribed circle space, the middle cylinder 6 and the mesh plate 8 therein, the high voltage electrode 22 is disposed in the high voltage electrode jacket 23, the high voltage electrode jacket 23 is made of an insulating material, and the high voltage electrode 22 is made of a conductive material; the plasma power supply 20 includes a plasma power high voltage terminal 21 and a plasma power ground terminal 19. The high-voltage electrode 22 is connected with the high-voltage end 21 of the plasma power supply; the outer wall cylinder 3 is a grounding end and is connected with a plasma power supply grounding end 19; the discharge formed between the high voltage electrode discharge tip 24 and the nozzle outlet 12 may be used for nozzle ignition and to facilitate stable combustion. The diameter of the high-voltage electrode outer sleeve is 1 mm-1000 mm, preferably the diameter C of an inscribed circle of the wave cyclone 5, so that the high-voltage electrode outer sleeve 23 can block a channel in the middle of the wave cyclone structure, air and fuel are mixed more uniformly, and the combustion performance of the nozzle is further improved.
A seventh embodiment of the invention provides a nozzle array comprising a plurality of nozzles as described in any of the above embodiments.
The nozzle array is a circular array, the circular array comprises P circles of nozzles, each circle of nozzles comprises Q nozzles, and the number of the nozzles is more than or equal to 1 and less than or equal to P, Q and less than or equal to 100.
The nozzle array is a rectangular array, the rectangular array comprises P rows of nozzles, each row of nozzles comprises Q nozzles, and the number of the nozzles is more than or equal to 1 and less than or equal to P, Q and less than or equal to 100.
An eighth embodiment of the present invention provides a burner comprising a nozzle as described in any one of the first to sixth embodiments above, or a multi-orifice nozzle array as described in the seventh embodiment.
Up to this point, the present embodiment has been described in detail with reference to the accompanying drawings. From the above description, those skilled in the art should clearly recognize the present invention.
It is to be noted that, in the attached drawings or in the description, the implementation modes not shown or described are all the modes known by the ordinary skilled person in the field of technology, and are not described in detail. In addition, the above definitions of the various elements are not limited to the specific structures, shapes or modes mentioned in the embodiments, and those skilled in the art may easily modify or replace them, for example:
(1) the wave rotational flow structure can also adopt other structures;
(2) directional phrases used in the embodiments, such as "upper", "lower", "front", "rear", "left", "right", etc., refer only to the orientation of the attached drawings and are not intended to limit the scope of the present invention;
(3) the embodiments described above may be mixed and matched with each other or with other embodiments based on design and reliability considerations, i.e. technical features in different embodiments may be freely combined to form further embodiments.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit 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 protection scope of the present invention.
Claims (10)
1. A nozzle having both internal and external mixing regions, comprising: the device comprises a middle cylinder, an outer wall cylinder, a mesh plate and a wave cyclone; wherein,
the wave cyclone is coaxially arranged in the outer wall cylinder;
the middle cylinder is embedded into the wave cyclone from the outlet end of the wave cyclone along the axial direction of the wave cyclone, and the wave cyclone is divided into an inner ring cyclone structure and an outer ring cyclone structure;
the outer ring rotational flow structure, the middle cylinder and the outer wall cylinder enclose an outer flow passage, and the inner ring rotational flow structure and the middle cylinder enclose an inner flow passage;
the mesh plate is arranged in the middle cylinder, an inner blending area is formed between the mesh plate and the outlet end of the wave cyclone, and the inner blending area is communicated with the inner flow passage; the outer wall cylinder, the outlet ends of the wave cyclones and the middle cylinder form an outer mixing area in a surrounding mode, the outer mixing area is communicated with the outer flow channel, and the part, protruding out of the middle cylinder, of the outer wall cylinder forms an outlet mixing area;
the fuel and the air flowing into the inner flow passage enter the inner mixing area to be mixed into a first zone-swirl combustible mixture, the fuel and the air flowing into the outer flow passage enter the outer mixing area to be mixed into a second zone-swirl combustible mixture, the first zone-swirl combustible mixture passes through the mesh plate to become a non-swirl combustible mixture, and the non-swirl combustible mixture is mixed with the second zone-swirl combustible mixture in the outlet mixing area.
2. The nozzle of claim 1 wherein said wave swirler is formed by a plurality of radially undulating wave crests and a plurality of circumferentially spaced wave troughs, the circumferentially spaced wave troughs defining an inscribed circle, the circumferentially spaced wave crests forming an circumscribed circle, and said intermediate cylinder having a diameter between the inscribed circle diameter and the circumscribed circle diameter.
3. The nozzle of claim 1, wherein some or all of the inner ring vortex structures are trimmed off in the axial direction, and an upstream portion of the wave swirler forms a cavity, and an inner blending zone is formed between the bottom of the cavity and the mesh plate.
4. The nozzle of claim 1 wherein the outlet end of the wave swirler is trimmed with a groove.
5. The nozzle of claim 1 wherein the nozzle central axis defines an on-duty flame flow path, the combustible mixture entering the on-duty flame flow path from the on-duty flame fuel inlet.
6. The nozzle of claim 1 wherein said outer wall cylinder comprises an outer wall inner cylinder and an outer wall sleeve disposed about said outer wall inner cylinder, said outer wall sleeve being axially movable to effect transition between diffusion combustion mode and premixed combustion mode by adjusting the axial position of said outer wall sleeve.
7. The nozzle of claim 1 wherein the nozzle central axis is provided with a high voltage electrode sheath, the high voltage electrode being located within the high voltage electrode sheath, the discharge being formed between the high voltage electrode discharge tip and the nozzle outlet.
8. The nozzle of claim 1, wherein the ratio of the open area of the mesh plate to the mesh plate area is between 40% and 80%.
9. A nozzle array comprising a plurality of nozzles according to any one of claims 1 to 8,
the nozzle array is a circular array, the circular array comprises P circles of nozzles, each circle of nozzles comprises Q nozzles, and the number of the nozzles is not less than 1 and not more than P, Q and not more than 100; or,
the nozzle array is a rectangular array, the rectangular array comprises P rows of nozzles, each row of nozzles comprises Q nozzles, and the number of the nozzles is greater than or equal to 1 and less than or equal to P, Q and less than or equal to 100.
10. A burner comprising a nozzle according to any one of claims 1 to 8, or an array of nozzles according to claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611136457.0A CN106705122B (en) | 2016-12-09 | 2016-12-09 | A kind of nozzle, nozzle array and burner having both inside and outside dilution zone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611136457.0A CN106705122B (en) | 2016-12-09 | 2016-12-09 | A kind of nozzle, nozzle array and burner having both inside and outside dilution zone |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106705122A true CN106705122A (en) | 2017-05-24 |
| CN106705122B CN106705122B (en) | 2019-02-01 |
Family
ID=58936639
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611136457.0A Active CN106705122B (en) | 2016-12-09 | 2016-12-09 | A kind of nozzle, nozzle array and burner having both inside and outside dilution zone |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106705122B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107366929A (en) * | 2017-07-20 | 2017-11-21 | 中国科学院工程热物理研究所 | Nozzle with expansion shape profile cyclone |
| CN108204604A (en) * | 2018-03-13 | 2018-06-26 | 中国航空发动机研究院 | Combustion chamber Multi-stage spiral nozzle with mechanical periodicity export structure |
| CN110160083A (en) * | 2019-05-24 | 2019-08-23 | 西安航天动力研究所 | The steady flame device of gas-air mixer |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5235813A (en) * | 1990-12-24 | 1993-08-17 | United Technologies Corporation | Mechanism for controlling the rate of mixing in combusting flows |
| US5638675A (en) * | 1995-09-08 | 1997-06-17 | United Technologies Corporation | Double lobed mixer with major and minor lobes |
| CN103988020A (en) * | 2011-12-12 | 2014-08-13 | 西门子公司 | Fuel injector for two combustible materials |
| CN105674263A (en) * | 2016-02-23 | 2016-06-15 | 中国科学院工程热物理研究所 | Nozzle with mixing combustion stabilizing structures, nozzle array and combustor |
| CN105757716A (en) * | 2016-02-22 | 2016-07-13 | 中国科学院工程热物理研究所 | Nozzle for premixed combustion, nozzle array and combustor |
-
2016
- 2016-12-09 CN CN201611136457.0A patent/CN106705122B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5235813A (en) * | 1990-12-24 | 1993-08-17 | United Technologies Corporation | Mechanism for controlling the rate of mixing in combusting flows |
| US5638675A (en) * | 1995-09-08 | 1997-06-17 | United Technologies Corporation | Double lobed mixer with major and minor lobes |
| CN103988020A (en) * | 2011-12-12 | 2014-08-13 | 西门子公司 | Fuel injector for two combustible materials |
| CN105757716A (en) * | 2016-02-22 | 2016-07-13 | 中国科学院工程热物理研究所 | Nozzle for premixed combustion, nozzle array and combustor |
| CN105674263A (en) * | 2016-02-23 | 2016-06-15 | 中国科学院工程热物理研究所 | Nozzle with mixing combustion stabilizing structures, nozzle array and combustor |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107366929A (en) * | 2017-07-20 | 2017-11-21 | 中国科学院工程热物理研究所 | Nozzle with expansion shape profile cyclone |
| CN107366929B (en) * | 2017-07-20 | 2020-03-17 | 中国科学院工程热物理研究所 | Nozzle with divergent profile swirler |
| CN108204604A (en) * | 2018-03-13 | 2018-06-26 | 中国航空发动机研究院 | Combustion chamber Multi-stage spiral nozzle with mechanical periodicity export structure |
| CN108204604B (en) * | 2018-03-13 | 2023-05-23 | 中国航空发动机研究院 | Combustion chamber multi-stage swirl nozzle with periodically varying outlet structure |
| CN110160083A (en) * | 2019-05-24 | 2019-08-23 | 西安航天动力研究所 | The steady flame device of gas-air mixer |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106705122B (en) | 2019-02-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6889495B2 (en) | Gas turbine combustor | |
| CN106224959B (en) | Burner, burner array and burner with regulating flow quantity nozzle | |
| KR20120098620A (en) | Method of fuel staging in combustion apparatus | |
| JP2002168449A (en) | Mixer having plurality of swirlers | |
| JP2005351616A (en) | Burner tube and method for mixing air and gas in gas turbine engine | |
| CN102175043A (en) | Gas turbine engine combustor can with trapped vortex cavity | |
| CN114811581B (en) | Air-fuel dual-stage high-proportion hydrogen-doped ultralow-nitrogen combustor, method and boiler | |
| CN105757716B (en) | A kind of nozzle, nozzle array and burner for premixed combustion | |
| CN105737200B (en) | A kind of atomizer, nozzle array and burner | |
| CN106705122B (en) | A kind of nozzle, nozzle array and burner having both inside and outside dilution zone | |
| EP3425281B1 (en) | Pilot nozzle with inline premixing | |
| CN106247408B (en) | A kind of nozzle, nozzle array and burner for widening tempering nargin | |
| CN105864765B (en) | Nozzle, nozzle array with Plasma Actuator and burner | |
| CN111829007A (en) | Axial staged combustion chamber based on flame tube concave cavity structure | |
| CN105674263B (en) | One kind has the steady combustion structure nozzle of blending, nozzle array and burner | |
| KR102014828B1 (en) | Partially Premixed Annular Rich-Lean Jet Oxygen-enriched Burner | |
| CN113124422B (en) | Axial staged combustor | |
| CN106705045B (en) | A kind of adjustable nozzle of interior outer flow passage equivalent proportion, nozzle array and burner | |
| CN105783031B (en) | A kind of integrated plasma excitation device, nozzle array and burner | |
| CN212132520U (en) | Axial staged burner | |
| RU2197685C1 (en) | Burner | |
| CN115807947A (en) | Axial premixing low-emission flame tube | |
| CN111536555A (en) | Engine and engine combustion chamber thereof | |
| CN105650642B (en) | A kind of nozzle forming low regime, nozzle array and burner | |
| JPH0942672A (en) | Gas turbine combustor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |