CN101000145A - Combustion chamber of miniature gas turbine with double premixed channel using natural gas - Google Patents
Combustion chamber of miniature gas turbine with double premixed channel using natural gas Download PDFInfo
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- CN101000145A CN101000145A CN 200610000757 CN200610000757A CN101000145A CN 101000145 A CN101000145 A CN 101000145A CN 200610000757 CN200610000757 CN 200610000757 CN 200610000757 A CN200610000757 A CN 200610000757A CN 101000145 A CN101000145 A CN 101000145A
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Abstract
The invention is a natural gas-fired double-premixing channel micro fuel gas engine combustion chamber, a single cylinder-structured 100kw-level micro fuel gas engine combustion chamber, using natural gas as fuel, and having two fuel feed regions, i.e. on-duty torch region and main fuel region, and its greatest character lies in not only adopting lean fuel premixing combustion mode in the main fuel region but also adopting the premixing combustion technique in the on-duty torch region, thus maximuly reducing NOx output, and it is a double-premixing channel, low-NOx exhaust combustion chamber.
Description
Technical field
The present invention relates to the combustion of natural gas technical field, is a kind of ' 100kW level miniature gas turbine combustion chamber device, and this device is fuel for single jar structure with the natural gas, is the combustion chamber of a kind of poor fuel premixed combustion low Nox (NOx) discharging.
Background technology
Distributed energy supply is the main direction of energy technology development, and miniature gas turbine is the major impetus of distributed power generation, distributed energy supply.Miniature gas turbine is meant power in the new-generation system below hundreds of kilowatts, and it generally adopts the backheat circulation, and generating efficiency can reach 30% or higher, comprises compressor, combustion chamber, turbine, regenerator, generator etc.This system architecture compactness, volume is little, the efficient height.Wherein, the combustion chamber is the critical piece of miniature gas turbine, and it is related to the efficient and the discharging of system.For this reason, require the combustion chamber Fuel Consumption of design low, discharging is few, compact conformation, and volume is little, the efficiency of combustion height, resistance is little, and cost is low, long service life.
Along with the raising of national requirements for environmental protection, the pollutant emission standard increasingly stringent, obtaining alap nitrogen oxide (NOx) discharge capacity is the key factor that gas turbine has the market competitiveness.The formation mechanism of NOx has three kinds, i.e. heating power NOx, and fuel NOx and NOx fast, for the combustion chamber of gas turbine natural gas fuel, NOx discharges based on heating power NOx.Therefore, the method for the control NOx of gas turbine gas combustion chamber discharging has two classes, and a class is the low NOx technology of wet method, and another kind of is the low NOx technology of dry method.The low NOx technology of wet method is meant and sprays into water or steam in the combustion chamber, the flame peak temperature reduced, thereby reduce the NOx discharge capacity to greatest extent.Adopt the low NOx technology of wet method owing to need the demineralized water treatment facility, make gas turbine unit cost increase, volume increases, and water spray or steam can increase the discharge capacity of carbon monoxide simultaneously, causes the combustion chamber wall surface corrosion, and shorten service life.Therefore, adopting dry method low Nox (NOx) technology is to improve a kind of attractive method of the miniature gas turbine unit market competitiveness.The low NOx technology of dry method is meant the combustion process by rationalization, from the air distribution angle, guarantees that combustion chamber bulk temperature level is lower, and the NOx content that generates in the combustion process is not exceeded standard.Therefore, the measure of dry method control NOx discharging mainly contains: 1, reduce fuel oxygen concentration on every side; 2, under the less condition of oxygen concentration, keep enough time of staying, make the N in the fuel be difficult for generate NOx, and make the NOx that generated be reduced decomposition through homogeneous phase, heterogeneous reaction; 3, under the condition of excess air, reduce temperature peak, reduce heating power NOx.Technical measures such as flue gas recirculation, fractional combustion, the burning of deep or light deviation, poor fuel premixed combustion have been derived thus.
In February, 1996 the disclosed patent No. be WO 96/02796 and in October, 1998 the disclosed patent No. be to have introduced the structure of the low emission combustor that a kind of gas turbine uses in the patent of US5816050.This combustion chamber flame drum is provided with outer cover outward, and the HTHP air that compressor or regenerator come out is up along flame drum tail, and burner inner liner head air flow channel is an enclosed construction, and head is provided with igniter fuel nozzle and main fuel spray nozzle.Whole combustion chamber is provided with three grades of radial whirl devices, gives seed region and primary zone air supply respectively, and another grade radial whirl device then provides secondary wind.In the middle of the combustion chamber is seed region, is provided with one-level radial whirl device, and seed region is sprayed into by a cylindrical dividing plate and main fuel and separates out, and forms main fuel and sprays into passage, and the outlet of second level radial whirl device is the main fuel spray nozzle outlet.Secondary wind swirler air-flow direction of rotation is opposite with primary zone air-flow direction of rotation with seed region, the reverse burner inner liner that enters.The shortcoming of this structure is that the cylindrical dividing plate of seed region is directly exposed to high temperature combustion zone, need the cooling air, this thigh cooling air need extract from other parts of gas turbine, reduced the performance of combustion chamber, increase the discharge capacity of combustion chamber carbon monoxide, made the operation of unit and startup operating mode worsen.Three grades of radial whirl devices of Bu Zhiing have increased the complexity of Combustion chamber design simultaneously, have improved design cost, and this is disadvantageous for the miniature gas turbine unit.In April, 2002, the disclosed patent No. was that the patent of US6374615B1 has been introduced a kind of method that overcomes above-mentioned shortcoming, the igniter of this combustion chamber is installed in the centre bore, igniter fuel passage, air duct and main fuel-air pre-mixing passage coaxial arrangement, three's outlet is positioned at same plane.The igniter fuel channel outlet is that one group of angle is 30 °～60 ° an outward-dipping spray orifice, makes the fuel ejection retrodeviate from the igniter head.Igniting is not provided with swirler with air duct, but its outlet is nozzle-like outlet.Arranged one group of secondary wind spray orifice that axial direction extends at the sudden expansion position of burner inner liner.At the igniter end hole of radially cutting sth. askew along circumferential arrangement of one group of band angle is arranged, be used for importing one air cooling ignition electric nozzle with air duct from igniting.Compare with above-mentioned patent, this patent has removed the stripper loop of seed region, has simplified the structure of seed region.Have only one group of radial whirl device, but be provided with one group of axial secondary air channel and one group cooling, increased fuel channel simultaneously and sprayed inclined hole and air duct outlet nozzle outward, do not reduce the complexity that designs with the hole of radially cutting sth. askew.Though these two patents all are called the low NOx combustion chamber, the fuel of seed region all is to adopt diffusion combustion mode in two patents, and the reduction amplitude of its NOx is limited, and the growing amount of whole combustion chamber NOx will mainly be determined by the NOx growing amount of seed region.Therefore, be necessary to do further work, the air flow structure of rationalization's seed region makes that the NOx discharge capacity of whole combustion chamber is reduced to greatest extent.
Summary of the invention
Purpose of the present invention just provides a kind of double premixed channel miniature gas turbine combustion chamber of natural gas fuel, is single jar structure, and the combustion chamber is provided with two fuel drainage areas, is respectively torch on duty district and main fuel district.The fuel in torch on duty district uses as igniter fuel when unit starting, as torch on duty, plays the effect of steady combustion when normal operation.The maximum characteristics of this device are the poor fuel premixed combustion modes that not only adopts in the main fuel district, and also adopt the premixed combustion mode in torch on duty district, thereby reducing the growing amount of NOx to greatest extent, is a kind of miniature gas turbine combustion chamber device of 100kW level low NOx drainage.
For achieving the above object, technical scheme of the present invention is achieved in that
A kind of double premixed channel miniature gas turbine combustion chamber of natural gas fuel is provided, and the 100kW level miniature gas turbine combustion chamber for single jar structure comprises head of combustion chamber, three parts of burner inner liner and heat shield; Wherein, head of combustion chamber is the multi-layer thin shell structure of coaxial arrangement, each layer by screw with separate briquetting and be linked to be an integral body; Head of combustion chamber is by the combustion chamber head-shield of a upstream radial wall face closure, the burner inner liner head, the eddy flow cup, axial eddy device and gas collection cup are formed, chamber head covers on center position and axially inwardly forms a coaxial bore hole, and ignition electric nozzle is installed in the bore hole, and the gas collection cup is welded in the enlarging of combustion chamber head-shield and bore hole lower exit and forms collection chamber, gas collection cup and eddy flow cup constitute torch fuel-air duct on duty, and eddy flow cup and burner inner liner head constitute main fuel-air duct; It has two fuel channels, is respectively double torch fuel channel on duty of igniting and main combustion zone fuel channel; Fuel in the torch passage on duty as igniter fuel, provides fuel for torch on duty when normal operation when starting ignition; Three groups of swirlers have been arranged in the head of combustion chamber, be respectively: the radially main swirler that burner inner liner head upstream end face forms with the eddy flow cup, the radially secondary wind swirler of axial eddy device in torch fuel-air duct on duty and burner inner liner head downstream position, wherein, the air-flow direction of rotation of secondary wind radial whirl device is opposite with the direction of rotation of radially main swirler and axial eddy device; The gas-turbine combustion chamber combustion air all from downstream, combustion chamber adverse current to the head supply, fuel is then in two bursts of supplies of chamber head part, enters the combustion chamber by main fuel supply pipe and igniting and torch supply pipe on duty respectively; Igniting and torch on duty directly spray in the collection chamber with fuel; Be provided with built-in main fuel manifold in the head-shield of combustion chamber, the main fuel pipe sprays into fuel in the fuel manifold, many fuel that connected by the downstream are in charge of and are injected to radially main swirler central authorities, evenly mix the back with wind and enter the combustion chamber by main fuel-air duct and participate in burning.
Described miniature gas turbine combustion chamber has been arranged two groups of fuel nozzle ports on its described gas collection cup, is arranged in the upstream and downstream of axial eddy device; The fuel shunting of upstream fuel nozzle ports makes the fuel concentration in torch fuel-air duct on duty be not more than 5%, the position of downstream fuel nozzle ports should guarantee that fuel-air mixture has enough blending spaces in runner, guarantees fuel-air mixture in igniting and the torch passage on duty abundant premix before fire burns as far as possible; The nozzle hole number of two groups of spouts is 3～12, and spray orifice is in the alternate layout of circumferential direction; According to the thickness of gas collection wall of cup face, spray orifice is arranged to become with radial direction the hole of cutting sth. askew of 0 °～30 ° of angles respectively in same axial plane, and the direction in the hole of cutting sth. askew is consistent with axial eddy device air-flow direction of rotation.
A kind of method that reduces the gas-turbine combustion chamber nitrogen oxides emission that described miniature gas turbine combustion chamber provided, it is the fuel shunting in torch on duty district, a part of fuel is sprayed in the air in swirler the place ahead; Poor fuel premixed combustion technology is not only adopted in this combustion chamber in the main fuel district like this, and also adopts the premixed combustion mode in torch on duty district, is a kind of combustion chamber of double premixed channel low nox emission.
Described method, the fuel quantity of its described swirler upstream fuel nozzle ports shunting makes that the fuel concentration in torch fuel-air duct on duty is not more than 5%.
Described miniature gas turbine combustion chamber, the runner of the radially main swirler of its described burner inner liner head upstream end face, it is one group of groove of cutting sth. askew that has angle with radial direction, this angle is 36 °～42 °, the quantity of groove is 16～24, the cross section of groove of cutting sth. askew is a rectangle, and the area of rectangle is determined according to assignment of traffic.
Described miniature gas turbine combustion chamber, one group of the downstream of its described burner inner liner head runner of secondary wind swirler radially, be one group with the hole of cutting sth. askew that radially forms an angle, the diameter in hole of cutting sth. askew is determined according to the air distribution scheme, the cut sth. askew angle in hole is 25 °～40 °, and quantity is 16～24.
Described miniature gas turbine combustion chamber, the runner of the axial eddy device in its described igniting and the torch gas channel on duty, be one group around equally distributed another of the axial direction hole of cutting sth. askew, its inclination angle is 30 °～50 °, the diameter in another hole of cutting sth. askew determines that according to the air distribution scheme quantity is 12～24.
Described miniature gas turbine combustion chamber, its described ignition electric nozzle is installed in the central bore hole, and the bore hole downstream has radially outer enlarging, and the subtended angle of enlarging is 30 °～45 °; After lighting a fire successfully, the ignition electric nozzle segment distance of in bore hole, can dropping back, thus protection sparking plug head needn't design the head that the cooling air cools off sparking plug in addition.
Described miniature gas turbine combustion chamber, the downstream end of the downstream end of its eddy flow cup and gas collection cup is not in same axial plane.In gas collection cup downstream end position, the axial downstream of the downstream end of eddy flow cup has been extended a segment distance.Like this, seed region and torch on duty district have formed a relatively independent space, help improving the firing characteristic of combustion chamber, and when burning, torch on duty is subjected to the influence of primary air less, reaches the purpose of stablizing poor fuel premixed combustion flame simultaneously.
Described miniature gas turbine combustion chamber, its combustion chamber import and export air-flow temperature rise is little, is generally 250 ℃～350 ℃; Adopt residual enthalpy to utilize technology, air-flow drives in the wrong direction from the downstream, combustion chamber and enters head of combustion chamber, by with the heat exchange of burner inner liner wall, improve the entry of combustion chamber air themperature; The burner inner liner wall adopts many group fins to strengthen the heat exchange of air and wall along burner inner liner outer wall circumferential arrangement, reaches cooling burner inner liner wall, reduces the purpose of carbon monoxide emission simultaneously.
The present invention not only adopts the premixed combustion mode of poor fuel in the main fuel district, and also adopts the premixed combustion technology in torch on duty district, thereby reduces the growing amount of NOx to greatest extent, is a kind of combustion chamber of low NOx drainage of double premixed channel.
Description of drawings
Fig. 1 a is the head schematic top plan view of combustion chamber of the present invention;
Fig. 1 b is along the A-A profile among Fig. 1 a;
Fig. 1 c is along the B-B profile among Fig. 1 a;
Fig. 2 a is a burner inner liner head construction schematic diagram of the present invention;
Fig. 2 b is that A among Fig. 2 a is to view with along the B-B profile;
Fig. 3 is eddy flow cup of the present invention and disjoining pressure block structure schematic diagram;
Fig. 4 is a gas collection cup structure schematic diagram of the present invention;
Fig. 5 is an axial eddy device structural representation of the present invention;
Fig. 6 is a structure chart of the present invention.
The specific embodiment
The present invention is a kind of double premixed channel miniature gas turbine combustion chamber of 100kW level natural gas fuel, and this combustion chamber is single jar structure, is made up of head of combustion chamber, burner inner liner and heat shield.The fuel that enters the combustion chamber is divided into two strands, and one is igniting and torch on duty fuel, and another thigh is a main fuel, is provided with two spouts at the outer surface of combustion chamber head-shield, will light a fire respectively and spray into the appointed area of combustion chamber with torch on duty with fuel and main fuel.Burner inner liner and heat shield are the Circular Cylindrical Thin Shells body of coaxial arrangement, and the gap between the two is an air duct, and this combustion chamber adopts residual enthalpy to utilize technology, and air is flowed to head of combustion chamber by the downstream adverse current of combustion chamber in air duct.Because the temperature rise of miniature gas turbine combustion chamber import and export air-flow is less, be generally 250 ℃～350 ℃, therefore, on the burner inner liner wall, there is not the air film Cooling Design, but adopt hydraulically rough surface or fin to improve air and the heat exchange between the burner inner liner outer wall in the air duct, reach the purpose of cooling off the burner inner liner wall.Do like this, can improve the air themperature of entry of combustion chamber on the one hand, reduce CO emission simultaneously.Burner inner liner is provided with blending hole at downstream position, is used for burning fully of burner inner liner fuel, reduces incomplete combustion loss, and coolant outlet combustion gas simultaneously makes it to reach the delivery temperature of design.The heat shield wall has the air-flow entrance hole, and whole air that the combustion chamber needs enter combustion chamber participation burning from the annular gap and the air intake on the heat shield wall of heat shield and burner inner liner end through air duct and blending hole.
Head of combustion chamber of the present invention is a hierarchy, each layer by screw with separate briquetting and be linked to be an integral body.Head of combustion chamber comprises the combustion chamber head-shield, ignition electric nozzle, gas collection cup, eddy flow cup and burner inner liner head.It between each parts coaxial arrangement.The combustion chamber head-shield is a hat-shaped structure, and shade links to each other with the heat shield upstream face.By screw head of combustion chamber and burner inner liner head are held together.An advantage of Lian Jieing is an easy accessibility like this, and is easy to maintenance.The combustion chamber is fixed on the pressurizer tank by screw in the gas turbine unit.
Chamber head covers on center position, and axially inwardly formation one is cylindrical, and the center of this cylinder is that a bore hole constitutes cylindrical shell, and ignition electric nozzle is installed in this bore hole.The present invention is provided with a horn-like enlarging of expansion radially outward at the end of the bore hole of mounting points firearm, the angle of horn-like enlarging is 30 °～45 °, this structure makes and forms a diffusion district at ignition electric nozzle head place, is convenient to the igniting and the burning of fuel-air mixture.Simultaneously, among the present invention, ignition electric nozzle can move in central bore backward, and the sparking plug head is burnt out when avoiding burning.She Ji benefit is to draw the head that one air-flow cools off sparking plug separately like this.
The eddy flow cup is positioned between combustion chamber head-shield and the burner inner liner head by separating briquetting and screw axial.Eddy flow cup inwall and collection chamber outer wall constitute igniting and torch air duct on duty.The axial eddy device realization of the radial location of eddy flow cup by being provided with in air duct at igniting and torch on duty.This axial eddy device is coaxial with the combustion chamber head-shield, is installed in the air duct of igniting and torch on duty.The runner of the axial eddy device of the present invention design be one group around the equally distributed hole of cutting sth. askew of axial direction, its inclination angle is 30 °～50 °, this swirler is used to air generation eddy flow that igniting and torch on duty are used, thereby reaches the purpose of the retention flame.The cut sth. askew aperture in hole determines that according to assignment of traffic the quantity in hole is 12～24.
Eddy flow cup outer wall and burner inner liner head inwall form main fuel passage.Among the present invention, burner inner liner head upstream end face has evenly been arranged one group of radially main swirler of groove formation of cutting sth. askew that becomes a certain angle with radial direction in the sagittal plane, and this angle is 36 °～42 °, and the quantity of groove is 16～24.The cross section of groove of cutting sth. askew is a rectangle, and the area of rectangle is determined according to assignment of traffic.
The gas collection cup is the cylindrical housings of an end band enamel shape shade, enamel shape shade links to each other with head-shield top, combustion chamber, the other end of gas collection cup links to each other with the end of central bore flare, like this, gas collection cup inwall, bore hole outer wall and combustion chamber head-shield inwall form an enclosed areas, and this zone is called igniting and torch fuel plenum on duty.Igniting and torch on duty import this collection chamber with fuel by the spout on the head-shield of combustion chamber.Among the present invention, be provided with two groups of igniting and torch fuel nozzle ports on duty on the gas collection wall of cup face, be arranged in the upstream and downstream position of axial eddy device respectively along the wall circumferential arrangement.There is requirement in the aperture of two groups of spouts; the fuel quantity that requirement is arranged in the fuel nozzle ports shunting of axial eddy device upstream make igniting and torch on duty with the volume of fuel concentration in the air duct less than 5%; She Ji purpose is to reduce the fuel concentration fluctuation like this; make igniting and torch on duty even with fuel mix in the air duct; help protecting the axial eddy device, unlikelyly burn out because of fuel concentration reduces tempering.The layout palpus handled of the downstream nozzle exit area of axial eddy device, should enough blending spaces be arranged with fuel-air mixture in the eddy flow cup is design considerations, can guarantee like this to light a fire and torch passage on duty in fuel-air mixture abundant premix before fire burns, thereby reduce the NOx discharging to greatest extent, this also is the key that the present invention can reduce the NOx discharging to greatest extent.The quantity of spray orifice is 3～12, many spray orifices layout, and it is even to help fuel-Air mixing.And two groups of spray orifices are in the alternate layout of circumferential direction.According to the thickness of gas collection wall of cup face, spray orifice is arranged to become with radial direction the hole of cutting sth. askew of 0 °～30 ° of angles respectively in same axial plane.The direction in hole of cutting sth. askew is consistent with axial eddy device air-flow direction of rotation.
Among the present invention, the downstream end of eddy flow cup and gas collection cup end be not in a plane.Help improving the firing characteristic of combustion chamber like this, when burning, torch on duty is subjected to the influence of primary air less, reaches the purpose of stablizing poor fuel premixed combustion flame simultaneously.
Among the present invention, be provided with built-in fuel manifold in the head-shield of combustion chamber, main fuel sprays into to this fuel manifold by the main fuel spray orifice on the head-shield of combustion chamber, this fuel manifold is in charge of with 3～16 fuel and is linked to each other, the main fuel that the combustion chamber is used is in charge of by this fuel and is sprayed into to the cut sth. askew central authorities of groove of the gas channel of main swirler radially, fully enters burner inner liner behind the premix with fuel through the air-flow of main swirler in main fuel passage.The purpose that adopts a plurality of fuel nozzles is to make fuel even premix in the air-flow of main combustion zone.
The present invention is in the downstream of burner inner liner head, and place, the exit position of main fuel passage is provided with one group of radial whirl device and enters the mouth as secondary wind.This swirler be one group with the hole of cutting sth. askew that radially forms an angle, the diameter in hole determines that according to the air distribution scheme angle in the hole of cutting sth. askew is 25 °～40 °, the quantity in hole is 16～24.The direction of rotation of this strand air-flow is opposite with the air-flow direction of rotation that axial eddy device and radially main swirler come out; to weaken the air-flow spin intensity; be unlikely to cause air-flow adherent from the main fuel passage back of coming out because of rotation and sudden expansion because of air-flow; thereby the protection combustion chamber wall surface makes the main fuel air-flow concentrate on the burning of burner inner liner central position.
Accompanying drawing is specific embodiments of the invention.
Shown in accompanying drawing 1b, the 100kW level miniature gas turbine combustion chamber of single jar structure is by head of combustion chamber 5, and burner inner liner 20 and heat shield 30 are formed.Whole combustion chamber is fixed on the pressurizer tank 40 by screw 50.The high temperature air that comes out from regenerator enters the combustion chamber by two groups of perforates 301 on annular gap between heat shield and the burner inner liner 100 and the heat shield.The air that enters the combustion chamber is divided into two strands, and one blending hole 201 that is provided with by the burner inner liner downstream enters burner inner liner and participates in burning, plays the purpose of afterburning and cooling combustion chamber outlet high-temperature flue gas.Another strand by the air duct 202 formed by heat shield inwall and burner inner liner outer wall to head of combustion chamber 5 motions, for whole combustion chamber provides the air of lighting a fire, wind and secondary wind.This arrangement of air-flow is good for improving efficiency of energy utilization.Air in the air duct 202 is in head of combustion chamber 5 motions, carry out heat exchange with the outer wall of burner inner liner 20, playing the effect of cooling burner inner liner 20 wall surface temperatures on the one hand, improved the temperature of entry of combustion chamber air on the other hand, is the mode that a kind of residual enthalpy utilizes.Reduced the temperature difference of combustion chamber inlet and outlet simultaneously,, in this case, do not needed to be provided with film cooling holes fully, thereby can reduce CO emission, reduced incomplete combustion loss because the combustion chamber import and export temperature difference is generally 250 ℃～350 ℃.Be the heat exchange efficiency of air and burner inner liner outer wall wall in the further raising passage 202, prolong the service life of burner inner liner, present embodiment has adopted rib structure 21 to strengthen the disturbance between air-flow and wall.
Shown in accompanying drawing 1b, head of combustion chamber 5 is the multi-layer thin shell structure of coaxial arrangement, and each layer is linked to be an integral body by screw 52.A benefit with screw connection rather than welding is to be convenient to dismounting and maintenance.Head of combustion chamber comprises combustion chamber head-shield 10, burner inner liner head 22, eddy flow cup 90, axial eddy device 94 and gas collection cup 96.Combustion chamber head-shield 10 axially inwardly forms a cylindrical structural at center position, and the center of this cylinder is a bore hole 12, and ignition electric nozzle 80 is installed in this bore hole 12.The wall of bore hole 12 is provided with a horn-like enlarging of expansion radially outward endways, and the angle of horn-like enlarging is 30 °～45 °, makes to form a diffusion district at ignition electric nozzle head place, is convenient to the igniting and the burning of fuel-air mixture.Simultaneously, among the present invention, ignition electric nozzle 80 can move in central bore 12 backward, and the sparking plug head is burnt out when avoiding burning, and does not need to draw separately the head that one air-flow cools off sparking plug like this.
Shown in accompanying drawing 2a and accompanying drawing 2b, burner inner liner head 22 is that a upstream extremity is worn radial whirl device 23, the thin walled shell of downstream band radial whirl device 25.The radial whirl device 23 of this upper surface is one group of groove 24 of cutting sth. askew that becomes a certain angle with radial direction, and a wind of combustion chamber from then on swirler enters the combustion chamber.This swirler is called radially main swirler 23, and its angle is 36 °～42 °, and the quantity of groove is 16～24.The cross section of groove of cutting sth. askew is a rectangle, and the area of rectangle is determined according to assignment of traffic.One group of radial whirl device 25 in burner inner liner head 22 downstreams be one group with the hole 26 of cutting sth. askew that radially forms an angle, the diameter in hole determines that according to the air distribution scheme angle in the hole of cutting sth. askew is 25 °～40 °, the quantity in hole is 16～24.The secondary wind of combustion chamber enters the combustion chamber by this radial whirl device 25.The air-flow direction of rotation of radial whirl device 25 is opposite with the air-flow direction of rotation of radially main swirler 23; purpose is in order to weaken the air-flow spin intensity; be unlikely to cause air-flow adherent from the main fuel passage back of coming out because of rotation and sudden expansion because of air-flow; the protection combustion chamber wall surface; make not overtemperature of wall, make the main fuel air-flow concentrate on the burning of burner inner liner central position simultaneously.
Shown in accompanying drawing 3 and accompanying drawing 1b, eddy flow cup 90 is worn the cylindrical housings of enamel shape shade for the upper end, be provided with between eddy flow cup 90 and the combustion chamber head-shield 10 and separate briquetting 93, between burner inner liner head 22 and combustion chamber head-shield 10, the inwall of the outer wall of eddy flow cup 90 and burner inner liner head 22 constitutes wind and main fuel passage together by screw 52 and hole 91 axial location.Swirler 25 is positioned at the terminal position place of main fuel passage.
Shown in accompanying drawing 4, the upstream face of gas collection cup 96 is welded on the inwall of combustion chamber head-shield 10, the downstream end of gas collection cup 96 welds mutually with the end of the flare of central bore housing 12, like this, the inwall three of the outer wall of the inwall of gas collection cup 96, bore hole housing 12 and combustion chamber head-shield 10 forms the igniting and the torch fuel plenum on duty of sealing jointly.
Shown in accompanying drawing 1b and accompanying drawing 5, the outer wall of the inwall of eddy flow cup 90 and gas collection cup 96 constitutes igniting and torch air duct on duty.Be provided with an axial eddy device 94 in this passage, the runner 95 of swirler is one group and centers on the equally distributed hole of cutting sth. askew of axial direction that its inclination angle is 30 °～50 °.Be used to make the air of igniting and torch on duty to produce eddy flow, thereby reach the purpose of the retention flame.In the design, the aperture in the hole of cutting sth. askew determines that according to assignment of traffic the quantity in hole is 12～24.The radial location of eddy flow cup realizes by axial eddy device 94.
Shown in accompanying drawing 1a, accompanying drawing 1b and accompanying drawing 1c, the fuel of combustion chamber is divided into two strands: one is a main fuel, is injected to the built-in fuel manifold 61 that is provided with in the gas-turbine combustion chamber head-shield 10 by spout 60.Another strand is injected in the collection chamber by spout 70 for igniting and torch on duty fuel.Fuel manifold 61 is in charge of 62 with 3～16 fuel and is linked to each other, the main fuel that the combustion chamber is used is in charge of 62 by this fuel and is sprayed into to the cut sth. askew central authorities of groove 24 of the gas channel of radially main swirler 23, fully enters burner inner liner behind the premix with fuel through the air-flow of main swirler 23 in main fuel passage.Adopt a plurality of minutes fuel nozzles, make fuel-air even premix in main fuel passage.
Be provided with two groups of fuel nozzle ports 97 and 98 on gas collection cup 96 walls, by these two groups of spouts, the fuel in the collection chamber is injected to igniting and torch on duty is used in the air duct, uses with conduct igniting and torch on duty after the air pre-mixing.Two groups of fuel nozzle ports on the gas collection cup 96 are arranged in the upstream and downstream position of axial eddy device 94 respectively.Volume of fuel concentration in the feasible igniting of fuel quantity of upstream spout 97 shuntings of swirler 94 and the torch on duty usefulness air duct is less than 5%; by fuel shunting and premix; help reducing the fuel concentration fluctuation; make igniting and torch on duty with the abundant premix before catching fire of fuel in the air duct; fuel shunting simultaneously also helps protection axial eddy device, is unlikely to burn out because of fuel concentration reduces tempering.The position of the downstream spout group 98 of axial eddy device 94 must carefully be arranged, should enough blending spaces be arranged with fuel-air mixture in runner is design considerations, the purpose of doing like this be guarantee as far as possible to light a fire and torch passage on duty in fuel-air mixture abundant premix before fire burns, discharge thereby reduce NOx to greatest extent.Two groups of spouts 97 and 98 spout quantity are respectively 3～12, and two groups of spray orifices are arranged between the circumferential direction homogeneous phase.These two groups of spouts can be arranged to become with radial direction the hole of cutting sth. askew of 0 °～30 ° of angles according to the thickness of gas collection cup 96 walls in same axial plane, the direction in the hole of cutting sth. askew is consistent with axial eddy device air-flow direction of rotation.
In the present invention, the downstream end face of gas collection cup 96 and eddy flow cup 90 is coplane not, help reducing the main fuel air-flow like this to the dilution of torch on duty district fuel with to the interference of burning, be convenient to torch on duty under the extreme poverty fuel combustion mode, the flame stabilization of combustion chamber is played a role.
More than by the specific embodiment the present invention is described in detail, in conjunction with the accompanying drawing of being given, it will be apparent to those skilled in the art key problem in technology of the present invention, should be understood that simultaneously embodiment only is an exemplary forms.Can carry out suitable distortion and modification when the present invention is used according to actual state, this structure is done slightly to change and promptly be can be used as the oil inflame chamber simultaneously.These distortion and modification, and the specific embodiment that is applied to different fuel combustions all should drop within the scope that claim of the present invention protects.
Claims (10)
1, a kind of double premixed channel miniature gas turbine combustion chamber of natural gas fuel, the 100kW level miniature gas turbine combustion chamber for single jar structure comprises head of combustion chamber (5), (30) three parts of burner inner liner (20) and heat shield; Wherein, head of combustion chamber (5) is the multi-layer thin shell structure of coaxial arrangement, each layer by screw (52) with separate briquetting (93) and be linked to be an integral body; Head of combustion chamber (5) is by the combustion chamber head-shield (10) of a upstream radial wall face closure, burner inner liner head (22), eddy flow cup (90), axial eddy device (94) and gas collection cup (96) are formed, combustion chamber head-shield (10) axially inwardly forms a coaxial bore hole (12) at center position, ignition electric nozzle (80) is installed in the bore hole (12), gas collection cup (96) is welded in the enlarging of combustion chamber head-shield (10) and bore hole (12) lower exit and forms collection chamber, gas collection cup (96) constitutes torch fuel-air duct on duty with eddy flow cup (90), and eddy flow cup (90) constitutes main fuel-air duct with burner inner liner head (22); It is characterized in that having two fuel channels, be respectively double torch fuel channel on duty of igniting and main combustion zone fuel channel; Fuel in the torch passage on duty as igniter fuel, provides fuel for torch on duty when normal operation when starting ignition; Three groups of swirlers have been arranged in the head of combustion chamber (5), be respectively: the radially main swirler (23) that burner inner liner head (22) upstream face forms with eddy flow cup (90), the axial eddy device (94) in torch fuel-air duct on duty and the radially secondary wind swirler (25) of burner inner liner head downstream position, wherein, the air-flow direction of rotation of secondary wind radial whirl device (25) is opposite with the direction of rotation of radially main swirler (23) and axial eddy device (94); The gas-turbine combustion chamber combustion air all from downstream, combustion chamber adverse current to the head supply, fuel is then in two bursts of supplies of chamber head part, enters the combustion chamber by main fuel supply pipe (60) and igniting and torch supply pipe on duty (70) respectively; Igniting and torch on duty directly spray in the collection chamber with fuel; Be provided with built-in main fuel manifold (61) in the combustion chamber head-shield (10), main fuel pipe (60) sprays into fuel in the fuel manifold (61), many fuel that connected by the downstream are in charge of (62) and are injected to radially main swirler central authorities, evenly mix the back with wind and enter the combustion chamber by main fuel-air duct and participate in burning.
2, miniature gas turbine combustion chamber according to claim 1 is characterized in that, has arranged two groups of fuel nozzle ports on the described gas collection cup (96), is arranged in the upstream and downstream of axial eddy device (94); The fuel shunting of upstream fuel nozzle ports (97) makes the fuel concentration in torch fuel-air duct on duty be not more than 5%, the position of downstream fuel nozzle ports (98) should guarantee that fuel-air mixture has enough blending spaces in runner, guarantees fuel-air mixture in igniting and the torch passage on duty abundant premix before fire burns as far as possible; Two groups of spouts 97) and the nozzle hole number of (98) be 3～12, and spray orifice is in the alternate layout of circumferential direction; According to the thickness of gas collection cup (96) wall, spray orifice is arranged to become with radial direction the hole of cutting sth. askew of 0 °～30 ° of angles respectively in same axial plane, and the direction in the hole of cutting sth. askew is consistent with axial eddy device air-flow direction of rotation.
3, a kind of method that reduces the gas-turbine combustion chamber nitrogen oxides emission that miniature gas turbine combustion chamber according to claim 1 and 2 provided, it is characterized in that, the fuel shunting sprays into a part of fuel in the air in swirler the place ahead in torch on duty district; Poor fuel premixed combustion technology is not only adopted in this combustion chamber in the main fuel district like this, and also adopts the premixed combustion mode in torch on duty district, is a kind of combustion chamber of double premixed channel low nox emission.
4, method according to claim 3 is characterized in that, the fuel quantity of described swirler upstream fuel nozzle ports shunting makes that the fuel concentration in torch fuel-air duct on duty is not more than 5%.
5, miniature gas turbine combustion chamber according to claim 1, it is characterized in that, the runner of the radially main swirler (23) of described burner inner liner head (22) upstream face, it is one group of groove of cutting sth. askew (24) that has angle with radial direction, this angle is 36 °～42 °, the quantity of groove is 16～24, and the cross section of the groove of cutting sth. askew (24) is a rectangle, and the area of rectangle is determined according to assignment of traffic.
6, miniature gas turbine combustion chamber according to claim 1, it is characterized in that, one group of the downstream of described burner inner liner head (22) runner of secondary wind swirler (25) radially, be one group with the hole of cutting sth. askew (26) that radially forms an angle, the diameter in hole (26) of cutting sth. askew is determined according to the air distribution scheme, the cut sth. askew angle of hole (26) is 25 °～40 °, and quantity is 16～24.
7, miniature gas turbine combustion chamber according to claim 1, it is characterized in that, the runner of the axial eddy device (94) in described igniting and the torch gas channel on duty, be one group and center on the equally distributed hole of cutting sth. askew of axial direction (95), its inclination angle is 30 °～50 °, the diameter in hole (95) of cutting sth. askew determines that according to the air distribution scheme quantity is 12～24.
8, miniature gas turbine combustion chamber according to claim 1 is characterized in that, described ignition electric nozzle (80) is installed in the central bore hole (12), and bore hole (12) downstream has radially outer enlarging, and the subtended angle of enlarging is 30 °～45 °; After lighting a fire successfully, ignition electric nozzle (80) segment distance of in bore hole (12), can dropping back, thus protection sparking plug head needn't design the head that the cooling air cools off sparking plug in addition.
9, miniature gas turbine combustion chamber according to claim 1 is characterized in that, the downstream end of the downstream end of eddy flow cup (90) and gas collection cup (96) is not in same axial plane; In gas collection cup (96) downstream end position, the axial downstream of downstream end of eddy flow cup (90) has been extended a segment distance, like this, seed region and torch on duty district have formed a relatively independent space, help improving the firing characteristic of combustion chamber, when burning, torch on duty is subjected to the influence of primary air less, reaches the purpose of stablizing poor fuel premixed combustion flame simultaneously.
10, miniature gas turbine combustion chamber according to claim 1 is characterized in that, combustion chamber import and export air-flow temperature rise is little, is generally 250 ℃～350 ℃; Adopt residual enthalpy to utilize technology, air-flow drives in the wrong direction from the downstream, combustion chamber and enters head of combustion chamber, by with burner inner liner (20) wall heat exchange, improved the entry of combustion chamber air themperature; Burner inner liner (20) wall adopts many group fins (21) to strengthen the heat exchange of air and wall along burner inner liner (20) outer wall circumferential arrangement, reaches cooling burner inner liner (20) wall, reduces the purpose of carbon monoxide emission simultaneously.
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| CNB2006100007576A CN100483029C (en) | 2006-01-12 | 2006-01-12 | Combustion chamber of miniature gas turbine with double premixed channel using natural gas |
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| CNB2006100007576A CN100483029C (en) | 2006-01-12 | 2006-01-12 | Combustion chamber of miniature gas turbine with double premixed channel using natural gas |
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| CNB2006100007576A Expired - Fee Related CN100483029C (en) | 2006-01-12 | 2006-01-12 | Combustion chamber of miniature gas turbine with double premixed channel using natural gas |
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