CN116557855A - Fuel atomizing nozzle of combustor and afterburning pressurization system - Google Patents
Fuel atomizing nozzle of combustor and afterburning pressurization system Download PDFInfo
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- CN116557855A CN116557855A CN202310491126.2A CN202310491126A CN116557855A CN 116557855 A CN116557855 A CN 116557855A CN 202310491126 A CN202310491126 A CN 202310491126A CN 116557855 A CN116557855 A CN 116557855A
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- 239000000446 fuel Substances 0.000 title claims abstract description 89
- 238000002485 combustion reaction Methods 0.000 claims abstract description 72
- 239000000295 fuel oil Substances 0.000 claims abstract description 48
- 238000000889 atomisation Methods 0.000 claims abstract description 15
- 230000005540 biological transmission Effects 0.000 claims abstract description 13
- 239000003921 oil Substances 0.000 claims description 47
- 238000010438 heat treatment Methods 0.000 claims description 15
- 239000002803 fossil fuel Substances 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 72
- 238000007789 sealing Methods 0.000 description 13
- 230000000694 effects Effects 0.000 description 9
- 238000009413 insulation Methods 0.000 description 7
- 239000002245 particle Substances 0.000 description 6
- 239000002737 fuel gas Substances 0.000 description 5
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 4
- 230000004323 axial length Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000009467 reduction Effects 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 238000002156 mixing Methods 0.000 description 3
- 238000010248 power generation Methods 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 239000002912 waste gas Substances 0.000 description 3
- 229910052581 Si3N4 Inorganic materials 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 229910002092 carbon dioxide Inorganic materials 0.000 description 2
- 230000001276 controlling effect Effects 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 239000007771 core particle Substances 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 239000012071 phase Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000002000 scavenging effect Effects 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 239000004071 soot Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
- F01N3/00—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust
- F01N3/08—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for rendering innocuous
- F01N3/10—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for rendering innocuous by thermal or catalytic conversion of noxious components of exhaust
- F01N3/24—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for rendering innocuous by thermal or catalytic conversion of noxious components of exhaust characterised by constructional aspects of converting apparatus
- F01N3/36—Arrangements for supply of additional fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/38—Nozzles; Cleaning devices therefor
- F23D11/383—Nozzles; Cleaning devices therefor with swirl means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/40—Mixing tubes or chambers; Burner heads
- F23D11/402—Mixing chambers downstream of the nozzle
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The invention relates to a fuel atomizing nozzle of a combustor and an afterburning pressurization system, and belongs to the technical field of fuel atomization. The fuel atomizing nozzle comprises a fuel nozzle core and a gas cyclone; the fuel nozzle core comprises a first fixed end and a fuel transmission guide post; the gas cyclone comprises a fuel oil introducing part, an air introducing part and an atomization cylindrical cavity; the fuel oil transmission guide post is sequentially provided with a first column section, a swirl groove and a second column section. The invention can improve the combustion efficiency of fossil fuel, reduce combustion emission and improve the utilization efficiency of fuel.
Description
Technical Field
The invention belongs to the technical field of fuel atomization, and relates to a fuel atomizing nozzle of a combustor and a post-combustion pressurizing system.
Background
Along with the increasing use of fossil energy, fossil energy becomes more and more scarce, and simultaneously, harmful substances such as HC, CO and particulate matters after fuel combustion also have more and more serious to the environmental impact, solve fuel combustion emission problem and improve the utilization efficiency of fossil energy and pay more and more attention, and the efficient atomizing nozzle is not separated from the efficient atomizing nozzle for improving the combustion efficiency in both the engine tail gas afterburning technology and the traditional gas turbine efficient combustion.
Disclosure of Invention
In view of the above problems, the present invention provides a fuel atomizing nozzle and an afterburning pressurization system of a burner, which are used for improving the combustion efficiency of fossil fuel, reducing the combustion emission and improving the fuel utilization efficiency.
The invention provides a fuel atomizing nozzle of a combustor, which comprises a fuel nozzle core and a gas cyclone,
the fuel nozzle core comprises a first fixed end and a fuel transmission guide post;
the gas cyclone comprises a fuel oil introducing part, an air introducing part and an atomization cylindrical cavity;
the first fixed end is provided with a fuel inlet;
the fuel oil transmission guide post is sequentially provided with a first post section, a swirl groove and a second post section, wherein the first post section is close to the first fixed end, and the second post section is far away from the first fixed end;
the first column section is provided with an oil outlet and a spiral oil duct, and the spiral oil duct is used for spirally conveying the fuel oil output from the oil outlet to the swirl groove;
the swirl groove is used for injecting fuel into the chute after rotating;
the second column section is provided with a chute which is communicated with the swirl groove and the atomizing cylindrical cavity; the chute is used for injecting fuel into the atomization cylindrical cavity;
the first fixed end is provided with a fuel inlet which is communicated with the oil outlet;
the fuel oil leading-in part is connected with the atomization cylindrical cavity and comprises a containing cavity and a second fixed end; the accommodating cavity is used for accommodating the fuel oil transmission guide post, and the second fixed end is used for connecting the first fixed end;
the accommodating cavity is sequentially provided with a first accommodating section and a second accommodating section; the first accommodating section is close to the first fixed end, the diameter of the first accommodating section is larger than that of the first column section, an oiling space is formed between the first accommodating section and the first column section, and the oil outlet is arranged in the region of the first column section located in the oiling space;
the atomizing cylinder is communicated with the air inlet.
Optionally, the swirl groove is a radial circular groove along the fuel delivery post.
Optionally, the atomizing cylinder communicates with the air introduction portion through a swirl hole.
Optionally, the chute is symmetrically provided with a plurality of chute; the cross-sectional area of the spiral oil passage is 2-3 times the total cross-sectional area of the plurality of inclined grooves.
Optionally, the orientation of the chute outlet is arranged opposite to the orientation of the swirl hole outlet.
Optionally, the end of the fuel inlet is provided with an end stepped cylindrical cavity section.
Optionally, the outlet aperture is perpendicular to the axis of the terminal stepped cylindrical cavity section.
The invention discloses an afterburning supercharging system, which also comprises an engine exhaust pipe, an afterburning combustor, a turbocharger and an integrated starting motor; the afterburner comprises a heating element, a nozzle, a jet flow combustion chamber and a swirl combustion chamber, wherein the nozzle uses the fuel atomizing nozzle.
Compared with the prior art, the invention has at least the following beneficial effects:
(1) The fuel nozzle core and the gas cyclone arranged in the fuel atomizing nozzle can realize the effect of accelerating fuel step by step, and the fuel atomizing effect is improved.
(2) The fuel oil spraying chute arranged on the fuel oil atomizing nozzle is positioned at the tail end of the fuel oil conveying spiral groove, the angle is opposite to the center of the rotational flow hole, more sufficient fuel oil atomization can be realized, the mixing with air is accelerated, and the combustion effect of the burner is improved.
(3) The fuel atomizing nozzle has a simple structure, only has a four-stage structure, and is convenient to use, replace and maintain.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention.
FIG. 1 is a schematic view of the overall structure of the burner of the present invention.
FIG. 2 is a schematic view of a burner jet combustion chamber and a portion of an accessory configuration of the present invention.
FIG. 3 is a schematic view of the fuel nozzle structure of the present invention.
FIG. 4 is a schematic illustration of a fuel nozzle core of the present invention.
Fig. 5 is a cross-sectional view of the fuel nozzle of the present invention.
FIG. 6 is a top partial cross-sectional view of the gas swirler of the present invention;
fig. 7 is a cross-sectional view of a cantilever rotor in the afterburning supercharging system of the present invention.
Fig. 8 is an afterburning supercharging system of the present invention.
Reference numerals:
1. the engine comprises an engine exhaust, 2, an afterburner, 3, a turbocharger, 4, a starting integrated motor, 5, a heat insulating sealing device, 6, a swirl combustion chamber, 7, a jet combustion chamber, 8, an engine exhaust inlet, 9, an afterburner outlet, 10, a supercharger outlet, 11, a motor bracket, 12, a coupler, 13, a fuel inlet, 14, an air inlet, 15, a heating element, 16, a fuel nozzle core, 17, a gas swirler, 18, an atomizing cylindrical cavity, 19, a secondary swirl area, 20, a jet area, 21, an outlet pipeline, 22, a first exhaust interface, 23, a second exhaust interface, 24, a swirl hole, 25, a gas inlet, 26, an oil outlet, 27, a spiral oil duct, 28, a gas inlet, 29, a chute, 30, a fuel guide pipe, 31, an oil filling space, 32, a mounting mating hole, 33, a rotating shaft, 34, a turbine, 35, a bearing, 36, a centrifugal compressor impeller and 37, and an axial radial damper.
Detailed Description
In order that the above-recited objects, features and advantages of the present invention will be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description. It should be noted that, without conflict, the embodiments of the present invention and features in the embodiments may be combined with each other. In addition, the invention may be practiced otherwise than as specifically described and thus the scope of the invention is not limited by the specific embodiments disclosed herein.
3-5, a fuel atomizing nozzle for a burner is disclosed, the fuel nozzle core 16 including a first fixed end and a fuel transfer post; the gas cyclone 17 comprises a fuel oil introduction part, an air introduction part 14 and an atomization cylinder 18; the first fixed end is provided with a fuel inlet 13; the fuel oil transmission guide post is sequentially provided with a first post section, a cyclone groove 31 and a second post section, wherein the first post section is close to the first fixed end, and the second post section is far away from the first fixed end; the first column section is internally provided with an oil outlet 26, the periphery of the first column section is provided with a spiral oil duct 27, and the oil outlet is close to the first fixed end; the spiral oil duct is spirally arranged on the periphery of the first column section between the oil outlet hole and the cyclone groove; the spiral oil duct is used for spirally conveying the fuel oil output from the oil outlet to the swirl groove; the swirl groove is a radial circular groove along the fuel oil transmission guide post; the swirl groove is used for injecting fuel into the chute after rotating; the periphery of the second column section is provided with a chute which is communicated with the swirling groove and the atomizing cylindrical cavity; the angle between the axis of the chute and the axis of the second column section and/or the axis of the atomizing cylinder cavity is alpha; the chute is used for injecting fuel into the atomization cylindrical cavity; the fuel inlet is communicated with the oil outlet; the fuel oil leading-in part is connected with the atomization cylindrical cavity and comprises a containing cavity and a second fixed end; the accommodating cavity is used for accommodating the fuel oil transmission guide post, and the second fixed end is used for connecting the first fixed end; the accommodating cavity is sequentially provided with a first accommodating section and a second accommodating section; the first accommodating section is close to the first fixed end, the diameter of the first accommodating section is larger than that of the first column section, an oiling space 31 is formed between the first accommodating section and the first column section, and the oil outlet is arranged in the region of the oiling space of the first column section; the fuel oil flows out from the oil outlet and flows into the spiral oil duct through the oil injection space; the atomizing cylinder is communicated with the gas introducing part 28 through the swirl hole 24; the compressed air in the gas introduction portion is rotated by the swirl holes and then introduced into the atomizing cylinder 18.
Alternatively, the oil outlet holes 26 are provided in m, m > =1, and m oil outlet holes are provided in the radial direction of the first column section.
Alternatively, the axial length a of the first column section is 6.5-7.5mm, preferably 7.25mm, and the axial length c of the swirl groove is 4.5-5.5mm, preferably 5.25mm, the axial length of the second column section e is 0.5-1mm, preferably 1mm, the diameters of the first column section and the second column section are equal, d 0 Is 3-6mm in diameter d 0 The number of the chute is 3-4mm, preferably 3.5mm when the number of the chute is less than 4, and 4-6mm when the number of the chute is more than 4; radial depth d of swirl groove 1 0.15-0.45mm, preferably 0.3mm; cross-sectional area s of chute 1 Is 0.01mm 2 -0.03mm 2 Preferably 0.015mm 2 Radial depth d 2 0.05-0.15mm, preferably 0.1mm; cross-sectional area s of spiral oil passage 2 Is 2ns 1 -3ns 1 Preferably s 2 Is 2.5ns 1 Preferably 0.098mm 2 Wherein n is the number of the inclined grooves, and the radial depth d of the spiral oil duct 3 0.125-0.375mm, preferably 0.25mm; total cross-sectional area s of multiple oil outlet holes 3 For 4ms 2 -5ms 2 Preferably 0.40mm 2 Diameter d 4 0.25-0.75mm, preferably 0.5mm; the axial length h of the atomizing cylinder is 12-14mm, preferably 12mm, and the diameter d 5 Is 2d 0 -5d 0 Preferably 13mm; the axial distance b between the d6 swirl hole and the end face of the second column section far from the first fixed end is approximately equal to L/d 5 =1/2, preferably 6.5mm; cross-sectional area s of swirl holes 4 Is 8mm 2 -12mm 2 Preferably 10mm 2 The axial center distance L between the axial midpoint of the swirl hole and the corresponding radial plane of the atomizing cylindrical cavity is 5-7mm, preferably 5.25mm; the angle α of the axis of the chute to the axis of the second column section and/or to the axis of the atomizing cylinder satisfies α=arctan (L/(b-1/2 d) 0 ) Preferably 30 deg..
Alternatively, a: b: c: e=7.25: 6.5:5.25:1, a step of; d, d 0 ：d 1 ：d 2 ：d 3 ：d 4 ：d 5 =3.5: 0.3:0.1:0.25:0.5:13. the number and cross-sectional area of the chute are related to the total fuel quantity value; the fuel flow rate used in this example was about 20mg/s, correspondingly 2 chutes were used; the direction of the chute outlet is opposite to the direction of the swirl hole outlet, so that the fuel and the air can be fully mixed, and the lifting is realizedCombustion quality; the fuel oil leading-in part is communicated with the atomization cylindrical cavity; the first fixed end is in threaded connection with the second fixed end; the first fixed end is of a columnar structure, and the second fixed end is of a columnar accommodating cavity; a sealing gasket 33 is arranged on the transitional contact surface of the first fixed end and the fuel oil transmission guide post, and the sealing gasket is tightly pressed on the axial contact surface of the first fixed end and the second fixed end through the screw fastening of the first fixed end and the second fixed end so as to realize that the fuel oil is sealed without leakage; the fuel inlet is a multi-section ladder columnar cavity, and the tail end ladder columnar cavity section close to one end of the first column section is communicated with the oil outlet; the tail end stepped columnar cavity section is a fuel oil guide pipe, and the diameter of the fuel oil guide pipe is larger than or equal to that of the oil outlet; the oil outlet is vertical to the axis of the tail end stepped columnar cavity section; the swirl holes are uniformly arranged along the circumferential direction of the atomizing cylindrical cavity; the gas introducing part 28 is an annular chamber and is arranged on the outer ring of the atomizing cylinder; the wall thickness between the gas introducing part and the atomizing cylindrical cavity is the cross section area s of the swirl hole 4 0.5-1 times of (2); the gas inlet part is arranged on the outer side of the gas inlet part, and the gas inlet part is further sealed by the shell; the air inlet part is communicated with the gas inlet part and is used for inputting compressed air; the air inlet direction of the air inlet part is parallel to the tangential direction of the air inlet part, and is used for inputting the compressed air into the air inlet part along the tangential direction of the air inlet part; one side of the atomizing cylinder cavity, which is far away from the second fixed end, is open and is used for releasing atomized fuel; the gas introducing part is a closed chamber; the gas cyclone also comprises a mounting matching hole 32 which is arranged on the inner wall of the fuel oil leading-in part of the gas cyclone, the matching clearance between the fuel oil nozzle core and the mounting matching hole is less than or equal to 2 times of the thickness of the boundary layer when fuel oil flows, and the fuel oil channel, the swirl groove and the chute form a fuel oil channel together, and the fuel oil is prevented from leaking when the fuel oil passes through in a small clearance fit way; the fuel oil transmission guide post is in the same line with the axis of the atomization cylindrical cavity; swirl holes 24 are centripetal holes; the interface between the swirl hole and the gas introducing part is arranged at an angle with the axis of the swirl hole; the swirl holes are spiral centripetal holes or radial plane centripetal holes.
In use, the fuel nozzle core 16 is in threaded fastening connection with the gas swirler 17, and the sealing gasket 33 is pressed tightly to realize fuel sealingNo leakage; the gas cyclone is connected with the shell into a whole, so that the air tightness of the shell and the gas cyclone is realized; the air connecting pipe of the air introducing part is connected to the shell, and when the fuel nozzle is used, the fuel inlet on the fuel nozzle core is communicated with an external fuel connector through threaded connection, and the air connecting pipe at the air introducing part is communicated with an external air source, so that the complete fuel nozzle structure function is realized; the fuel enters the oiling space through the fuel inlet via the oil outlet, and enters the swirl groove for rotation through the spiral oil duct on the fuel nozzle core, after the fuel obtains the rotation speed, the fuel is balanced to enter the flow distribution of the chute via the spiral oil duct, and is injected into the atomizing cylinder cavity in a conical shape after entering the chute, meanwhile, the compressed air enters the gas introducing part in a tangential direction through the air introducing part and rotates, and then enters the atomizing cylinder cavity in a tangential direction through the swirl hole. Since structurally the angle α of the chute 11 satisfies α=arctan (L/(b-1/2 d) 0 ) Preferably 30 deg., so that in the atomizing cylinder, the high-speed fuel ejected through the chute is directly impact-blended with the high-speed air entering through the swirl holes 24, and the fuel and air are more uniformly blended through the direct collision of the gas phase and the liquid phase.
1-8, an afterburning supercharging system, in particular for a piston engine, is disclosed and comprises an engine exhaust pipe 1, an afterburning combustor 2, a turbocharger 3 and an integral starting motor 4; the afterburner 2 comprises a heating element, a nozzle, a jet combustion chamber and a swirl combustion chamber, wherein the nozzle uses the fuel atomizing nozzle.
The engine exhaust pipe 1 is connected with the afterburner 2; the engine exhaust pipe inlet 8 is connected with an engine exhaust port, the supercharger outlet 10 is connected with an engine air box, and the air introducing part 14 of the afterburner 2 is communicated with the engine air box.
The starting integrated motor 4 is fixed on the supercharger 3 through the motor bracket 11, the shaft of the starting integrated motor 4 and the shaft of the turbocharger 3 transmit torque through the coupling 12, the starting integrated motor 4 drags the turbocharger 3 to rotate when the engine starts, compressed air provided by the turbocharger 3 enters an engine air box through the supercharger outlet 10, scavenging pressure is provided for the engine start, and the engine can be easier to start on a plateau.
After the engine is started, engine exhaust enters a swirl combustion chamber 6 of the afterburner 2 through an exhaust pipe 1 of the engine, compressed air provided by the turbocharger 3 enters a jet combustion chamber 7 of the afterburner 2 through an air inlet 14 of the afterburner through an engine air box, fuel oil enters the jet combustion chamber 7 of the afterburner 2 through a fuel oil inlet 13 of the afterburner, and contacts with air entering the air inlet 14 of the afterburner under the action of a silicon nitride heating rod 15 in the jet combustion chamber 7 of the afterburner 2 to finish the ignition process of the afterburner 2, the ignited high-temperature fuel gas enters the swirl combustion chamber 6 of the afterburner 2 from the jet combustion chamber 7 of the afterburner 2 to be mixed with the engine exhaust entering the engine exhaust pipe 1 for secondary combustion, HC and CO in the engine exhaust are converted into harmless water and carbon dioxide in the secondary combustion process, and the particulate matters have relatively larger mass and longer retention time in the swirl combustion chamber 6, can be fully combusted, and finally, and harmless matters can be converted into harmless matters to be discharged through an outlet 9 of the afterburner; the turbocharger 3 is flanged to the afterburner 2 at the afterburner outlet 9 and the flange faces are pressed with nuts.
Optionally, 2 engine exhaust pipes 1 are provided and are respectively connected with the first exhaust port and the second exhaust flange.
The high-temperature gas discharged by the afterburner 2 enters the turbocharger 3 to drive the turbine of the turbocharger 3 to work, the turbocharger 3 obtains larger energy, the working mode of the starting integrated motor 4 is changed into a power generation mode, the control of the turbocharger 3 is realized by controlling the power generation amount, the high-temperature gas temperature control of the turbocharger 3 can be realized by controlling the oil quantity entering through the fuel inlet 13 of the afterburner 2, the turbocharger 3 always works in a high-efficiency interval, the two control modes are regulated in a combined mode, the accurate control of the turbocharger 3 can be realized under the condition that the redundant high-temperature gas is not discharged before the turbine of the turbocharger 3, and the high-temperature gas energy which is originally required to be discharged is converted into electric energy to be output. The use of two regulation modes can maximize the recovery efficiency of the exhaust gas energy.
One specific working process case of the invention is: when a certain heavy diesel engine works at a rotating speed of 1500rad/min, the pressure ratio of a supercharger is 1.5, the rotating speed of the supercharger is 45000rad/min, and the opening of a turbine bypass valve is 20%. The emission data of the original machine are that the carbon smoke concentration is 2.9FSN and the CO concentration is 900 multiplied by 10 -6 THC concentration is 93×10 -6 NOx concentration of 1450X 10 -6 The total amount of particles was 1.75X10 8 # mL, total mass of particles 3.5X10 -4 Mu g/mL, the geometric average diameter of the particulate matters is 102.5nm, the oil consumption is 180kg/h, and the exhaust temperature is 853K.
At the moment, the afterburning pressurization system adopts the gas supply quantity of 0.0125kg/s and the oil injection quantity of 0.000625kg/s in the afterburner, the oil-gas ratio of the fuel oil and the air of the point combustion chamber is designed to be 0.0613, the combustion temperature in the jet burner reaches 1200K at the highest, and the temperature in the main combustion area reaches 1600K. After the afterburning supercharging system provided by the invention, the soot concentration is reduced from 2.9FSN to 1.7FSN by 41.3%; CO concentration is 900×10 -6 Reduced to 430X 10 -6 The reduction is 38.6%; THC concentration is 93×10 -6 Reduced to 56X 10 -6 The reduction is 39.8%; NO (NO) X The concentration is 1450×10 -6 Reduced to 980X 10 -6 The reduction is 32.4%; the total amount of the particles is 1.75X10 8 The #/mL is reduced to 0.82 multiplied by 10 8 # mL, 53.1% lower; the total mass of the particles is 3.5X10 -4 Mu g/mL was reduced to 2.71X 10 -4 Mu g/mL, 22.6% lower; the geometric mean diameter of the particles is reduced from 102.5nm to 85.6nm by 16.5%.
The energy entering the turbine increases due to the closing of the turbine bypass valve and the energy of the post combustion in the post combustion boost system. At this time, the supercharger speed was increased from 45000rad/min to 53000rad/min, and the pressure ratio was increased from 1.5 to 1.8. At this time, the pressure sensor located at the intake manifold of the engine detects that the pressure ratio of intake air exceeds the demand of the diesel engine, the turbocharger system control unit changes the operation mode of the integrated motor 4 into the generation mode, and increases the generation power to 0.8kW, and the generation amount is 0.6kW/h at this time. The rotation speed of the supercharger is reduced from 53000rad/min to 45000rad/min by increasing the power generation of the starting integrated motor, the pressure ratio is reduced to 1.5, and the pressure ratio required by the operation of the diesel engine is returned. Compared with the matching mode of the traditional supercharger and the diesel engine, which are used for discharging the redundant waste gas through the waste gas bypass valve, the afterburning supercharging system for improving the energy recovery efficiency provided by the invention realizes more utilization of waste gas energy.
Optionally, the afterburner comprises a heating element 15, a nozzle, a jet combustion chamber 7 and a swirl combustion chamber 6; further, the afterburner is an afterburner for afterburning tail gas of a piston engine; the atomizing cylindrical cavity forms a primary rotational flow area of the jet combustion chamber 5; the jet combustion chamber 7 further comprises a secondary swirl zone 19 and a jet zone 20; the fuel nozzle core is used for guiding fuel into the primary swirling area, the primary swirling area is communicated with the secondary swirling area, and the secondary swirling area is communicated with the jet flow area; the heating element is arranged in the secondary rotational flow area and is used for igniting the gas blending atomized fuel in the secondary rotational flow area; the jet flow area is communicated with the swirl combustion chamber.
Optionally, the heating element is a silicon nitride heating rod; the gas is air; the primary swirl zone, the secondary swirl zone and the jet flow zone are cylindrical cavities; the swirl combustion chamber comprises a plurality of shell surfaces, an outlet pipeline 21 is arranged on the first shell surface, the outlet pipeline extends from the outside of the shell to the inside of the swirl combustion chamber to the center position of the inside of the swirl combustion chamber, and the ratio of the diameter of the jet flow area to the diameter of the secondary swirl area is 3:5 to 2:5; a first exhaust port 22 and/or a second exhaust port 23 are/is arranged on a third housing surface and/or a fourth housing surface adjacent to the first housing surface and the second housing surface respectively; cross-sectional area of air introduction portion 14: cross-sectional area of the first exhaust port: the ratio of the sectional areas of the second exhaust ports is 1:1:1. further, the ratio of engine displacement to volume of the blended combustion chamber is 50:1 to 65:1.
Further, the cross section of the swirl combustion chamber is a rounded rectangular cavity or original shape.
Optionally, the first exhaust interface and the second exhaust interface are respectively connected with the engine exhaust pipe 1, tail gas generated after engine combustion enters the cyclone combustion chamber along the tangential direction through the first exhaust interface and the second exhaust interface, cyclone is formed in the cyclone combustion chamber to be fully mixed, HC, CO and carbon core particles in the engine tail gas are further combusted in the cyclone combustion chamber to be converted into CO2 and H2O, and chemical energy is released.
Optionally, the first exhaust interface and the second exhaust flange are arranged on two sides of the cyclone combustion chamber relatively with the outlet pipeline 21 as a boundary, and engine tail gas enters the cyclone combustion chamber from two sides along tangential directions respectively, so that opposite air flow is convenient to form cyclone in the combustion chamber, and the opposite air flow and high-temperature fuel gas entering the combustion chamber through the jet flow area are fully mixed, so that better secondary combustion effect is achieved.
Optionally, a gas introduction hole 25 is arranged on one side of the gas introduction part 14, which is close to the secondary cyclone area, and the gas introduction hole is a centripetal hole and is communicated with the air introduction part and the secondary cyclone area; the axis of the gas leading-in hole is arranged at an angle with the axis of the secondary rotational flow area; tangential velocity can be generated when the gas flows through the cyclone separator, so that the cyclone separator is convenient to generate; the gas introduction portion has the same cross-sectional area as the swirl hole 24.
Optionally, the fuel nozzle core 16 is a detachable nozzle, the end face of the fuel nozzle is sealed by a sealing gasket, and the heating element 1 is tightly attached by bolt pretightening force to perform conical surface sealing.
Optionally, the jet zone is connected with a swirl combustion chamber; the volumes of the first-stage swirl area, the jet flow area, the second-stage swirl area and the chamber of the swirl combustion chamber are sequentially increased.
In use, when the burner is operated prior to the engine: the heating rod 1 is preheated in advance, and fuel oil enters the nozzle through the fuel oil inlet 13, is sprayed out through the fuel oil guide pipe and the oil outlet 26, flows through the spiral oil duct 27 on the fuel oil nozzle core, enters the chute 29 at the tail end of the spiral oil duct and is sprayed into the primary rotational flow area; the gas enters the gas introducing part 28 from the air introducing part, one part flows into the primary cyclone region through the cyclone holes of the primary cyclone region, and the other part directly enters the secondary cyclone region from the gas introducing hole of the secondary cyclone region; the fuel oil is fully mixed with the gas entering the cyclone holes of the primary cyclone in the primary cyclone area, enters the secondary cyclone area, is ignited by a heating rod extending into the secondary cyclone area, starts to mix and burn, and is mixed with the gas entering the gas inlet hole of the secondary cyclone area to continue burning; and then enters a jet flow area, and meanwhile, flame is reversely spread to a primary rotational flow area, and the heating rod is powered off, so that the ignition process is completed.
When the engine is operated prior to the burner: after the engine is started, after the exhaust gas temperature of the engine reaches a threshold value (300 ℃ in general), the heating rod 1 is preheated, fuel oil enters the nozzle through the fuel oil inlet and then enters the first-stage swirl zone through the chute at the tail end of the spiral oil duct from the fuel oil guide pipe 30, the fuel oil is mixed with the gas from the air introducing part in the first-stage swirl zone and enters the second-stage swirl zone to start mixed combustion, then enters the swirl combustion chamber through the jet flow zone to perform secondary combustion, the high-temperature tail gas is ignited in the swirl mixed combustion chamber, the flame is transmitted back to the first-stage swirl zone, and then the heating rod 1 is closed to complete the ignition process.
The high-temperature fuel gas in the first-stage swirl zone enters the second-stage swirl zone to be continuously mixed with the gas for combustion, then enters the jet flow zone to expand and accelerate, enters the swirl combustion chamber, is mixed with the tail gas of the piston engine entering the swirl combustion chamber through the first exhaust interface for secondary combustion, and HC, CO and carbon nuclear particles are continuously combusted in the secondary combustion process to be converted into CO 2 And H 2 O releases energy, and the completely combusted gas is discharged through an outlet pipeline of the cyclone combustion chamber.
The primary swirl zone of the invention realizes the full mixing of gas and fuel through the swirl holes opposite to the chute, and meanwhile, the gas and fuel flow in the primary swirl zone is slower than that in the secondary swirl zone, so that the mixed gas can be fully combusted in the primary swirl zone, and the primary swirl zone is a main combustion zone after stable combustion. The secondary swirl zone realizes ignition during starting and simultaneously serves as a secondary combustion zone to carry out combustion reaction. Firstly, gas enters the combustor along the tangential direction, a pre-rotation effect is formed in a cavity of an air introducing part, and part of the gas enters a first-stage rotational flow area along the tangential direction through a side wall surface rotational flow hole of the cavity of the first-stage rotational flow area to form a first-stage rotational flow; the other part of the gas enters the secondary swirl zone tangentially along the burner through a gas inlet hole on the side wall of the gas inlet part to generate secondary swirl; the jet flow area accelerates the expansion of the high-temperature fuel gas and enters the cyclone combustion chamber.
The primary cyclone area enters the secondary cyclone area and is primary cyclone; when the gas enters the secondary cyclone area from the air inlet part, the gas passes through the gas inlet holes (the cyclone holes in shape) to naturally generate cyclone, and the gas inlet holes are uniformly and circularly distributed along the section and form secondary cyclone when the gas and the primary cyclone are converged in the secondary cyclone area, so that the primary cyclone is enhanced.
The jet flow is realized through a jet flow area, the jet flow area is communicated with a secondary rotational flow area and a rotational flow combustion chamber, the inner space of the secondary rotational flow area is smaller than that of the rotational flow combustion chamber, so that pressure difference is generated at two sides of the jet flow area, rotational flow is accelerated through the jet flow area, and after entering the rotational flow combustion chamber, the rotational flow is separated from the constraint of the pipe wall of the jet flow area, so that jet flow is formed.
Optionally, the engine air box is connected with the air introducing part 14 of the afterburner 2, and the starting integrated motor 4 is connected with a turbocharger shaft through a coupling and transmits torque.
The cantilever rotor device comprises a rotating shaft 33 and a radial turbine 34, wherein a bearing 35, a centrifugal compressor impeller 36, an axial radial damper 37 and the radial turbine 34 are sequentially arranged on the rotating shaft 33 from front to back.
The heat insulation sealing device 5 is positioned between the centrifugal compressor impeller and the radial turbine, one side of the centrifugal compressor impeller is connected with the bearing in an end face matching way, the other side end face of the centrifugal compressor impeller is connected with the axial radial damper, and the bearing, the centrifugal compressor impeller and the axial radial damper are pressed on the shaft shoulder of the rotating shaft by adopting the front end nut, so that the rotor system is assembled.
The centrifugal compressor impeller and the radial turbine adopt back-to-back mode, and the middle is separated by an axial radial damper and a heat insulation sealing device. The bearing is positioned at the forefront end of the rotating shaft and supports the whole rotor system, and the rotor is supported by the cantilever. When the rotor system rotates at a high speed, air entering from the front end of the impeller of the compressor is centrifuged. Part of it is cooled by the bearing.
Meanwhile, the axial radial damper can generate axial and radial damping when the rotor system runs, so that the vibration energy of the rotor is dissipated; a first small gap is formed between the axial end face of the axial radial damper and the static part, and a second small gap is formed between the radial outer cylindrical surface of the axial radial damper and the static part; and along with the high-speed rotation of the rotating shaft, the air flows in the first small gap and the second small gap are rotated and extruded at high speed, and the effect of vibration energy of the rotor is dissipated, so that the stable operation of the cantilever type rotor device is ensured.
The heat insulation sealing device is fixed on the static component, the inside is ventilated, and the heat radiated and transferred by the fuel gas can be taken away, so that the heat insulation is realized. The high-pressure gas leaked from the dynamic-static interface is sealed by the cooperation between the inner cylindrical surface of the heat insulation sealing device and the rotating shaft. Further, the inner cylindrical surface of the heat insulation sealing device is matched with the outer cylindrical surface of the rotating shaft to form a third small gap, the rotating shaft 1 rotates at a high speed to drive air flow in the third small gap to rotate at a high speed, a rotary sealing effect is achieved, and high-pressure air is sealed.
The gap width is related to the rotating speed and the pressure value in the disc cavity, and under the working conditions that the working rotating speed is 120000-16000rpm and the disc cavity pressure is 1.1 standard atmospheric pressure, the widths of the first small gap and the second small gap are 0.4mm-0.5mm, so that a better vibration reduction effect can be achieved.
The width of the gap between the inner cylindrical surface of the heat insulation sealing device and the outer cylindrical surface of the rotating shaft is related to the design rotating speed and the pressure, and the width of the third small gap is 0.4mm-0.5mm under the working condition that the working rotating speed is 120000-16000rpm and the pressure is 1.1 atmospheric pressure, so that the effect of better maintaining the stability of the rotor can be achieved.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention.
Claims (8)
1. A fuel atomizing nozzle of a burner comprises a fuel nozzle core and a gas cyclone, and is characterized in that,
the fuel nozzle core comprises a first fixed end and a fuel transmission guide post;
the gas cyclone comprises a fuel oil introducing part, an air introducing part and an atomization cylindrical cavity;
the first fixed end is provided with a fuel inlet;
the fuel oil transmission guide post is sequentially provided with a first post section, a swirl groove and a second post section, wherein the first post section is close to the first fixed end, and the second post section is far away from the first fixed end;
the first column section is provided with an oil outlet and a spiral oil duct, and the spiral oil duct is used for spirally conveying the fuel oil output from the oil outlet to the swirl groove;
the swirl groove is used for injecting fuel into the chute after rotating;
the second column section is provided with a chute which is communicated with the swirl groove and the atomizing cylindrical cavity; the chute is used for injecting fuel into the atomization cylindrical cavity;
the first fixed end is provided with a fuel inlet which is communicated with the oil outlet;
the fuel oil leading-in part is connected with the atomization cylindrical cavity and comprises a containing cavity and a second fixed end; the accommodating cavity is used for accommodating the fuel oil transmission guide post, and the second fixed end is used for connecting the first fixed end;
the accommodating cavity is sequentially provided with a first accommodating section and a second accommodating section; the first accommodating section is close to the first fixed end, the diameter of the first accommodating section is larger than that of the first column section, an oiling space is formed between the first accommodating section and the first column section, and the oil outlet is arranged in the region of the first column section located in the oiling space;
the atomizing cylinder is communicated with the air inlet.
2. The fuel atomizing nozzle of claim 1, wherein the swirl slot is a radial annular slot along the fuel delivery post.
3. The fuel atomizing nozzle according to any one of claims 1 to 2, wherein the atomizing cylinder communicates with the air introduction portion through a swirl hole.
4. The fuel atomizing nozzle according to any one of claims 1 to 2, wherein a plurality of the inclined grooves are symmetrically provided; the cross-sectional area of the spiral oil passage is 2-3 times the total cross-sectional area of the plurality of inclined grooves.
5. A fuel atomizing nozzle as set forth in claim 3, wherein the orientation of the chute outlet is disposed opposite the orientation of the swirl orifice outlet.
6. A fuel atomising nozzle according to any of the claims 1-2 wherein the end of the fuel inlet is provided with an end stepped cylindrical cavity section.
7. The fuel atomizing nozzle of claim 6, wherein the outlet orifice is perpendicular to an axis of the terminal stepped cylindrical cavity section.
8. The afterburning supercharging system is characterized by further comprising an engine exhaust pipe, an afterburning combustor, a turbocharger and an integrated starting motor; an afterburner comprising a heating element, a nozzle, a jet combustion chamber and a swirl combustion chamber, wherein the nozzle uses the fuel atomizing nozzle according to any one of claims 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310491126.2A CN116557855A (en) | 2023-05-04 | 2023-05-04 | Fuel atomizing nozzle of combustor and afterburning pressurization system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310491126.2A CN116557855A (en) | 2023-05-04 | 2023-05-04 | Fuel atomizing nozzle of combustor and afterburning pressurization system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116557855A true CN116557855A (en) | 2023-08-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310491126.2A Pending CN116557855A (en) | 2023-05-04 | 2023-05-04 | Fuel atomizing nozzle of combustor and afterburning pressurization system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116557855A (en) |
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2023
- 2023-05-04 CN CN202310491126.2A patent/CN116557855A/en active Pending
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