CN101294715A - Combustion equipment and burner combustion method - Google Patents
Combustion equipment and burner combustion method Download PDFInfo
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- CN101294715A CN101294715A CNA200810092375XA CN200810092375A CN101294715A CN 101294715 A CN101294715 A CN 101294715A CN A200810092375X A CNA200810092375X A CN A200810092375XA CN 200810092375 A CN200810092375 A CN 200810092375A CN 101294715 A CN101294715 A CN 101294715A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 53
- 238000009841 combustion method Methods 0.000 title claims description 5
- 239000000446 fuel Substances 0.000 claims abstract description 121
- 239000000463 material Substances 0.000 claims description 12
- 230000001535 kindling effect Effects 0.000 claims description 11
- 230000001154 acute effect Effects 0.000 claims description 8
- 230000015572 biosynthetic process Effects 0.000 claims description 4
- 238000000926 separation method Methods 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 3
- RKTYLMNFRDHKIL-UHFFFAOYSA-N copper;5,10,15,20-tetraphenylporphyrin-22,24-diide Chemical group [Cu+2].C1=CC(C(=C2C=CC([N-]2)=C(C=2C=CC=CC=2)C=2C=CC(N=2)=C(C=2C=CC=CC=2)C2=CC=C3[N-]2)C=2C=CC=CC=2)=NC1=C3C1=CC=CC=C1 RKTYLMNFRDHKIL-UHFFFAOYSA-N 0.000 claims description 2
- 239000003570 air Substances 0.000 description 49
- 239000007789 gas Substances 0.000 description 46
- 230000002093 peripheral effect Effects 0.000 description 17
- 238000011144 upstream manufacturing Methods 0.000 description 15
- 238000002156 mixing Methods 0.000 description 9
- 238000010586 diagram Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 8
- 230000003321 amplification Effects 0.000 description 6
- 238000003199 nucleic acid amplification method Methods 0.000 description 6
- 230000000052 comparative effect Effects 0.000 description 5
- 230000004888 barrier function Effects 0.000 description 4
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- 230000008676 import Effects 0.000 description 3
- 230000014759 maintenance of location Effects 0.000 description 3
- 238000002844 melting Methods 0.000 description 3
- 230000008018 melting Effects 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000000116 mitigating effect Effects 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 239000012080 ambient air Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000002407 reforming Methods 0.000 description 1
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Abstract
Combustion equipment of a coaxial jet combustion scheme is provided that includes: a burner plate in which fuel and air are mixed with each other while the fuel and air pass through an air hole; a burner plate extension which is a portion of the burner plate and extends toward a combustion chamber side spaced apart from the air hole; and a protrusion disposed on the combustion chamber side of the burner plate extension so as to protrude in a direction where flow of the fuel moves. In the combustion equipment, a gap between opposite portions of the protrusion is greater than a diameter of the air hole and a flame source forming area is defined between the burner plate, the burner plate extension and the protrusion. The combustion equipment of a coaxial jet combustion scheme can achieve a further reduction in NOx emissions.
Description
Technical field
The present invention relates to the combustion method of burner and burner.
Background technology
In recent years, more and more stricter about the restriction of the discharge of atmosphere pollution material.For example, in gas turbine burner, be included in the nitrogen oxide (NO that discharges in the gas in order to reduce
X) discharge rate, studied combustion system miscellaneous.
As a kind of combustion system, have with fuel nozzle and airport be configured in coaxial on, and in the combustion chamber, supply with the coaxial jet flow of fuel and air and make the coaxial jet flow combustion system of its burning.This coaxial jet flow combustion system and existing premixed combustion mode compare, and can promote fuel and Air mixing in very short distance, and can reduce NO
XDischarge rate.
Patent documentation 1: TOHKEMY 2003-148734 communique.
Because the burner of coaxial jet flow combustion system can rapid mixing fuel and air, therefore can reduce NO
XDischarge rate.From now on, will require further to reduce NO
XDischarge rate.
NO
XThe rising that growing amount is accompanied by burning gas temperature is the exponential function increase.Therefore, in order further to reduce NO
XDischarge rate, effective method are when improving fuel and Air mixing degree, further increase the flow with respect to the air of fuel, and reduce the temperature of the burning gases in the combustion chamber.
But, if improve ratio, under the thin condition of fuel, turn round with respect to the air mass flow of fuel flow rate, then the state of flame becomes unstable.Therefore, at NO
XBe limited in the minimizing.
Summary of the invention
The objective of the invention is in the burner of coaxial jet flow combustion system, realize lower NO
X
Of the present invention being characterized as has: the burner plate that above-mentioned fuel and above-mentioned air is mixed during together by airport at fuel and air; Part as this burner plate extends to from the burner plate extension of combustion chamber one side of above-mentioned airport separation; And, the jut that direction is given prominence to that passes through at the above-mentioned fuel stream of the combustion chamber of this burner plate extension one side direction, and the gap of relative above-mentioned jut is also bigger than the diameter of above-mentioned airport, and the formation kindling material forms the zone between above-mentioned burner plate, above-mentioned burner plate extension and above-mentioned jut.
The present invention has following effect.
According to the present invention, in the burner of coaxial jet flow combustion system, can realize lower NO
X
Description of drawings
Fig. 1 is the figure that has amplified the peripheral position of fuel nozzle and airport in embodiment 1.
Fig. 2 is the figure that has amplified the peripheral position of fuel nozzle and airport in embodiment 2.
Fig. 3 is the figure that has amplified the peripheral position of fuel nozzle and airport in embodiment 3.
Fig. 4 is the figure that has amplified the peripheral position of fuel nozzle and airport in embodiment 4.
Fig. 5 is the figure that has amplified the peripheral position of fuel nozzle and airport in embodiment 5.
Fig. 6 is the figure that has amplified the peripheral position of fuel nozzle and airport in embodiment 6.
Fig. 7 has represented that near the fuel of jut flows and the figure of the flow regime of air stream.
Fig. 8 is the figure (variation) that has amplified the peripheral position of fuel nozzle and airport in embodiment 1.
Fig. 9 is the figure (variation) that has amplified the peripheral position of fuel nozzle and airport in embodiment 1.
Figure 10 is the figure (variation) that has amplified the peripheral position of fuel nozzle and airport in embodiment 5.
Figure 11 is the schematic diagram of gas turbine structure.
Figure 12 is the structural map of the airport among the embodiment 3.
Figure 13 is that flame propagation is to the figure of the occasion of the upstream side of jut in the burner plate of embodiment 1.
Figure 14 has represented in the burner plate of embodiment 1, flows into the figure of the situation in the combustion chamber from the fuel stream of fuel nozzle ejection.
Among the figure:
1～7-jut, 10-fuel nozzle, 11-burner plate, 12-airport, 21-air stream, 22-fuel stream, 30-pre-mixed gas, 31-burnt gas, 32-circular flow, 40-flame, 51,52-heat energy, 110-air compressor, 120-pressure-air, 180-combustion chamber.
The specific embodiment
Figure 11 is the figure that has used coaxial jet flow combustion system on the gas turbine burner as a kind of burner, is the whole skeleton diagram of gas turbine.
Gas turbine has air compressor 110, burner 302 and turbine 190.
Air compressor 110 compresses air outside and generates pressure-air 120, and imports in the unit rooms 140 from diffuser 130.Then, pressure-air 120 flows through lining 160 and is configured in gap between the urceolus 250 on the concentric circles of lining periphery after the tail pipe that has flow through tail pipe 150 and be arranged on its periphery flows gap between the sleeve 151.Tail pipe 150 is connected respectively with urceolus 250 with lining 160, the mobile sleeve 151 of tail pipe.Pressure-air 120 is reverse flow after having flow through above-mentioned gap, imports in the combustion chamber 180 from the airport 12 that is arranged on the burner plate 11.
On the other hand, in fuel system 170, fuel is boosted by petrolift 171 and utilizes flow control valve 172 to regulate flow.Then, fuel is from the inlet portion ejection of fuel nozzle 10 to airport 12.At this moment, fuel nozzle 10 and airport 12 dispose coaxially.So-called " arranged coaxial " is meant, the burner plate 11 that has airport 12 in the configuration of the downstream of fuel nozzle 10, and from fuel nozzle 10 roughly to the center of airport inlet face ejection fuel, thereby form the mode that air flows with inside at the outer circumferential side of fuel stream, disposed the structure of fuel nozzle 10 and burner plate 11 at airport 12.And " coaxial jet flow " is meant, in the inside of airport 12, formed the jet flow of circular air stream at the outer circumferential side of fuel stream.
Supply in the combustion chamber 180 of lining 160 inside from the fuel stream and the air stream of airport 12 ejections, and burn and formation flame, thus the burning gases 181 of generation HTHP.The burning gases 181 that generate in burner 302 import in the turbine 190 from tail pipe 150.
In turbine 190, utilize the burning gases 181 revolving wormgear axles of HTHP.In addition, utilize the generator 200 that links with turbine wheel shaft to obtain power output from burning gases 181.Air compressor 110 and generator 200 link by an axle and turbine 190.But air compressor 110, turbine 190, generator 200 also can be the structures of two axles.
In addition, though fuel system 170 has been made a system in Figure 11, the multi-combustor structure that also exists fuel system to be divided into a plurality of systems and to supply with to a plurality of fuel header.For example, at widely used gas turbines such as heat power stations, with respect to the turbine rotating shaft with radial arrangement a plurality of burners.
In above-mentioned coaxial jet flow combustion system, can be with NO
XDischarge rate suppresses lowlyer., because NO
XIt is strict that the environmental limitations value of discharge rate becomes year by year, even if therefore coaxial jet flow combustion system also wishes further to reduce NO
XDischarge rate.
Here, NO
XThe rising that growing amount is accompanied by burning gas temperature is the exponential function increase.Therefore, in order further to reduce NO
XDischarge rate need increase the flow of air with respect to fuel, and reduce the temperature of the burning gases in the combustion chamber when improving fuel and Air mixing degree., if turn round under the thin condition of fuel, then the state of flame becomes unstable.Thereby, in coaxial jet flow combustion system in order to realize NO
XThe minimizing of discharge rate, needs improve the flame holding of burner.
[embodiment 1]
Fig. 1 (b) is 180 front views of having observed burner plate 11 from the combustion chamber.Fig. 1 (a) be in the whole skeleton diagram of the gas turbine of Figure 11 amplification the general profile chart at peripheral position of fuel nozzle 10 and airport 12, and be the A-A cutaway view of Fig. 1 (b).
The burner of present embodiment has: fuel nozzle 10; Burner plate 11 with airport 12; Be arranged on the jut 1 on the burner plate 11; And the lining 160 that forms combustion chamber 180.Between burner plate 11 and lining 160, be provided with spring sealed circle 161.
Airport 12 is formed on the burner plate 11.In addition, as Fig. 1 (b), airport 12 is configured to 3 row with concentric circles, and is provided with 6,12,18 airports 12 from interior all sides of burner.In addition, to be listed as from interior all sides be the first row airport 12-1, secondary series airport 12-2, the 3rd row airport 12-3 to each airport successively.Then, Fig. 1 (b) constitutes a burner plate.
In addition, shown in Fig. 1 (a), have stairstepping, form recess 200 in burner axle center one side by burner plate 11.On this recess 200, dispose the export department of 6 airport 12-1 (first row) of axle center one side that is arranged on burner.In addition, be provided with on the end difference 201 of stepped burner plate 11, disposing the export department of secondary series airport 12-2 and the 3rd row airport 12-3 with respect to recess 200.
And, on burner plate 11, be provided with side surface part 202 as the face that connects recess 200 and end difference 201.
Here, recess 200 is rounded with respect to burner axle center.In addition, side surface part 202 is made the shape of digging out cylinder from burner plate 11.Therefore, the stairstepping of burner plate 11 forms continuously along circumferencial direction.In addition, in the present embodiment, be provided with in the downstream of the side surface part 202 of burner plate 11 and pass through the outstanding jut 1 of direction at the combustion chamber of burner plate extension one side direction fuel stream and air stream, thereby utilize the stairstepping of burner plate 11, make from the fuel stream and the air stream of first row airport 12-1 ejection and collide on the end difference of burner plate 11.The gap of this jut 1 is also bigger than the diameter of airport.In addition, vertically cut off the occasion of burner plate at the face that forms with respect to the end difference 201 by burner plate 11, the front end of jut 1 becomes acute angle.And jut 1 also along the circumferential direction forms in the same manner continuously with the stairstepping of burner plate 11.
In addition, shown in Fig. 1 (b), the jut 1 that is arranged on the side surface part 202 of burner plate 11 is provided with to hinder from the mode of the part of the fuel stream of first row airport 12-1 ejection and air stream, and has the effect of upsetting the barrier that combustion flow and air flow.And, be formed with the circular flow of high temperature in the downstream of jut 1.This circular flow becomes kindling material, and by providing heat energy to unburned pre-mixed gas, unburned pre-mixed gas is lighted a fire.Therefore, improve the flame holding of burner integral body.Its result can turn round under the thinner condition of fuel, and can reduce NO
XDischarge rate.
Utilize Fig. 7 that the mechanical device that improves this flame holding is described.Fig. 7 is the figure that the heat energy among the expression jut 1 and the first row airport 12-1 reaches the state that flows.
Flow in the first row airport 12-1 from the fuel stream of fuel nozzle 10 ejections.Then, in the inside of airport 12-1, the coaxial jet flow that the outer circumferential side that flows at fuel has formed air stream flows to the downstream, and carries out premixed.From the air stream 21 of first row airport 12-1 ejection and the pre-mixed gas 30 of fuel stream 22, to the space ejection of surrounding by the recess 200 and the side surface part 202 of burner plate 11.Then, the pre-mixed gas 30 that sprays from above-mentioned space forms flame 40 in combustion chamber 180, become the burnt gas 31 of high temperature.Like this, the space that is surrounded by burner plate, burner plate extension, jut becomes the zone that forms kindling material.
Shown in Fig. 8 (a), jut 1 is not made acute angle-shaped triangle, and it is also passable to make tetragonal jut 5.Thus, simplified the making of jut 5, thereby can reduce cost of manufacture.
In addition, shown in Fig. 8 (b), jut 6 also can be the conical in shape that relaxes.The jut 6 of conical in shape is provided with the slope in the scope of whole side surface part 202.There is following possibility in occasion using jut (flameholder) retention flame: if produce turbulent flow (secondary flow) at the upstream side of jut, then flame arrives the upstream side of jut along the low flow velocity portion of turbulent flow.In this occasion, also there is the situation that burns out jut (flameholder)., by shown in Fig. 8 (b), making the conical in shape of mitigation, can suppress to be created in the turbulent flow of the upstream side of jut 6, thereby can prevent burning out of jut 6.
Figure 13 is the occasion of having represented at the burner plate that uses present embodiment, and flame 40 is transmitted to the figure of situation of the upstream side of jut 1.The wall that side surface part 202 contacts with flame 40 is heated by flame 40.Therefore, in the occasion of not cooling off jut 1, exist jut 1 by the possibility of melting loss.Thereby, flowing through the airport 12 of burner plate extension by making fuel stream 22 and air stream 21, air and fuel that temperature is lower especially than flame 40 cool off jut 1.In addition, in the occasion of the fluid of supplying with cooling jut 1 beyond airport, it is complicated that the structure of runner becomes.Thereby,, can prevent the melting loss of jut 1 with simple structure by fuel and air being flow through be arranged on the airport on the burner plate extension.
Secondly, for effect of the present invention and effect are described, premixer (comparative example) and the difference of the present invention with fluted body flameholder described.In comparative example, premixer has the runner of the toroidal on the outer circumferential side that is arranged on the burner of igniting.And the fluted body flameholder is arranged in the export department of premixer.In this comparative example, the inside of premixer is bonded in advance, and has been full of pre-mixed gas in the inside of premixer.Therefore, if flame propagation is to the upstream side of fluted body flameholder, then flame is transmitted to without a break in the premixer and may makes the flameholder melting loss.
With respect to this comparative example, in structure of the present invention, constitute by the airport 12 that separates one by one between jut 1 and the fuel nozzle 10.Figure 14 (a) expression is from the fuel stream of fuel nozzle to the combustion chamber ejection.In the present invention, (left side of Figure 14) is connected with a space 2 airports 12 in the upstream, and fuel stream 22 sprays from the inlet center of fuel nozzle 10 to airport 12.Therefore, than the inlet face of airport 12 position, be suppressed and the mixing of air stream from the fuel stream of fuel nozzle 10 ejections by upstream side.And if fuel stream flow in the airport 12, then fuel stream 22 is mixing with ambient air stream in the diffusion gradually.That is, leaning on the position of upstream side than the inlet face of airport 12, and do not having fuel in the space between the airport of adjacency 211.Therefore, even if flame propagation, can prevent also that flame propagation is to adjacent airport to the upstream side in portion of air hole 12.
In addition, at fuel and air during together by airport 12, the burner plate 11 of fuel combination and air and the configuration relation of fuel nozzle 10 have and prevent that flame from entering the characteristic of airport, and be very high compared with the premixer reliability of comparative example.Distribution 212 of fuel concentration on the H-H cross section among Figure 14 (a) and VELOCITY DISTRIBUTION 213 are illustrated among Figure 14 (b).The longitudinal axis is the coordinate of air intake face, and from the center of airport inlet radius is represented as r.In addition, transverse axis is the relative value of fuel concentration and speed.In addition, the position of dotted line 214 expression airport walls.As shown in the figure, owing to the influence of wall shear stress, the speed of mobile fluid is slack-off near wall 214.Therefore, exist flame to enter the possibility of airport inside along slow-footed zone., the burner plate 11 in according to the present invention and the configuration relation of fuel nozzle 10, in slow-footed wall zone nearby, it is 212 very low that fuel concentration distributes.And, also exist by being captured heat and the effect of quencher, thereby flame can be at airport wall regional spread nearby by wall.Therefore, jut is set, even if flame propagation to the upstream side of jut, also can prevent to be transmitted to the fuel jet orifice of fuel nozzle 10 by the direction of passing through along fuel stream from airport 12 ejections.According to the above, utilize the jut retention flame, and play the also good effect of anti-back-fire.
And hope is inserted into fuel nozzle the inside of airport.As if the inside that fuel nozzle is inserted into airport, then can improve fuel and Air mixing degree.Therefore, by as shown in Figure 9 fuel nozzle 10 being inserted into the inside of airport 12, can realize the raising of further degree of mixing and the raising of flame holding simultaneously.
In addition, with respect to the central shaft of burner, the central shaft of inclination airport 12 also is effectively.Especially, by disposing airport 12 obliquely,, thereby can further improve the stability of flame so that the fuel stream and the air stream that spray from airport 12 have the speed composition that rotates with respect to the burner central shaft.
[embodiment 2]
Fig. 2 (b) is 180 front views of having observed burner plate 11 from the combustion chamber.Fig. 2 (a) be in the whole skeleton diagram of the gas turbine of Figure 11 amplification the general profile chart at peripheral position of fuel nozzle 10 and airport 12, and be the B-B cutaway view of Fig. 2 (b).
In embodiment 1, the flame stabilizationization that will form by the first row airport 12-1, and improved the stability of the flame that forms by secondary series airport 12-2 and the 3rd row airport 12-3.To this, present embodiment has also improved the stability of the flame that is formed by secondary series airport 12-2 by at secondary series airport 12-2 jut 2 being set.Its result can further improve the flame holding of burner integral body.
This basic mechanical device that improves flame holding is identical with content illustrated in fig. 7.That is, all sides (the first row airport 12-1) in burner not only, and also be formed with the circular flow of high temperature at burner outer circumferential side (secondary series airport 12-2).Therefore, circular flow becomes kindling material, also provides heat energy to the pre-mixed gas from the ejection of secondary series airport, thereby improves fire behaviour.
In addition, in Fig. 2, be provided with 2 grades jut.But, 3 grades, 4 grades, multistage jut also can be set according to the hole count of airport or configuration.
In addition, the jut shown in the embodiment 2 not only can be acute angle-shaped, also can consider making property and does quadrangularly.And, also can be the jut of the conical in shape of mitigation.
In addition, in embodiment 2,, can realize simultaneously that further degree of mixing improves and the raising of flame holding by fuel nozzle being inserted the inside of airport.
[embodiment 3]
Fig. 3 (b) is 180 front views of having observed burner plate 11 from the combustion chamber.Fig. 3 (a) be in the whole skeleton diagram of the gas turbine of Figure 11 amplification the general profile chart at peripheral position of fuel nozzle 10 and airport 12, and be the C-C cutaway view of Fig. 3 (b).Figure 12 is the figure that has represented the shape of airport 12.
In the present embodiment, the shape of burner plate 11 is made the shape of having dug out circular cone.That is, as shown in figure 12, the face of the burner plate 11 at export department 301 places of airport 12 is the shapes to the expansion of combustion chamber direction.Therefore, the face that is formed by the export department 301 of airport 12 is with respect to the inclined of burner.
In addition, at the barrier that is provided with upset fuel stream and air stream than the export department 301 of airport 12 by the position in downstream.This barrier is equivalent to jut 1.This jut 1 is circular shape, and is arranged on the airport of each row.In addition, jut 1 is arranged in the downstream of export department 301 of the airport 12 of inclination.
Usually, in the burner that has used flameholder,, then also exist flame to arrive the upstream portion of flameholder and burn out the situation of flameholder along the low flow velocity portion of this turbulent flow if produce turbulent flow (secondary flow) at the upstream portion of flameholder.; because the face that is formed by the export department 301 of airport 12 is with respect to the inclined of burner; so not do not cause the acute angle part or the viscous flow position of turbulent flow, thereby can prevent burning out of jut and improve combustor reliability at the upstream side of barrier (jut).In addition, jut 1 is set, not only improves the flame holding of burner central portion, but also improve the flame holding of peripheral part, thereby can improve the flame holding of burner integral body by listing at each airport.
[embodiment 4]
Fig. 4 (b) is 180 front views of having observed burner plate 11 from the combustion chamber.Fig. 4 (a) be in the whole skeleton diagram of the gas turbine of Figure 11 amplification the general profile chart at peripheral position of fuel nozzle 10 and airport 12, and be the D-D cutaway view of Fig. 4 (b).
Present embodiment is different with embodiment 1, and jut 3 is arranged on the burner central side.In addition, burner plate 11 has increased the thickness of all sides (the axle central side of burner) in the burner with respect to the burner outer circumferential side.Like this, by changing the thickness of burner plate 11, can make the position difference of the export department of the airport 12 on the burner direction of principal axis.
In addition, shown in Fig. 4 (b), burner plate 11 forms end difference 201 by stairstepping is set at burner axle central side, and Monday, side formed recess 200 outside burner.On this recess 200, dispose the export department of secondary series and the 3rd row airport 12-2,12-3.In addition, on the end difference 201 of the burner plate 11 that is provided with ladder with respect to recess 200, the export department that disposes the first row airport 12-1.In the present embodiment, the end difference 201 with first row airport 12-1 of burner plate is equivalent to burner plate extension.
In addition, end difference 201 is with respect to the rounded shape in burner axle center.Therefore, the stairstepping of burner plate 11 forms continuously along circumferencial direction.In addition, side surface part 202 is a cylindrical shape.
In the present embodiment, on the side surface part 202 of burner plate 11, be provided with acute angle-shaped jut 3, make from the fuel stream and the air of secondary series airport 12-2 ejection with the stairstepping that utilizes burner plate 11 and flow the side surface part 202 of collision at burner plate 11.This acute angle-shaped jut 3 also forms along circumferencial direction in the same manner continuously with the stairstepping of burner plate 11.
According to this structure, form the circular flow of high temperature in the downstream of jut 3.And, as becoming kindling material and form the zone than secondary series and the 3rd row airport the annulus between lining 160 and the burner plate extension of being sandwiched in by the space in downstream.That is,, therefore improved the flame holding of burner outer circumferential side because circular flow becomes kindling material and provides heat energy to the unburned pre-mixed gas from the secondary series that is positioned at the burner outer circumferential side and 12 ejections of the 3rd row airport.The mechanical device of basic flame holding is identical with embodiment 1.In the present embodiment, because burner plate 11 is with respect to the outer circumferential side of burner, thickness on interior all sides of burner (burner axle center one side) is thicker, therefore is difficult to be subjected to the restriction on the area, can a plurality of juts 3 be set according to the hole count of airport, position on each position.
[embodiment 5]
Fig. 5 (b) is 180 front views of having observed burner plate 11 from the combustion chamber.Fig. 5 (a) be in the whole skeleton diagram of the gas turbine of Figure 11 amplification the general profile chart at peripheral position of fuel nozzle 10 and airport 12, and be the E-E cutaway view of Fig. 5 (b).
In the present embodiment, the thickness of burner plate 11 is certain.Therefore, the flow channel length of airport 12 is identical.And, cone shape jut 4 is set on the end face of burner plate 11.Shown in Fig. 5 (b), cone shape jut 4 is arranged on the burner central part, and configuration is the fuel stream and the air stream that can hinder from first row airport 12-1 ejection.Form the circular flow of high temperature in the downstream of jut 4.This circular flow is by providing heat energy to unburned pre-mixed gas, and the raising flame holding is promoting to fight.
Because therefore the jut 4 that relates to present embodiment is not only newly-installed burner for simple structure, and on the burner that has been provided with, appends jut 4 is set, can improve flame holding.
In addition, in Fig. 5, jut 4 is one., a plurality of juts 4 are set, also can further improve flame holding by hole count or configuration according to airport.
And, as shown in figure 10, also can be by the jut 7 of toroidal is set between the first row airport 12-1 and secondary series airport 12-2, the flame holding of periphery in improving simultaneously.
[embodiment 6]
Present embodiment will have been used combination from the fuel nozzle of embodiment 1 to embodiment 5 described structure and airport as a burner, and make up a plurality of these burners and constitute a burner.
Fig. 6 (b) is 180 front views of having observed burner plate 11 from the combustion chamber.Fig. 6 (a) be in the whole skeleton diagram of the gas turbine of Figure 11 amplification the general profile chart at peripheral position of fuel nozzle 10 and airport 12.
Shown in Fig. 6 (b), at burner of the central side of burner configuration, and at 6 burners of outer circumferential side configuration of this burner.On these burners, be connected with fuel system respectively.In addition, all burner has adopted the burner of Fig. 1 to construct.
Shown in Fig. 6 (a), fuel system is distributed to each burner, by the burner number of control, make fuel be changed to 100% loading condiction, thereby can stably burn away from the starting conditions of gas turbine according to the load burning.In addition, because each burner combustion stability is high, therefore can reduce the lower limit of the fuel flow rate that supplies to a burner.And, by increasing the fuel nozzle number, can provide the different burner of capacity of each jar with comparalive ease.
In addition, also can use burner of the present invention, and the thickness that 6 burners that will be configured in this burner outer circumferential side are made the burner plate necessarily and the structure of jut is not set in the configuration of the central side of burner.In this configuration, the burner that is arranged on the central side of burner plays the effect of kindling material.Therefore, even if at the burner of outer circumferential side individually under the state of the retention flame, also can be from the burner burner heat supply laterally of central side.Thereby, can improve combustion stability in burner integral body.
From the burner shown in the embodiment 1 to embodiment 6, not only be applied to gas turbine burner, but also can be applied to carry fuel reforming on fuel cell with burner, boiler with burner, hot air heater or incinerator etc., the burner miscellaneous that acts as a fuel with gases such as methane.
The present invention has the utilizability on the following industry.
This burner configuration is not limited only to gas turbine, can also be corresponding to burner or the fuel electricity of boiler The modification device in pond is with burner etc., all burners of burning gases fuel.
Claims (10)
1. a burner is characterized in that,
Have: the burner plate that above-mentioned fuel and above-mentioned air is mixed during together by airport at fuel and air; Part as this burner plate extends to from the burner plate extension of combustion chamber one side of above-mentioned airport separation; And pass through the outstanding jut of direction at the above-mentioned fuel of the combustion chamber of this burner plate extension one side direction stream, and the gap of relative above-mentioned jut is also bigger than the diameter of above-mentioned airport, forms kindling material and form the zone between above-mentioned burner plate, above-mentioned burner plate extension and above-mentioned jut.
2. a burner is characterized in that,
Have: make the burner plate of the stairstepping that above-mentioned fuel and above-mentioned air mix during together by airport at fuel and air; Outer circumferential side at this burner plate extends to from the burner plate extension of combustion chamber one side of above-mentioned airport separation; And pass through the outstanding acute angle-shaped jut of direction at the above-mentioned fuel of the combustion chamber of this burner plate extension one side direction stream, and the gap of relative above-mentioned jut is also bigger than the diameter of above-mentioned airport, forms kindling material and form the zone between above-mentioned burner plate, above-mentioned burner plate extension and above-mentioned jut.
3. burner according to claim 1 is characterized in that,
Above-mentioned burner plate extension has been strengthened the above-mentioned burner plate of axle center one side by the outer circumferential side with respect to above-mentioned burner the stairstepping of thickness forms,
Outer circumferential side at above-mentioned stairstepping is provided with jut.
4. burner according to claim 1 is characterized in that,
The thickness of above-mentioned burner plate is certain,
With hindering, be arranged on than the ejection portion of above-mentioned airport and lean on the position in downstream from the jut of the above-mentioned burner plate of the above-mentioned fuel stream of the above-mentioned airport ejection of axle center one side that is configured in above-mentioned burner and air stream.
5. burner according to claim 1 is characterized in that,
Above-mentioned airport is centroclinal with respect to the axle of above-mentioned burner.
6. burner according to claim 1 is characterized in that,
Above-mentioned jut is tetragonal jut.
7. burner according to claim 1 is characterized in that,
Possess a plurality of burners with above-mentioned burner plate.
8. burner according to claim 6 is characterized in that,
At the axle center of above-mentioned burner, configuration has the above-mentioned burner of the burner plate of stairstepping,
And, dispose the certain burner of thickness of above-mentioned burner plate at the outer circumferential side of above-mentioned burner.
9. the combustion method of a burner is characterized in that, possesses:
In the inside that is arranged at the airport on the burner plate, the outer circumferential side that is formed on fuel stream has formed first operation of the coaxial jet flow of air stream;
This coaxial jet flow is from second operation of above-mentioned airport to the combustion chamber ejection; And,
Above-mentioned coaxial jet flow collision is on the jut of the burner plate extension that extends to combustion chamber one side of separating from above-mentioned airport, and the 3rd operation of formation kindling material.
10. the combustion method of burner according to claim 9 is characterized in that,
Fuel stream and air stream from above-mentioned airport ejection have the speed composition with respect to the central shaft rotation of above-mentioned burner.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2007-116304 | 2007-04-26 | ||
| JP2007116304 | 2007-04-26 | ||
| JP2008089152A JP5188238B2 (en) | 2007-04-26 | 2008-03-31 | Combustion apparatus and burner combustion method |
| JP2008-089152 | 2008-03-31 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101294715A true CN101294715A (en) | 2008-10-29 |
| CN101294715B CN101294715B (en) | 2010-09-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810092375XA Active CN101294715B (en) | 2007-04-26 | 2008-04-24 | Combustion equipment and burner combustion method |
Country Status (3)
| Country | Link |
|---|---|
| JP (1) | JP5188238B2 (en) |
| CN (1) | CN101294715B (en) |
| HK (1) | HK1125689A1 (en) |
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| CN102032569A (en) * | 2009-09-30 | 2011-04-27 | 株式会社日立制作所 | Combustor |
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2008
- 2008-03-31 JP JP2008089152A patent/JP5188238B2/en active Active
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- 2009-04-28 HK HK09103923.7A patent/HK1125689A1/en unknown
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Also Published As
| Publication number | Publication date |
|---|---|
| CN101294715B (en) | 2010-09-22 |
| JP2008292138A (en) | 2008-12-04 |
| JP5188238B2 (en) | 2013-04-24 |
| HK1125689A1 (en) | 2009-08-14 |
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