CN100368664C - Combustion chamber/venturi cooling apparatus and method for low nox emission combustor - Google Patents
Combustion chamber/venturi cooling apparatus and method for low nox emission combustor Download PDFInfo
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- CN100368664C CN100368664C CNB018239404A CN01823940A CN100368664C CN 100368664 C CN100368664 C CN 100368664C CN B018239404 A CNB018239404 A CN B018239404A CN 01823940 A CN01823940 A CN 01823940A CN 100368664 C CN100368664 C CN 100368664C
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- venturi tube
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- 238000001816 cooling Methods 0.000 title claims abstract description 138
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 33
- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000010304 firing Methods 0.000 claims description 49
- 239000000446 fuel Substances 0.000 claims description 26
- 239000007789 gas Substances 0.000 claims description 17
- 230000003187 abdominal effect Effects 0.000 claims description 13
- 239000000112 cooling gas Substances 0.000 claims description 2
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 33
- 238000011144 upstream manufacturing Methods 0.000 description 17
- 238000007599 discharging Methods 0.000 description 10
- 239000000203 mixture Substances 0.000 description 4
- 239000003550 marker Substances 0.000 description 3
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- 238000010438 heat treatment Methods 0.000 description 2
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- NUFNQYOELLVIPL-UHFFFAOYSA-N acifluorfen Chemical compound C1=C([N+]([O-])=O)C(C(=O)O)=CC(OC=2C(=CC(=CC=2)C(F)(F)F)Cl)=C1 NUFNQYOELLVIPL-UHFFFAOYSA-N 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000007084 catalytic combustion reaction Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000001351 cycling effect Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 210000000867 larynx Anatomy 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/005—Combined with pressure or heat exchangers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02G—HOT GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINE PLANTS; USE OF WASTE HEAT OF COMBUSTION ENGINES; NOT OTHERWISE PROVIDED FOR
- F02G3/00—Combustion-product positive-displacement engine plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
Abstract
The present invention relates to a method and a device, which are used for providing cooling air for a drain combustor (10) with low NOx in a gas turbine to a venturi pipe (11) and a combustion chamber (13). The method and the device comprise: the point near the throat of the combustion chamber (13) is provided with an annular air channel (14) surrounding the combustion chamber and the venturi pipe, so the cooling air can pass along the combustion chamber (13) and the venturi pipe (11), and the air goes out from the position near the front part of a convergence region (28) of the venturi pipe (11). When the cooling air passes through the combustion chamber (13) and the venturi pipe (11), the cooling air is heated, and the heated cooling air returns to a premixing chamber (12); thereby, the efficiency of the combustor (10) is increased, and the discharge amount of NOx in the combustion process is reduced simultaneously.
Description
Technical field
The present invention relates generally to a kind of apparatus and method, and these apparatus and method are used for cooling and are used for gas turbine engine cooling combustion chamber and Venturi tube to reduce oxide emissions.More specifically say so and disclosed a kind of device, this device is used for cooling combustion chamber/Venturi tube, and can will introduce mixing chamber to be used for combustion process and to reduce the nitrogen oxide discharge capacity through the cooling air of preheating.
Background technique
The present invention typically is used for driving the gas turbine engine of the low NOx of the dry type of generator.Each burner comprises that one closes the firing chamber in a chamber and a downstream in the fuel/air premix of upstream, is separated by a Venturi tube with a narrow throat therebetween, and this has the effect of the Venturi tube pilot flame suppressor of throat.The present invention relates to improve the cooling of the firing chamber that comprises the venturi tube wall, reduce the nitrogen oxide discharge capacity simultaneously.
U. S. Patent 4,292 has been narrated a gas turbine burner in 801, and this burner is included in fuel and the premixing cavity of air and the firing chamber in a downstream of upstream.
U. S. Patent 5,117,636 and U. S. Patent 5,285,631 spoken of cooling combustion locular wall and venturi tube wall.Say in this two patent, if the throat that the outlet of the air passageways of cooling usefulness approaches very much Venturi tube, with regard to the problem that exists to allow cooling air channels to enter the firing chamber.Venturi tube has a marker space in the downstream of the portion of dispersing (flaring portion), and it produces a pressure difference, thereby attracts the air of cooling usefulness, and this situation can cause the unstability of burning.Yet venturi tube wall and chamber wall are sufficiently cooled also is very important, because the temperature in the firing chamber is very high.
The present invention has eliminated the problem of being discussed in the prior art, because the cooling route of Venturi tube is no longer put into the zone of combustion at axial afterbody and venturi throat downstream row through adjusting the air that makes cooling usefulness.In fact, the air of cooling usefulness flows in the opposite direction and is driven in the premixing cavity that enters the Venturi tube upstream with the air that is used in cooling combustion chamber and Venturi tube, having improved the efficient of total combustion process has eliminated simultaneously at U. S. Patent 5, the marker space in the repetitive cycling of the cooling air of any kind of Venturi tube afterbody of discussing in 117,636.
The MANUFACTURER and the user to the regulations gas turbine burner very deeply concerned of discharging of government's promulgation recently.The discharging of nitrogen oxide deeply concerned especially (NOx) is because the nitrogen oxide discharging causes the pollution to air.
The formation of well-known nitrogen oxide is the function of the flame temperature waiting time and equivalent proportion.The real nitrogen oxide that shows of bygone can reduce by reducing the time that flame temperature and flame rests on higher temperature.Nitrogen oxide also is that equivalent proportion and fuel are to the stoichiometric function of air (f/a).That is falling the nitrogen oxide discharging needs extremely low f/a ratio.Reducing f/a than being not have cost, mainly is possible " stopping working "." stop working " is such a case: because its unstability, flame no longer can be kept.This situation can take place usually when fuel-air stoichiometry is reduced to a little higher than thin flammability limits (poor flammability limits).By the premixed air preheating, can reduce " stopping working " temperature of flame, thereby allow under the reduction temperature, to burn, so the discharging of NOx can be lower.So the lower limit that the introducing preheated air is driving f/a compares a lean-limit is an ideal situation to reduce NOx and still keep stable flame simultaneously.
In the double mode gas turbine engine systems of a twin-stage, second level burner comprises that Venturi tube structure is with smooth combustion flame.Fuel (rock gas or liquid) and the burner premixing cavity of air in the Venturi tube upstream carry out premixing, and the mixture of air/fuel burns in the downstream of Venturi tube throat.This Venturi tube structure can quicken air/fuel and flow through throat and do not allow flame flash back premixing district ideally.It is that fuel is continuous and smooth combustion is necessary that the flame that surpasses throat in Venturi tube keeps distinguishing.Chamber wall and in the burned flame heating of venturi tube wall of narrow throat region front and back, therefore essential cooling.In the past, this is by backside impingement cooling method cooling, and the air that cools off flows along the rear side of combustion wall and venturi tube wall, and cooling air is gone out the firing chamber that is discharged into the Venturi tube downstream there.
The present invention has overcome the problem that cooling air channel took place of the above-mentioned type, has eliminated the situation that allows the air that cools off enter the combustion zone in Venturi tube downstream fully.The present invention does not allow the air of any cooling Venturi tube to flow into the firing chamber in downstream.The present invention is flow through along the air passageways of chamber wall and venturi tube wall the air that cools off this air that cools off to be preheated and at the air feed-in premixing cavity that cools off of Venturi tube (convergence wall) upstream.This has improved the efficient of total reduction NOx discharging again.
Summary of the invention
The invention provides a kind of burner that is used for the low NOx drainage of gas turbine engine, this burner comprises: a liner, this liner have one first annular wall; And comprise that one is used for the premixing cavity and the firing chamber in order to burn described fuel and air of fuel combination and air, and described premixing cavity is connected with the firing chamber, and described first annular wall has one first hole at least; One Venturi tube, it has one second annular wall, this second annular wall comprises that a convergent walls, disperses wall, described convergent walls is connected to form the necking down throat of a Venturi tube with the described wall of dispersing, described necking down throat is between described premixing cavity and described firing chamber, one described second annular wall from described first annular wall radially inwardly and have and the adjacent tail end in described at least one first hole, described second annular wall is from described first annular wall radially inwardly and have a tail end adjacent with at least one second hole with described at least one first hole; One passage, be used to make cooling air to flow through described Venturi tube, described passage extends from described at least one first hole to described at least one second hole, described at least one second hole is radially outer at described premixing cavity, described passage comprise one from described first wall radially inwardly with from the radially outer first portion of described second wall and from the radially outer second portion of described second wall, described second portion extends to described at least one second hole from described first portion, and described first hole is radially outer from described first portion; One blocking-up ring, it extends and is connected hermetically with them to described first annular wall from the tail end of described second annular wall, and described blocking-up ring prevents that the cooling air in the first portion of described passage from flowing directly into described firing chamber and not flowing through the second portion of described passage; Wherein, described passage is communicated with described at least one first hole and described at least one second orifice flow body, described passage is connected with described mixing chamber by described at least one second hole, cooling air is in cooling described Venturi tube and after being heated, flow into premixing cavity from described passage, thereby increased the efficient of combustion process and reduced the discharge amount of NOx.
Preferably, this burner also comprises one from the radially outer ringwise basically annular abdominal belt wall of first annular wall and at least one the 3rd hole described first annular wall, the first portion of described passage is connected with the second portion of described passage by described the 3rd hole, wherein, described abdominal belt wall forms the radially external boundary of the second portion of a described passage.
Preferably, described at least one first hole comprises a plurality of along circumferentially spaced a plurality of first holes of first annular wall, and each described first hole in the footpath of the first portion of passage to the outside.
Preferably, described at least one second hole comprises around circumferentially spaced a plurality of second holes of first annular wall, and the footpath that each described second hole is in premixing cavity to the outside.
Preferably, this at least one the 3rd hole comprises around circumferentially spaced a plurality of the 3rd holes of first annular wall, and each the 3rd hole is in the Venturi tube footpath to the outside.
The present invention also provides the method for the Venturi tube in a kind of cooling gas turbine engine combustors, this method comprises: a burner liner is provided, this liner has one first annular wall, and comprise that one is used for the firing chamber of premixing cavity and the described fuel of burning and the air of fuel combination and air, described premixing cavity is communicated with described firing chamber, and this first annular wall has one first hole at least; One Venturi tube is provided, this Venturi tube comprises one second annular wall, this second annular wall comprises that a convergent walls and disperses wall, thereby described convergent walls links to each other and forms the throat of this Venturi tube with the described wall of dispersing, described throat is between premixing cavity and firing chamber, and described second annular wall from first annular wall radially inwardly and have adjacent tail end at least one first hole with this; Provide a passage so that cooling air flows through described Venturi tube, described passage extends at least one second hole from this first hole, this at least one second hole is positioned at the radially outward place of premixing cavity and is connected with it, described passage comprises that one radially inwardly and from this second wall radially outward and along described disperses the first portion that wall and convergent walls are extended from first wall, an and second portion, this second portion is from described premixing cavity radially outward, and described second portion extends to this at least one second hole from described first portion; Make cooling air go into the first portion of described passage by described at least one first orifice flow; Heat is passed to cooling air from described second wall, thereby cool off this second wall and cooling air itself is heated; Make cooling air flow into the second portion of described passage from the first portion of described passage; Make cooling air flow through described at least one second hole and enter described premixing cavity from the second portion of described passage;
Preferably, the step that heat is passed to this cooling air from described second wall comprises heat is passed to described cooling air and heat is passed to described cooling air from described convergent walls from dispersing wall.
The present invention also provides a kind of method that produces low NOx drainage from the gas turbine engine burner, this method comprises: a burner liner is provided in burner, described liner has one first annular wall, and comprise the firing chamber of a premixing cavity in order to fuel combination and air feed and described fuel of burning and air, described premixing cavity is connected with described firing chamber, and described first annular wall has at least one first hole; One Venturi tube that comprises one second annular wall is provided, this Venturi tube second annular wall comprises that a convergent walls and disperses wall, described convergent walls links to each other with the described wall of dispersing, thereby form a throat of Venturi tube, described throat is between premixing cavity and firing chamber, described second annular wall is radially inside from described first annular wall, and has and tail end that this at least one first hole is contiguous; The passage that makes cooling air flow through Venturi tube is provided, described passage extends at least one second hole from described first hole, this at least one second hole is positioned at the premixing cavity radially outward, and be communicated with the latter, described passage comprises that one radially inwardly reaches from the described second wall radially outward and along described from described first wall and to disperse the first portion that wall and convergent walls are extended; And one from the radially outer second portion of premixing, and described second portion extends to described at least one second hole from described first portion; Make cooling air go into the first portion of passage by described at least one first orifice flow; Thereby heat is passed to described cooling air from second wall cool off this second wall and described cooling air itself is heated; Make cooling air flow into the second portion of described passage from the first portion of described passage; Make described cooling air flow through at least one second orifice flow and go into premixing cavity from the second portion of described passage; And, with the fuel mix in heated cooling air and the premixing cavity and burn described cooling air and described fuel.
Preferably, the step that heat is passed to cooling air from described second wall comprises heat is passed to described cooling air from the described wall of dispersing, and subsequently heat passed to cooling air from convergent walls.
Chamber wall of the present invention itself is cylindrical shape and the rib that comprises a plurality of protrusions on the outer surface in order to increase the surface area with the cool air mutual effect of flowing through of cooling off on the combustion cylinder liner basically.The venturi tube wall also connects together with the firing chamber and comprises a pair of convergent/divergent wall with restriction throat, and the latter and firing chamber liner are formed together intricately.The air of cooling usefulness not only flows through and flows through around Venturi tube around the throat less chamber wall, for whole burner chamber and Venturi tube provide cooling air.When cooling air during towards throat's upstream flow, the temperature of cooling air rises.
Cooling air channels is to be formed by the cylindrical wall that another and chamber wall separate, it is installed in around the chamber wall with one heart, a pair of tapered wall with one heart with structure similarly be arranged on around the venturi tube wall with form a complete annular passage with allow air around whole firing chamber and whole Venturi tube flow.The downstream of firing chamber and the inlet opening of cooling air are separated by an annular barrier layer, so that the cooling air in passage can't flow into the firing chamber downstream.Do not have air to be introduced, perhaps enter the zone that is spaced of Venturi tube by downstream to the firing chamber.In fact, the cooling air outlet is positioned at the Venturi tube upstream, and cooling air and combustion-gas flow flow in the opposite direction, earlier by chamber wall, venturi tube wall then.The cooling air that is preheated is introduced into premixing cavity at last, has increased the efficient of system, has reduced the discharge amount of nitrogen oxide because of flame holding.
Cooling air is derived from the compressor of steam turbine, and it is that the direction of upstream flows around whole burner body with respect to combustion process that this compressor makes high-pressure air.This high-pressure air is driven the air inlet hole of and near flow through a plurality of cooling air channels firing chamber downstream mobile around blazer.Force cooling air to flow to Venturi tube along burner outer wall, throat through Venturi tube, process has the forward position and a receive path of the venturi tube wall of an outlet air passage, and the latter makes air enter the premixing cavity of Venturi tube throat upstream by another serial inlet opening.Because such liquid form, cooling air just can not disturb the combustion process that occurs in second firing chamber, because do not have outlet or hole to interact with second firing chamber itself.In addition, when cooling air flowed to Venturi tube and is introduced in the inlet premixing cavity of Venturi tube upstream, cooling air was heated in passage, and heated air helps the efficient of burner and reduces disposal of pollutants.
The frame of burner comprises an annular in addition, and this annular is accepted the cooling air by the exit orifice of Venturi tube upstream in addition.This air is then further upstream by the many mouthfuls of intake air holes of leading to premixing cavity, and the cooling air that allows to be preheated flows into the premixing zone at the air passageways of preceding venturi tube wall.
Chamber wall comprises that the ring of a plurality of protuberances to increase heat from the transmission efficiency of combustion wall to air, makes this wall have more areas that contact with air.Though used an other concentric walls to form around the firing chamber and the cooling air channels of Venturi tube, in another embodiment, utilized the outer wall of this burner itself that this function is provided.
An object of the present invention is by providing air cooling, under desirable operating conditions, keep a stable flame, thereby in a gas turbine burner system, reduce the discharging of nitrogen oxide firing chamber and Venturi tube.
Another object of the present invention provides the buner system of the discharging of a low nitrogen oxide, it utilize a Venturi tube with use that multiple cooling air is provided with cooling combustion chamber and Venturi tube.
Another some purpose of the present invention is by the air that is preheated the premixing process that utilizes from the cooling combustion chamber and Venturi tube is come, the flame that the reduces burner temperature of " stopping working ".
According to these and will become below and more clearly reach other purposes, the present invention is made detailed narration below in conjunction with accompanying drawing.
Description of drawings
Fig. 1 shows the side sectional view of gas turbine engine systems of an expression prior art, and a cooling air channels is wherein gone into cooling air emission around firing chamber and the firing chamber;
Fig. 2 shows the stereogram of a gas turbine engine systems of the present invention;
Fig. 3 shows the side sectional view of a gas turbine burner system of the present invention;
Fig. 4 shows and is used for firing chamber of the present invention and Venturi tube and partly-premixed cross-sectional view of closing the chamber;
Fig. 5 shows a cross sectional view, and wherein part has been analysed and observe the cooling air channels that is positioned at the Venturi tube upstream in annular abdominal belt chamber, is used to receive cooling air so that this air is introduced premixing cavity;
Fig. 6 shows analysing and observe and enlarged view of chamber wall tail end interface;
Embodiment
Now see also Fig. 1.There is shown the burner 110 of an original gas turbine of prior art.This burner 110 comprises a Venturi tube 111, one premixing cavitys 112, and it is used for premixed air and fuel, and a burner chamber 113 and a burning cover 115.
As shown in this prior art burner, cooling air indicated by the arrow flows along Venturi tube 111 outer walls under pressure.This cooling air enters system by a plurality of positions along liner 110.Portion of air enters by hole 120, and remaining air flows along shell.Cooling air under pressure is the source with the steam turbine compressor, enters system by a plurality of holes 121.As shown in Figure 1, the convergent/divergent wall (convergent-divergent shape wall) 127 of the taper of cooling air bump and cooling Venturi tube 111, and flow through cylindrical channel 114 downstream, all walls of cooling drum shape firing chamber 113.This cooling air is gone out by annular release aperture 125 along chamber wall.This air enters the combustion process in downstream then.Part cooling air also enters the premixing district by hole 126.Remaining cooling air flow is to the front end of liner, and air covers 115 by front end and burning that hole 123 enters liner there.Not the cooling air that enters by hole 123 partly enter and by the zone 124 with gas and fuel mix.U. S. Patent 5,117,636 have discussed the structure of the Venturi tube of the prior art that is shown in Fig. 1.Discussed about cooling air near Venturi tube 111 by outlet passage 125 thereby the existence that combustion process and mixture-base are referred to as the marker space in the `636 patent is disturbed the problem of combustion process.
The present invention has eliminated any problem that is proposed fully in patent `636.
Now see also Fig. 2 and Fig. 3, there is shown gas turbine burner 10, it comprises a Venturi tube 11.
Venturi tube 11 comprises a cylindrical shape part, the venturi tube wall that it forms burner chamber 13 and integrally forms, and the venturi tube wall is in the downstream direction convergence and disperse (convergent-divergent), forms an annular or the circular necking down 11a of throat.The purpose of Venturi tube and the 11a of necking down throat is the tongues of fire 13 backflash from the firing chamber that prevent flame.
One concentric, the columnar wall 11b of part round the Venturi tube 11 that comprises convergence and disperse the venturi wall between Venturi tube 11 and concentric walls 11b, forming an air passageways 14, this passage allow cooling air along the outer surface of Venturi tube 11 by to cool off.
A housing (not shown) and comprise the air of pressurized in the outer surrounding of burner 10, move in the premixing zone 12 of this air upstream.This air is next from the compressor of steam turbine.This is the very high air of pressure.This cooling air channels 14 has some inlet openings 27, and this inlet opening 27 allows to enter by hole 27 and received by the first portion 45 around the passage 14 of Venturi tube 11 around the high-pressure air of burner.Cooling air passes through along Venturi tube 11, passes through the convergence of Venturi tube and disperses wall and the 11a of necking down throat of Venturi tube.The cooling air that is preheated is gone out from exit orifice 28, enters annular abdominal belt chamber 16.The cooling air of burner utilization process heating also is allowed to enter premixing cavity 12 by hole 29 and 22.Detail is shown in Fig. 5 and Fig. 6.Please note that entering is heated cooling air in cooling procedure at the premixing cavity of the convergent walls of Venturi tube and Venturi tube necking down throat 11a upstream now.The air that use was preheated orders about the f/a ratio and reaches a lean-limit (lower limit of poor ratio) to reduce the discharging of NOx in the steady flame.
Now see also Fig. 4, cooling air channels 14 comprises a plurality of spacer 14a, and they are separated Venturi tube 11 with wall 11b.Abdominal belt wall 16 forms one of second portion 46 of passages 14 a radially external boundary and ringwise basically chamber is provided, and its allows the pressure air of outside and the cooling air of going out to be accommodated within the premixing cavity 12.Downstream end in the firing chamber 13 that the annular tail end by Venturi tube 11 forms is being provided with an annular blocking-up ring 40, and it prevents that cooling air from leaking downstream and enters the firing chamber.This has just alleviated the combustion problem that is caused by cooling air in the prior art.
Now see also Fig. 5, there is shown air passageways 14 along having that section of Venturi tube of restraining and dispersing wall and the 11a of throat, wherein cooling air is discharged by hole 28 and is entered the air chamber that is formed by the abdominal belt wall of heaving 16.The air of the another part under elevated pressures enters and orders about the present heated cooling air that is included in the passage 14 by hole 32 and enters premixing cavity 12 at interior air by hole 22 and 29.
Fig. 6 shows the tail end of firing chamber 13 and comprises the end of the Venturi tube 11 of blocking-up ring 40, and this blocking-up ring 40 ringwise and be with seal form whole aft mounted around Venturi tube 11.Any part that the cooling air of inlet passage 14 can not escape and lose or enter firing chamber 13.Please note some air be allow by hole 30 and 31 enter above firing chamber 13 than the locular wall at rear portion.Outside that hole 30 and 31 is arranged on burner 10 is used for the tail end of cool burner.
The present invention also comprises the method for improved cooling combustion chamber and Venturi tube, and the air that this method allows to be used to cool off improves the efficient of combustion process itself to reduce the discharge amount of NOx.Aspect air stream, cooling air enters Venturi tube external chennel 14 by a plurality of holes 27.The air of one predetermined quantity is introduced passage 14 by parts 17.Cooling air is driven downstream by blocking-up ring 40, and it is expanded with catalytic combustion device 10 under the heat load condition.Cooling air upstream passes through the convergent/divergent section of the first portion 45 of passage 14, and it is by the second portion and the burner 10 of hole 28 inlet passages of Venturi tube 11.This cooling air is full of a chamber that is formed by ring abdominal belt 16 then.Because the pressure in the whole cooling path falls and the increase of temperature, the air that has increased pressure is introduced into abdominal belt chamber 16 by a plurality of holes 32.This cooling air passes through around a plurality of unit 18, and these a plurality of unit are positioned at whole abdominal belt chamber 16 to support to be in the abdominal belt under the pressure.Cooling air enters premixing cavity by the groove 29 of hole 22 and burner 10.Between cooling channel 14 and premixing cavity 12, there is not undesirable leakage to take place because the preceding support 19 that is fixed on burner 10 and the Venturi tube is arranged.Cooling air not the remaining part by hole 27 on unit 17 by and upstream advance to be introduced into burner 10 or lid 15.This air is to be introduced into by a plurality of positions in 16 fronts, abdominal belt chamber.
By such process, changed the path that is used to cool off and supply combustion air in the past just, reduced fuel-air ratio, the discharging that makes NOx reduces and does not produce unsettled flame.
Though the present invention is as mentioned above and be to narrate as present preferred embodiment,, should be understood that, that the present invention is not limited to the embodiment who is disclosed.On the contrary, the present invention plans to be included within protection scope of the present invention in the arrangement of the spirit of appended claims and all many variations in the scope and equivalence.
Claims (9)
1. burner that is used for the low NOx drainage of gas turbine engine, this burner comprises:
One liner, this liner have one first annular wall; And comprise that one is used for the premixing cavity and the firing chamber in order to burn described fuel and air of fuel combination and air, and described premixing cavity is connected with the firing chamber, and described first annular wall has one first hole at least;
One Venturi tube, it has one second annular wall, this second annular wall comprises that a convergent walls, disperses wall, described convergent walls is connected to form the necking down throat of a Venturi tube with the described wall of dispersing, described necking down throat is between described premixing cavity and described firing chamber, one described second annular wall from described first annular wall radially inwardly and have and the adjacent tail end in described at least one first hole, described second annular wall is from described first annular wall radially inwardly and have a tail end adjacent with at least one second hole with described at least one first hole;
One passage, be used to make cooling air to flow through described Venturi tube, described passage extends from described at least one first hole to described at least one second hole, described at least one second hole is radially outer at described premixing cavity, described passage comprise one from described first wall radially inwardly with from the radially outer first portion of described second wall and from the radially outer second portion of described second wall, described second portion extends to described at least one second hole from described first portion, and described first hole is radially outer from described first portion;
One blocking-up ring, it extends and is connected hermetically with them to described first annular wall from the tail end of described second annular wall, and described blocking-up ring prevents that the cooling air in the first portion of described passage from flowing directly into described firing chamber and not flowing through the second portion of described passage;
Wherein, described passage is communicated with described at least one first hole and described at least one second orifice flow body, described passage is connected with described mixing chamber by described at least one second hole, cooling air is in cooling described Venturi tube and after being heated, flow into premixing cavity from described passage, thereby increased the efficient of combustion process and reduced the discharge amount of NOx.
2. the burner of low NOx drainage as claimed in claim 1, it is characterized in that, it also comprises one from the radially outer ringwise basically annular abdominal belt wall of first annular wall and at least one the 3rd hole described first annular wall, the first portion of described passage is connected with the second portion of described passage by described the 3rd hole, wherein, described abdominal belt wall forms the radially external boundary of the second portion of a described passage.
3. the burner of low NOx drainage as claimed in claim 2 is characterized in that, described at least one first hole comprises a plurality of along circumferentially spaced a plurality of first holes of first annular wall, and each described first hole in the footpath of the first portion of passage to the outside.
4. the burner of low NOx drainage as claimed in claim 3 is characterized in that, described at least one second hole comprises around circumferentially spaced a plurality of second holes of first annular wall, and the footpath that each described second hole is in premixing cavity to the outside.
5. the burner of low NOx drainage as claimed in claim 4 is characterized in that, this at least one the 3rd hole comprises around circumferentially spaced a plurality of the 3rd holes of first annular wall, and each the 3rd hole is in the Venturi tube footpath to the outside.
6. the method for the Venturi tube in the cooling gas turbine engine combustors is characterized in that this method comprises:
One burner liner is provided, this liner has one first annular wall, and comprising that one is used for the firing chamber of premixing cavity and the described fuel of burning and the air of fuel combination and air, described premixing cavity is communicated with described firing chamber, and this first annular wall has one first hole at least;
One Venturi tube is provided, this Venturi tube comprises one second annular wall, this second annular wall comprises that a convergent walls and disperses wall, thereby described convergent walls links to each other and forms the throat of this Venturi tube with the described wall of dispersing, described throat is between premixing cavity and firing chamber, and described second annular wall from first annular wall radially inwardly and have adjacent tail end at least one first hole with this;
Provide a passage so that cooling air flows through described Venturi tube, described passage extends at least one second hole from this first hole, this at least one second hole is positioned at the radially outward place of premixing cavity and is connected with it, described passage comprises that one radially inwardly and from this second wall radially outward and along described disperses the first portion that wall and convergent walls are extended from first wall, an and second portion, this second portion is from described premixing cavity radially outward, and described second portion extends to this at least one second hole from described first portion;
Make cooling air go into the first portion of described passage by described at least one first orifice flow;
Heat is passed to cooling air from described second wall, thereby cool off this second wall and cooling air itself is heated;
Make cooling air flow into the second portion of described passage from the first portion of described passage;
Make cooling air flow through described at least one second hole and enter described premixing cavity from the second portion of described passage;
7. method as claimed in claim 6 is characterized in that, the step that heat is passed to this cooling air from described second wall comprises to be passed to heat described cooling air and heat is passed to described cooling air from described convergent walls from dispersing wall.
8. one produce the method for low NOx drainage, it is characterized in that this method comprises from the gas turbine engine burner:
One burner liner is provided in burner, described liner has one first annular wall, and comprise the firing chamber of a premixing cavity in order to fuel combination and air feed and described fuel of burning and air, described premixing cavity is connected with described firing chamber, and described first annular wall has at least one first hole;
One Venturi tube that comprises one second annular wall is provided, this Venturi tube second annular wall comprises that a convergent walls and disperses wall, described convergent walls links to each other with the described wall of dispersing, thereby form a throat of Venturi tube, described throat is between premixing cavity and firing chamber, described second annular wall is radially inside from described first annular wall, and has and tail end that this at least one first hole is contiguous;
The passage that makes cooling air flow through Venturi tube is provided, described passage extends at least one second hole from described first hole, this at least one second hole is positioned at the premixing cavity radially outward, and be communicated with the latter, described passage comprises that one radially inwardly reaches from the described second wall radially outward and along described from described first wall and to disperse the first portion that wall and convergent walls are extended;
And one from the radially outer second portion of premixing, and described second portion extends to described at least one second hole from described first portion;
Make cooling air go into the first portion of passage by described at least one first orifice flow;
Thereby heat is passed to described cooling air from second wall cool off this second wall and described cooling air itself is heated;
Make cooling air flow into the second portion of described passage from the first portion of described passage;
Make described cooling air flow through at least one second orifice flow and go into premixing cavity from the second portion of described passage; And,
With the fuel mix in heated cooling air and the premixing cavity and burn described cooling air and described fuel.
9. method as claimed in claim 8 is characterized in that, the step that heat is passed to cooling air from described second wall comprises heat is passed to described cooling air from the described wall of dispersing, and subsequently heat passed to cooling air from convergent walls.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/US2001/045097 WO2003093664A1 (en) | 2000-06-28 | 2001-11-30 | Combustion chamber/venturi cooling for a low nox emission combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1582365A CN1582365A (en) | 2005-02-16 |
| CN100368664C true CN100368664C (en) | 2008-02-13 |
Family
ID=32769576
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB018239404A Expired - Fee Related CN100368664C (en) | 2001-11-30 | 2001-11-30 | Combustion chamber/venturi cooling apparatus and method for low nox emission combustor |
Country Status (8)
| Country | Link |
|---|---|
| EP (1) | EP1461520A4 (en) |
| JP (1) | JP4121998B2 (en) |
| KR (1) | KR100831772B1 (en) |
| CN (1) | CN100368664C (en) |
| AU (1) | AU2002219991A1 (en) |
| BR (1) | BR0117192B1 (en) |
| CA (1) | CA2468646C (en) |
| MX (1) | MXPA04005182A (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7895841B2 (en) * | 2006-07-14 | 2011-03-01 | General Electric Company | Method and apparatus to facilitate reducing NOx emissions in turbine engines |
| KR100890823B1 (en) * | 2007-11-13 | 2009-03-30 | 한국기계연구원 | Gas turbine system |
| KR100862374B1 (en) * | 2007-11-13 | 2008-10-13 | 한국기계연구원 | Overheating preventing gas turbine system |
| US7874157B2 (en) * | 2008-06-05 | 2011-01-25 | General Electric Company | Coanda pilot nozzle for low emission combustors |
| US20100192580A1 (en) * | 2009-02-03 | 2010-08-05 | Derrick Walter Simons | Combustion System Burner Tube |
| US8646277B2 (en) * | 2010-02-19 | 2014-02-11 | General Electric Company | Combustor liner for a turbine engine with venturi and air deflector |
| US9267687B2 (en) | 2011-11-04 | 2016-02-23 | General Electric Company | Combustion system having a venturi for reducing wakes in an airflow |
| CN104807042A (en) * | 2015-05-15 | 2015-07-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Combustion chamber |
| US10215415B2 (en) * | 2015-09-23 | 2019-02-26 | General Electric Company | Premix fuel nozzle assembly cartridge |
| CN108518290B (en) * | 2018-02-24 | 2023-08-29 | 陕西航天机电环境工程设计院有限责任公司 | Array self-striking type water mist cooling device |
| US11428411B1 (en) * | 2021-05-18 | 2022-08-30 | General Electric Company | Swirler with rifled venturi for dynamics mitigation |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4982570A (en) * | 1986-11-25 | 1991-01-08 | General Electric Company | Premixed pilot nozzle for dry low Nox combustor |
| US5127221A (en) * | 1990-05-03 | 1992-07-07 | General Electric Company | Transpiration cooled throat section for low nox combustor and related process |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4984429A (en) * | 1986-11-25 | 1991-01-15 | General Electric Company | Impingement cooled liner for dry low NOx venturi combustor |
| DE19751299C2 (en) | 1997-11-19 | 1999-09-09 | Siemens Ag | Combustion chamber and method for steam cooling a combustion chamber |
| US6427446B1 (en) * | 2000-09-19 | 2002-08-06 | Power Systems Mfg., Llc | Low NOx emission combustion liner with circumferentially angled film cooling holes |
| US6430932B1 (en) * | 2001-07-19 | 2002-08-13 | Power Systems Mfg., Llc | Low NOx combustion liner with cooling air plenum recesses |
-
2001
- 2001-11-30 KR KR1020047008187A patent/KR100831772B1/en not_active IP Right Cessation
- 2001-11-30 CN CNB018239404A patent/CN100368664C/en not_active Expired - Fee Related
- 2001-11-30 BR BRPI0117192-5A patent/BR0117192B1/en not_active IP Right Cessation
- 2001-11-30 MX MXPA04005182A patent/MXPA04005182A/en active IP Right Grant
- 2001-11-30 AU AU2002219991A patent/AU2002219991A1/en not_active Abandoned
- 2001-11-30 EP EP01275164A patent/EP1461520A4/en not_active Withdrawn
- 2001-11-30 JP JP2004501791A patent/JP4121998B2/en not_active Expired - Fee Related
- 2001-11-30 CA CA002468646A patent/CA2468646C/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4982570A (en) * | 1986-11-25 | 1991-01-08 | General Electric Company | Premixed pilot nozzle for dry low Nox combustor |
| US5127221A (en) * | 1990-05-03 | 1992-07-07 | General Electric Company | Transpiration cooled throat section for low nox combustor and related process |
Also Published As
| Publication number | Publication date |
|---|---|
| AU2002219991A1 (en) | 2003-11-17 |
| BR0117192B1 (en) | 2010-12-14 |
| EP1461520A1 (en) | 2004-09-29 |
| CN1582365A (en) | 2005-02-16 |
| CA2468646A1 (en) | 2003-11-13 |
| KR20040058351A (en) | 2004-07-03 |
| JP2005520120A (en) | 2005-07-07 |
| EP1461520A4 (en) | 2010-04-14 |
| MXPA04005182A (en) | 2005-02-17 |
| CA2468646C (en) | 2009-09-29 |
| KR100831772B1 (en) | 2008-05-27 |
| BR0117192A (en) | 2004-11-09 |
| JP4121998B2 (en) | 2008-07-23 |
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