CN101566353A - Double-vortex combustion chamber - Google Patents
Double-vortex combustion chamber Download PDFInfo
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- CN101566353A CN101566353A CNA2009100838817A CN200910083881A CN101566353A CN 101566353 A CN101566353 A CN 101566353A CN A2009100838817 A CNA2009100838817 A CN A2009100838817A CN 200910083881 A CN200910083881 A CN 200910083881A CN 101566353 A CN101566353 A CN 101566353A
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Abstract
The invention discloses a double-vortex combustion chamber which adopts a full ring shaped flame tube structure and comprises a shell, an inner flame tube and an outer flame tube. The outer wall of the outer flame tube and the inner wall of the shell form a cooling cavity channel; the inner wall of the outer flame tube and the outer wall of the inner flame tube form a combustion channel; oil injection pipes and an igniting seat are arranged on the periphery of the shell; the outer flame tube is an integral forming part, the first section thereof is a diffusion section which adopts a constant pressure gradient design, and the second section thereof is provided with two rows of advancing air holes at the edge of the front wall of a recessed cavity, an evaporating pipe extends into the recessed cavity along the periphery direction of the recessed cavity and close to the inner side of the front wall of the recessed cavity, and the back wall of the recessed cavity is provided with a back air inlet duct at the half height; the third section is provided with an air film cooling air inlet port and an air film cooling air inlet baffle; and the fourth section is provided with a blending hole and a diffusion cooling hole. The double-vortex structure formed in the recessed cavity of the double-vortex combustion chamber improves the distribution of a fuel concentration field, realizes fractional combustion, increases the residence time of fuel combustion, reduces the pollutant discharge and ensures the outlet temperature to be more uniform.
Description
Technical field
The present invention relates to a kind of double-vortex combustion chamber, belong to engine art.
Background technology
The combustion chamber is an important component part of engine, and fuel burns at this, makes chemical energy be converted into heat energy.It is good that good combustion chamber should have an ignition performance, uniformity of temperature profile, and flow resistance loss is little, essential characteristics such as the few and compact conformation of exhaust pollution.
Traditional aircraft engine head of combustion chamber mainly adopts the combination configuration of cyclone and nozzle.Air is by producing a recirculating zone behind the cyclone, the combustion product of high temperature is lighted fresh fuel and AIR MIXTURES in the dirty forward end of the effect of recirculating zone, and the effect of stable incendiary source has been played in the recirculating zone.Standing vortex burning chamber (Trapped vortex combustor is called for short TVC), it has abandoned the traditional combustion chamber design in 40 years in the past.It mainly is made up of two parts, i.e. precombustion chamber and main combustion chamber.Precombustion chamber is used for steady flame, and main chamber is used to provide power.Precombustion chamber provides the retention flame necessary recirculating zone by cavity, and fuel and air inject in the cavity in some way, reaches the effect that improves the fuel concentration field and strengthen the intensity in whirlpool.The cyclone that typical eddy flow stable flame combusting device is arranged in its import department produces main recirculating zone.The combustion product of this regional translator unit heat mixes in the air fuel of injecting burner, forms continuous incendiary source and stable flame.This recirculating zone also can make the burning of whole burner become stable.If the inlet velocity of burner increases, it is unstable that this main recirculating zone will become, and this will cause adverse influence to the stable and efficiency of combustion of flame.Simultaneously, along with the enhancing that countries in the world are paid close attention to the aero-engine exhaust emission, traditional combustion chamber also is faced with the difficult problem of contaminated environment.
External TVC correlative study shows, TVC is applied to the main chamber of the higher ground gas turbine of aero-engine or emission request entirely.Its principal character is in the TVC of ring form, is divided into intension and outer the culvert.Entry of combustion chamber adopts diffuser, and diffuser comprises one or several annular slopes, and its effect is that the air of injecting is divided into different guiding, enters the diffuser runner.The fuel nozzle of main flow area is placed on the outlet of diffuser, in the import of main combustion chamber the place ahead a support plate identical with cavity the place ahead is arranged, and support plate is along circumferentially having many passages, and these passages are used for the combustion product transport outside cavity.The cavity recirculating zone of support plate back is just as at the indoor flameholder of afterbunring.Help to provide burning velocity at the air of cavity inside and the rapid mixing of fuel, this structure can also form and make that getting rid of gas forms the rational temperature field under the situation without injection apparatus.Body also has air and fuel oil to spray into behind cavity simultaneously, and related data shows that the fueller of existing TVC all adopts swirl nozzle or air atomizer spray nozzle both at home and abroad.
Introduced a kind of tangential standing vortex burning chamber among the publication number CN1858498, in its specification clear and definite introduction the structure of standing vortex burning chamber, the high centrifugal acceleration of utilizing tangential swirl to produce is strengthened the two-phase spray combustion.Introduced a kind of gas-turbine engine combustion chamber cartridge module in publication number CN1467407A, oil gas is mixed in advance in premixer, infeeds main flow then, is injected in the combustion chamber and burns; Utilize the principle of fractional combustion to reduce its NOx discharging.At application number 5791148, applying date Aug, 11,1998, introduced the design that standing vortex burning chamber is applied to the aero-engine main chamber among the LINER OF A GAS TURBINE ENGINE COMBUSTOR HAVINGTRAPPED VORTEX CAVITY gas-turbine combustion chamber of chamber (use) in the cavitation, clearly introduced the structure of this combustion chamber in its specification, main flow adopts the triple channel diffuser in conjunction with oil spout bar structure, be responsible for mixing of high-temperature fuel gas and main flow by the diffuser support plate, the cavity fuel feeding adopts pore to surround the structure of oilhole.Introduced a kind of single standing vortex burning chamber among the publication number C N 101070961A, clearly introduced the structure of combustion chamber in its specification, drive pore into and adopt baffle arrangement thereon at the cavity front and rear wall, the air-flow that enters cavity is led, form single vortex structure.
In the above-mentioned combustion chamber, the tangential standing vortex burning chamber of introducing among the publication number CN 1858498 adopts swirl atomizer or pneumatic nozzle, and the whirlpool of staying in the circumferential whirlpool of formation and the cavity influences each other.A kind of gas-turbine engine combustion chamber cartridge module of introducing in publication number CN1467407A is taked fuel and air pre-mixing gas; Main flow is not taked the diffuser structure, to a certain degree limits the main flow flow velocity, takes petal type to prop up plate structure, has increased weight.At application number 5791148, applying date Aug, 11,1998, the standing vortex burning chamber of introducing among the LINER OF A GAS TURBINE ENGINE COMBUSTOR HAVINGTRAPPED VORTEX CAVITY (using the gas-turbine combustion chamber in chamber in the cavitation) is applied in the design of aero-engine main chamber, main flow is taked oil spout bar fuel feeding, and weight is bigger; Adopt support plate diffuser structure, weight is bigger; Cavity fuel feeding and air admission hole are taked around structure, and be unfavorable to the formation of staying the whirlpool.The single-vortex combustion chamber of introducing among the publication number CN101070961A adopts baffle arrangement on the cavity, increased weight; The single vortex structure that forms in the cavity makes the fuel concentration field distribution even inadequately, and its time of staying in the cavity internal combustion falls short of, and has limited the further lifting of combustibility to a certain extent.
Summary of the invention
The invention provides a kind of novel oil-poor two standing vortex burning chambers, after having omitted the main flow fuel feeding and being used for the support plate of blending and the blast fence structure on the cavity, reduced standing vortex burning chamber weight effectively; Adopt evaporation tube as fueller at cavity, realized the raising of efficiency of combustion; On the cavity front and rear wall, open suitable air admission hole and air inlet duct air inlet, in the chamber, form two vortex structures.Thereby realize widening of TVC range of application.
Described double-vortex combustion chamber is useful under high speed, the high temperature inlet air flow condition and works.The pressure that utilizes high speed inlet air flow stagnation to produce makes cooling blast enter in the burner inner liner by the air film cooling air admission hole and the diffusion cooling hole of outer burner inner liner, plays the effect of cooling; Utilize the steady flame effect of cavity, make igniting, the fuel-lean blowout border of combustion chamber under high velocity air widen.The air inlet meeting of the cavity rear wall of double-vortex combustion chamber middle part makes and forms two vortex structures in the cavity that the retention flame is mainly played in the whirlpool that is positioned at the cavity bottom, can be regarded as a fixing point burning things which may cause a fire disaster; Cavity is to make the better blending of hot combustion gas at primary air and top against the effect of the secondary vortices of main flow air-flow position, improves combustibility.
The present invention is a kind of double-vortex combustion chamber, adopts full-annular type burner inner liner structure, comprises housing, internal layer burner inner liner, outer flame tube, and the outer wall of described outer flame tube and the inwall of described housing are formed the cooling chamber passage of combustion chamber; The outer wall of the inwall of described outer flame tube and described internal layer burner inner liner is formed the burning gallery of combustion chamber; Described housing is circumferentially evenly arranged spray bar and igniting seat, and the spout of spray bar is inserted into the inside of evaporation tube air inlet.
The described outer flame tube part that is formed in one, outer flame tube matrix is formed by first section, second section, the 3rd section, the 4th section; First section is the diffuser of taking the design of equal pressure gradient, second section cavity antetheca edge circumferentially evenly arranges the preceding air admission hole of two rows, the circumferential angle of air admission hole differs 1.5 ° before two rows, evaporation tube evenly arranges and the medial surface of pressing close to the cavity antetheca extend in the cavity along the cavity circumferential direction, and cavity rear wall 1/2nd is highly located the back air inlet duct circumferentially evenly arranged; The 3rd section is the outlet corner segments, circumferentially evenly arranges air film cooling air admission hole, and the air admission hole of side position circumferential arrangement air film cooling within it baffle plate, and described air film cooling air admission hole baffle plate is relative with air film cooling air admission hole; The 4th section is outlet section, adopts expanded form, and expansion angle circumferentially evenly has two row's blending hole and three row's diffusion cooling hole from the horizontal by 20 ° of angles, and the circumferential angle of two row's blending hole differs 4.5 °, and the circumferential angle of three row's diffusion cooling hole differs 1.5 °.
Air admission hole entered in the cavity and flows up to cavity rear wall change flow direction along the cavity bottom transverse before air admission hole and back air inlet duct before the cavity of described outer flame tube, gas were arranged from two of cavity antetheca; Gas laterally is blown in the cavity in the other direction from the back air inlet duct of cavity rear wall medium position; Entrainmented when part mainstream gas is flowed through cavity and entered cavity; The acting in conjunction of three strands of gases interacts, and can form each swirl flow up and down in cavity, realizes " two whirlpool " structure.
Outer flame tube outlet edge Outboard Sections that described outer flame tube matrix is the 4th section and shell rim place inner closed, the end of forming the cooling chamber passage, utilize high velocity air to flow into the pressure that produces after the cooling chamber passage stagnation, air admission hole, back air inlet duct, blending hole, air film cooling air admission hole and diffusion cooling hole flow into cavity inside and burning gallery respectively in the past.
Described spray bar and evaporation tube are formed the fuel feeding assembly, and evaporation tube circumferentially is evenly arranged between outer flame tube and the housing.
Described evaporation tube adopts branched structure, is divided into along four circumferential outlets by single import, and the evaporation tube air inlet is the horn mouth shape, and two evaporation tube outlets are wherein arranged along the pipeline section both sides that circumferential direction stretches, and outside wall surface is opened two evaporation tube outside wall surface outlet openings.
Described evaporation tube evenly arranges and the medial surface of pressing close to the cavity antetheca extend in the cavity along the cavity circumferential direction, and built-in length makes that air admission hole is on the same horizontal line before second row of evaporation tube outside wall surface outlet opening and cavity antetheca.
Double-vortex combustion chamber of the present invention adopts poor oil firing, and main flow does not have fuel feeding.
The invention has the advantages that:
(1) has than conventional axial combustion chamber and be more suitable for burning organizational form under high speed inlet air flow condition, omitted complicated cold gas stream technically, reduced aerodynamic loss, and the curved cavity simplicity of design, the complexity of structure and the weight of whole combustion chamber reduced;
(2) fueller adopts the mode that spray bar combines with evaporation tube, spray bar is inserted in the evaporation tube, volume required little, simple in structure, fuel oil energy accurately sprays in the evaporation tube simultaneously, whole evaporation tube places the higher air-flow of temperature, helps the evaporation and the atomizing of fuel oil, has improved the efficiency of combustion of fuel oil in whole combustion chamber;
(3) the cavity outlet section is provided with air film cooling air admission hole, the blending hole structure alternate with diffusion cooling hole, from air film cooling air admission hole, the gas that blending hole and diffusion cooling hole enter with flow into burning gallery from the cooling chamber passage, form the air film of one deck cover outlet section, improved the life-span of burner inner liner and improved the combustor exit Temperature Distribution.
(4) the two vortex structures that form in the cavity have improved the fuel concentration field distribution, realize fractional combustion, have increased the time of staying of oil inflame, have reduced the discharging of pollutant, have especially suppressed the generation of nitrogen oxide NOx.
(5) the further blending of combustion gas meeting that in the double-vortex combustion chamber burn and produce in the whirlpool district of the combustion gas of the whirlpool district burning generation of the interior close cavity of cavity bottom and close main flow airflow position makes that the outlet temperature of standing vortex burning chamber is more even.
Description of drawings
Fig. 1 is a double-vortex combustion chamber structural representation of the present invention;
Fig. 2 is the structural representation of outer flame tube of the present invention;
Fig. 3 is the axial sectional structure schematic diagram of double-vortex combustion chamber of the present invention;
Fig. 4 is the structural representation of fuel feeding assembly of the present invention;
Fig. 5 is the left sectional structure schematic diagram of fuel feeding assembly of the present invention;
Fig. 6 is that embodiment of the invention cavity inner shaft is to contoured velocity;
Fig. 7 is that embodiment of the invention cavity inner shaft is to flow field figure.
Among the figure:
1-housing 2-outer flame tube 3-internal layer burner inner liner 4-spray bar
5-cooling chamber passage 6-burning gallery 7-fuel feeding assembly 8-light a fire the seat
201-outer flame tube matrix 202-evaporation tube 203-blending hole
204-disperses air inlet duct hole behind the cooling 205-air film cooling air admission hole 206-
The 207-air film cools off first section of air admission hole baffle plate 208-outer flame tube matrix
The 3rd section of second section 210-outer flame tube matrix of 209-outer flame tube matrix
Air admission hole before the 4th section 212-cavity 213-of 211-outer flame tube matrix
The outlet of 214-evaporation tube air inlet 215-evaporation tube
216-evaporation tube outside wall surface outlet opening 401-spout
The specific embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
The present invention is a kind of double-vortex combustion chamber, as shown in Figure 1, comprises housing 1, outer flame tube 2 and internal layer burner inner liner 3.Housing 1 is circumferentially evenly arranged 8 and ten spray bars 4 of five igniting seats.
As shown in Figure 2, it is four sections that outer flame tube matrix 201 is divided into, promptly first of outer flame tube matrix section 208, second section 209 of outer flame tube matrix, the 3rd section 210 of outer flame tube matrix, the 4th section 211 of outer flame tube matrix.
As shown in Figures 2 and 3, the inwall of the outer wall of internal layer burner inner liner 3 and outer flame tube 2 is formed for the burning gallery 6 that gas mixture burns in the high temperature and high speed air-flow.The outer wall of outer flame tube 2 and housing 1 inwall form cooling chamber passage 5, utilize high velocity air to flow into the pressure that produces after the stagnation, preceding air admission hole 213 and the back air inlet duct 206 of a part of tolerance that makes the air-flow that enters cooling chamber passage 5 by the cavity 212 of outer flame tube 2 enters into and participates in burning in the cavity 212, remaining tolerance is from the air film cooling air admission hole 205 of outlet section, and blending hole 203 and diffusion cooling hole 204 enter into burning gallery 6 and carry out blending and cooling wall.Do not take the diffuser structure different with a kind of gas-turbine engine combustion chamber cartridge module main flow of introducing among the publication number CN 1467407A, diffuser is adopted in burning gallery 6 imports of the present invention, and the equivalent diffusion angle is 14 °; Expanding channel is taked in burning gallery 6 outlets, and expanding channel is from the horizontal by 20 ° of angles.At housing 1 along ten spray bars 4 circumferentially evenly are installed, in the middle of adjacent two spray bars 4, with spray bar 4 at a distance of 22.5 ° of axial locations along five igniting seats 8 circumferentially evenly are installed, by the ignition tip equipment igniting that trapped vortex combustion is outdoor is prepared.With a kind of gas-turbine engine combustion chamber cartridge module main flow of introducing among the publication number CN1467407A take fuel and air pre-mixing gas and with application number 5791148, applying date Aug, 11,1998, the standing vortex burning chamber main flow of introducing among the LINER OFA GAS TURBINEENGINE COMBUSTOR HAVING TRAPPED VORTEX CAVITY (using the gas-turbine combustion chamber in chamber in the cavitation) is taked oil spout bar fuel feeding difference, the present invention adopts fuel feeding assembly 7 fuel feeding, as shown in Figure 4, fuel feeding assembly 7 is made up of spray bar 4 and evaporation tube 202.Different with the fuel feeding assembly of single standing vortex burning chamber of introducing among the publication number CN101070961A, the spout 401 of spray bar 4 of the present invention is inserted into the inside of the evaporation tube air inlet 214 of evaporation tube 202, as shown in Figure 5, the spout 401 of spray bar 4 is inserted into the inside of evaporation tube air inlet 214, being sprayed onto in the evaporation tube 202 of the fuel oil energy entirely accurate of spray bar 4 spouts 401 ejections, evaporation tube 202 adopts branched structure, be divided into along four circumferential outlets by single import, evaporation tube air inlet 214 is the horn mouth shape, two evaporation tube outlets 215 are wherein arranged along the pipeline section both sides that circumferential direction stretches, and outside wall surface is opened two evaporation tube outside wall surface outlet openings 216.The evaporation tube air inlet 214 of horn mouth shape makes evaporation tube 202 can utilize the ejector action of the fuel oil of spray bar 4 ejections can increase the air inflow of evaporation tube 202 again.Evaporation tube 202 is evenly arranged along cavity 212 circumferential direction, and the medial surface of pressing close to cavity 212 antethecas extend in the cavity 212, and built-in length makes that air admission hole 213 is on the same horizontal line before second row of evaporation tube outside wall surface outlet opening 216 and cavity 212 antethecas of evaporation tube 202.The air that flows to from cooling chamber passage 5 also flow in the evaporation tube 202.In evaporation tube 202, fuel oil and high-temperature gas carry out blending, and heat absorption evaporation, the gas mixture of the ejection in the evaporation tube 202 is injected to cavity 212 inside, the wherein connection flame effect of when the purpose of the gas mixtures of evaporation tube outlet 215 ejections is to light a fire, playing, two evaporation tube outside wall surface outlet openings 216 of outside wall surface make the fuel emission direction consistent with the airintake direction of cavity antetheca, thereby with gas flow in the cavity 212, form two vortex fields structure, cause to produce different fuel concentration fields in the cavity 212, realize fractional combustion.With a kind of gas-turbine engine combustion chamber cartridge module of introducing among the publication number CN1467407A and with application number 5791148, applying date Aug, 11,1998, it is different to have introduced a kind of single standing vortex burning chamber among the standing vortex burning chamber of introduction and the publication number CN101070961A among the LINER OFA GAS TURBINE ENGINE COMBUSTORHAVING TRAPPED VORTEX CAVITY gas-turbine combustion chamber of chamber in the cavitation (use), the cavity antetheca edge of cavity 212 of the present invention opens the preceding air admission hole 213 of two rows, be used to strengthen the antetheca air inflow, / 2nd height and position places of rear wall have back air inlet duct 206, be used for air inlet, change rear wall air inlet position, improve air inflow simultaneously to a certain extent and guarantee the air-flow uniformity; Blast fence and reverse flow baffle do not lead to gas flow in the cavity 212 before and after not having on the cavity 212.As shown in Figures 2 and 3, flow in the cooling chamber passage 5 surplus air some from two row's air admission holes 213 of cavity 212 antethecas, flow in the cavity 212, the air that flows into cavity 212 is mobile cavity 212 in along the direction of parallel cavity 212 bottoms and back body; A part flows into air in the cooling chamber passage 5 when flowing through cavity 212 between first section 208 and the 3rd section 210 of outer flame tube matrix 201, because the pressure differential effect inside and outside the cavity 212, air inlet duct 206 flows into cavity 212 with vertical cavity 212 rear wall directions along the back; The air that flows into cavity 212 from cavity 212 preceding two row's air admission holes 213 is sheared mutually with the air that flows into cavity 212 from back air inlet duct 206, promptly forms a whirlpool near cavity 212 bottom positions in cavity 212 the first half; The primary air that flows into burning gallery 6 enters cavity 212 owing to entrainment the effect meeting by portion of air when flowing through cavity 212; Entrainmented the portion of air that enters cavity 212 air that flows into cavitys 212 from preceding two row's air admission holes 213 of cavity 212 and back air inlet duct 206 and the primary air and sheared mutually, also can be formed a whirlpool in the mobile position of the promptly close main flow of cavity 212 the latter halfs; Gas in some cooling chamber passage 5 enters cavity 212 from air film cooling air admission hole 205, by air film cooling air admission hole baffle plate 207 guiding, flows into burning gallery 6 along cavity 212 outlet sections and the 4th section 211 walls pasting the burner inner liner matrix; Air in the cooling chamber passage 5 of last part flows into burning gallery 6 by blending hole 203 and diffusion cooling hole 204.
Different with the high centrifugal acceleration reinforcement two-phase spray combustion that the tangential swirl of a kind of tangential standing vortex burning chamber utilization generation of introducing among the publication number CN1858498 produces, the present invention is by the preceding air admission hole 213 of two rows, back air inlet duct 206 and main flow are entrainmented the gas that flows in the cavity 212, gas mixture with evaporation tube 202 ejections, form in " two whirlpool ", " stay " in cavity 212, thereby realize fractional combustion, improved the performance of combustion chamber; The cold air jet that comes out from each pore forms attached wall air film at the burner inner liner inwall simultaneously, and flame tube wall and combustion gas are isolated.Because the heat exchange amount increases the good buffer action with air film greatly in the hole, has improved cooling effectiveness, has guaranteed the double-vortex combustion chamber reliably working.
At first intake air flow and the desirable oil-gas ratio according to the combustion chamber designs burning gallery 6 areas of burner inner liner and the ratio of cooling chamber passage 5 areas, determine open area according to the ideal velocity of combustor exit then, in order to guarantee that the burner inner liner import is current limliting cross section, combustion chamber, discharge area must be greater than the burner inner liner inlet-duct area.In order to guarantee the stable operation range of combustion chamber broad, when gross gas-oil ratio was 0.003, the oil-gas ratio in the evaporation tube 202 was 0.2～0.3, and the equivalent proportion in the whole cavity 212 is 0.36～0.54.According to the equivalent proportion in the cavity 212 is 0.36～0.54, and optimal design is to determine that tolerance is distributed in the cooling chamber.For guaranteeing that pore is to the good cooling capacity of burner inner liner on the cavity 212, design cavity 212 forebody-afterbody intake velocities are 120m/s, again according to the area of whole cooling chamber passage 5 imports, just can determine to cool off tolerance and distribute and the structural arrangement parameter.Now lift an optimum parameter design: air admission hole 213 diameters are 3mm before two rows, every row is along circumferentially distributing 120, throughput accounts for 24% of whole cooling chamber passage 5 flows, back air inlet duct 206 width are 1.7mm, along circumferentially distributing 9, throughput accounts for 21% of whole cooling chamber passage 5 flows, air film cooling air admission hole 205 diameter 3mm, along circumferentially distributing 90, throughput accounts for 9% of whole cooling chamber passage 5 flows, blending hole 203 diameter 6mm, along circumferentially distributing 40,42%, three row's diffusion cooling hole, 204 diameters that two round throughputs account for whole cooling chamber passage 5 flows are 1mm, every row is along circumferentially distributing 120, and the throughput of three rounds accounts for 4% of whole cooling chamber passage 5 flows.For above specific design case, carried out feasibility study by the method for three-dimensional numerical value simulation.Because 10 evaporation tubes 202 are along circumferentially evenly distributing, get final product so only need that the monocycle model of two heads is wherein carried out numerical simulation.Its condition for import is all by the real case setting.
Fig. 6 is that this combustion chamber cavity inner shaft is to contoured velocity figure, as can be seen from Figure 6, because the front and back air inlet of cavity and the interaction that main flow is entrainmented three strands of gases, in cavity, can form stable significantly two vortex structure flow field, the speed numerical values recited shows and divides a cloth to find out in the cavity on Fig. 6 the right, is in low regime in the whirlpool.
Fig. 7 is the inner cold flow field figure of this combustion chamber cavity, and is as can be seen, bigger near the last whirlpool of cavity bottom, the vortex core position of Maelstrom roughly is in the cavity center, under hot situation, this whirlpool can play the retention flame like this, can be regarded as a fixing incendiary source; Also have a whirlpool at the Maelstrom lower position, but less, can claim secondary vortices or little whirlpool, because its hot combustion gas blending better faster that the mainstream gas that flows through burning gallery and bottom are produced, thereby combustibility improved.The Study on Three Dimensional Numerical Simulation result shows to the double-vortex combustion chamber flow field, and this scheme satisfies efficient, the smooth combustion requirement under the high speed inlet air flow condition.
Claims (3)
1, double-vortex combustion chamber adopts full-annular type burner inner liner structure, comprises housing, internal layer burner inner liner, outer flame tube, and the outer wall of described outer flame tube and the inwall of described housing are formed the cooling chamber passage of combustion chamber; The outer wall of the inwall of described outer flame tube and described internal layer burner inner liner is formed the burning gallery of combustion chamber; The described outer flame tube part that is formed in one, outer flame tube matrix is formed by first section, second section, the 3rd section, the 4th section, first section is the diffuser of taking the design of equal pressure gradient, the 4th section is outlet section, adopt expanded form, expansion angle circumferentially evenly has two row's blending hole and three row's diffusion cooling hole from the horizontal by 20 ° of angles, the circumferential angle of two row's blending hole differs 4.5 °, and the circumferential angle of three row's diffusion cooling hole differs 1.5 °; Housing is circumferentially evenly arranged spray bar and igniting seat, and spray bar and evaporation tube are formed the fuel feeding assembly, and evaporation tube circumferentially is evenly arranged between outer flame tube and the housing, it is characterized in that:
The spout of spray bar is inserted into the inside of evaporation tube air inlet; Described evaporation tube adopts branched structure, is divided into along four circumferential outlets by single import, and the evaporation tube air inlet is the horn mouth shape, and two evaporation tube outlets are wherein arranged along the pipeline section both sides that circumferential direction stretches, and outside wall surface is opened two evaporation tube outside wall surface outlet openings;
Second section cavity antetheca edge of outer flame tube matrix circumferentially evenly arranges the preceding air admission hole of two rows, the circumferential angle of air admission hole differs 1.5 ° before two rows, evaporation tube evenly arranges and the medial surface of pressing close to the cavity antetheca extend in the cavity along the cavity circumferential direction, and cavity rear wall 1/2nd is highly located the back air inlet duct circumferentially evenly arranged; The 3rd section is the outlet corner segments, circumferentially evenly arranges air film cooling air admission hole, and the air admission hole of side position circumferential arrangement air film cooling within it baffle plate, and described air film cooling air admission hole baffle plate is relative with air film cooling air admission hole.
2, double-vortex combustion chamber according to claim 1, it is characterized in that: air admission hole entered in the cavity and flows up to cavity rear wall change flow direction along the cavity bottom transverse before air admission hole and back air inlet duct before the cavity of described outer flame tube, gas were arranged from two of cavity antetheca; Gas laterally is blown in the cavity in the other direction from the back air inlet duct of cavity rear wall medium position; Entrainmented when part mainstream gas is flowed through cavity and entered cavity; Three bursts of gas actings in conjunction interact, and form each swirl flow up and down in cavity, realize " two whirlpool " structure.
3, double-vortex combustion chamber according to claim 1, it is characterized in that: evaporation tube evenly arranges and the medial surface of pressing close to the cavity antetheca extend in the cavity along the cavity circumferential direction, and built-in length makes that air admission hole is on the same horizontal line before second row of the evaporation tube outside wall surface outlet opening of evaporation tube and cavity antetheca.
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| CN2009100838817A CN101566353B (en) | 2009-05-11 | 2009-05-11 | Double-vortex combustion chamber |
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| CN2009100838817A CN101566353B (en) | 2009-05-11 | 2009-05-11 | Double-vortex combustion chamber |
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Inventor after: Zhang Rongchun Inventor after: Fan Weijun Inventor after: Song Shuangwen Inventor after: Song Xuanjin Inventor after: Yang Maolin Inventor before: Fan Weijun Inventor before: Song Xuanjin Inventor before: Zhang Rongchun Inventor before: Xing Fei Inventor before: Kong Xianglei |
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Free format text: CORRECT: INVENTOR; FROM: FAN WEIJUN SONG XUANJIN ZHANG RONGCHUN XING FEI KONG XIANGLEI TO: ZHANG RONGCHUN FAN WEIJUN SONG SHUANGWEN SONG XUANJIN YANG MAOLIN |
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