CN1779328A - Trapped vortex combustor cavity manifold for gas turbine engine - Google Patents
Trapped vortex combustor cavity manifold for gas turbine engine Download PDFInfo
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- CN1779328A CN1779328A CN200510087541.3A CN200510087541A CN1779328A CN 1779328 A CN1779328 A CN 1779328A CN 200510087541 A CN200510087541 A CN 200510087541A CN 1779328 A CN1779328 A CN 1779328A
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 134
- 239000000203 mixture Substances 0.000 claims abstract description 99
- 239000000446 fuel Substances 0.000 claims abstract description 87
- 238000000034 method Methods 0.000 claims abstract description 38
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- 230000035939 shock Effects 0.000 claims description 6
- 239000012530 fluid Substances 0.000 claims description 5
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- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 39
- 238000002156 mixing Methods 0.000 description 17
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- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 4
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 4
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 4
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- 238000013459 approach Methods 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
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Classifications
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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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
In accordance with one embodiment, the present technique provides a combustor assembly (34) for use in a gas-turbine device. The combustor assembly (34) includes a first combustion zone (66) and a second combustion zone (46). The combustor assembly (34) further includes a first premix chamber (38) configured to receive a fuel (24) and air (58) to facilitate a first fuel-air mixture (62) having a first fuel-to-air ratio, wherein the first premix chamber (38) is fluidiclly coupled to the combustion chamber (42) at the first combustion zone (66). The combustor assembly also includes a second premix chamber (40) configured to receive a fuel (24) and air (60) to facilitate a second fuel-air mixture (72) having a second fuel-to-air ratio, wherein the second premix chamber (40) is fluidiclly coupled to the combustion chamber (42) at the second combustion zone (46), wherein the second combustion zone (46) is radially outboard of the first combustion zone (66).
Description
Statement about the research and development of federation patronage
The present invention finishes under government supports, the contract number that Ministry of Energy authorizes is DE-FC2601NT41020.Government has certain right for the present invention.
Technical field
The present invention relates to substantially about burner, for example the fuel charge of gas turbine device and burning.
Background technology
In traditional gas turbine device, air sucks back and fuel mix from environment, is lighted then to produce burning gases, and these burning gases for example can be used for the driven machine element or produce power.Traditional gas turbine device generally includes three main systems: compressor, burner and turbine.Compressor supplies to burner with air pressurized and with it.Burner can be configured to the multiple tank burner or be configured to annular, directly carries out fluid with turbine and is communicated with.Compressed air and fuel mix to be incorporated in the burner and burn, and the burning gases that burning generates start turbine, for example produce power or driven machine element.That is to say that burning gases flow through turbine and start this turbine, turbine then driving shaft proposes a few to drive compressor and to produce outputting power to drive engine or to be used to aircraft that power is provided.
Common cycle of operation of gas-turbine unit is long and according to the restriction of rules, from problem deserving of attention of toxic emission of burning gases.For example in combustion process, nitrogen and oxygen chemical combination produce nitrogen oxide (NOx), and the discharging of NOx often is subjected to the restriction of rules and emission behaviour is undesirable usually.Traditionally, gas turbine unit is by reducing the discharge capacity that fuel-air recently reduces NOx, and these devices often are known as thin device.Thin device has reduced the ignition temperature in the combustion chamber and has reduced the discharge capacity of the NOx that produces in the burning thus.Unfortunately, for example traditional lean burn device is easy to cause combustion instability, causes fuel-air mixture to change, and is easy to also cause that efficient reduces, and causes the increase of carbon monoxide (CO) discharge capacity.
Another kind of reduction peak temperature commonly used is to spray into water or steam in burner with the method that reduces the NOx discharge capacity.But spray into water or steam is a kind of relatively costly technology, and this technology also will cause undesirable side effect, promptly hinders the after-flame of carbon monoxide (CO).In addition, satisfying many areas to aspect the requiring of pollutant utmost point low emission amount, the method ability that sprays into water or steam is limited.
The method that another kind is used to reduce the NOx discharge capacity is that fuel is supplied with in classification in burner.This method has reduced the time under the maximum temperature, makes burner tip thinner.Equally, relevant with very thin premixed problem may be restricted.Classification is sent into fuel and is restricted with the trend that reaches sufficient burning.
Therefore need provide the combustion technology that reduces the NOx discharge capacity.
Summary of the invention
Concise and to the point says, is provided for the burner assembly of gas turbine unit according to the present technique of an embodiment.This burner assembly comprises first combustion zone and second combustion zone.This burner assembly further comprises first premixing cavity, this first premixing cavity is configured to receive fuel and air, have first fuel-air ratio to help first fuel-air mixture, wherein this first premixing cavity carries out fluid in first combustion zone and combustion chamber and is connected.Burner assembly also comprises second premixing cavity, this second premixing cavity is configured to receive fuel and air, has second fuel-air ratio to help second fuel-air mixture, wherein second premixing cavity carries out fluid in second combustion zone and combustion chamber and is connected, and wherein second combustion zone is at the radial outside of first combustion zone.
According on the other hand, present technique provides the exemplary method of supplying with burning gases for gas turbine unit.This method is included as first premixing cavity of burner assembly and supplies with fuel and compressed air, first fuel-air mixture that has first fuel-air ratio with generation.This method comprises first combustion zone that first fuel-air mixture is supplied to the combustion chamber of burner assembly.This method also is included as second premixing cavity of burner assembly and supplies with fuel and compressed air, second fuel-air mixture that has second fuel-air ratio with generation.This method further comprises second combustion zone that second fuel-air mixture is supplied to the combustion chamber of burner assembly, in second combustion zone, to produce the eddy current of second fuel-air mixture, wherein, second combustion zone is arranged in the first combustion zone radial outside.
Description of drawings
When the detailed explanation below reading in conjunction with the accompanying drawings, these and other feature, aspect and the advantage that can better understand the present invention, wherein, and in different figure, the identical identical Reference numeral of part employing, wherein:
Fig. 1 is the skeleton diagram according to the gas turbine unit of the exemplary embodiment of present technique;
Fig. 2 is the part summary sectional view of single-stage trapped vortex combustor (the trapped vortex combustor) assembly according to the exemplary embodiment of present technique;
Fig. 3 is the part summary sectional view according to the second entrapment vortex combustor assembly of the exemplary embodiment of present technique;
Fig. 4 is along the front view of the end plate of the trapped vortex combustion chamber, the second level of 4-4 line among Fig. 3;
Fig. 5 is used for describing the flow chart of setting up the example process of thin and stable fuel according to the single stage burner assembly burning present technique aspect, that be combustion gas turbine; And
Fig. 6 is used for describing the flow chart of setting up the example process of thin and stable fuel according to the two stage burner assembly burning present technique aspect, that be combustion gas turbine.
The specific embodiment
At first, for the term in following argumentation and the appended claims " or " definition mean inclusion relation " or ".That is to say term " or " do not mean and distinguish two and repel replacement schemes mutually.More appropriate says, when term " or " when being used for two conjunctions between the element, being defined as and comprising an element self, another element self and two combination of elements and arrangement.For example discuss or narration uses term " A " or " B " to comprise for one: " A " self, " B " self and any combination of forming by " A " " B ", for example " AB " and/or " B/A ".
Present technique is generally used for the burning of gas turbine unit.Gas turbine unit serves many purposes, and its exemplary embodiment will be discussed hereinafter, only lifts several examples herein, as commercial aircraft and power plant.Usually, the operation principle of gas turbine unit is to light liquid or gaseous fuel in the combustion zone, only lifts several examples herein, as propane, natural gas, synthesis gas or kerosene, produces burning gases, and these burning gases are used to start turbine.
With reference now to accompanying drawing,, at first with reference to figure 1, among Fig. 1 the description of summary according to the embodiment of the exemplary gas turbine unit 10 of present technique.It should be noted that following argumentation relates to exemplary embodiment, and the appended claims are not limited to the embodiment that discusses herein.Gas turbine unit 10 comprises shell 12, and it is used to protect the internal part different with fixing gas turbine unit 10.In addition, following will the argumentation, shell 12 also provides the structure with respect to gas turbine unit 10 steering currents.
For producing air-flow, exemplary gas turbine unit 10 comprises compressor 14.Be in operation, compressor 14 sucks air 16 from the atmosphere of gas turbine unit 10 peripheries, force air 16 to flow to downstream direction then in device.Compressor has improved the pressure of air thus.In other words, the air 16 in the compressor 14 compression environment improves its pressure, like this to produce compressed air 18 and air-flow.Compressor 14 hereinafter will be discussed as the compressed air source of whole device, particularly burner.For example compressor 14 can improve a factor 30 with the pressure of air 16, even higher.
Compressed air 18 is imported into the device downstream and enters a plurality of burner assemblies 20 (being burner pot), and these burner assemblies are around longitudinal axis 22 concentric arrangement of gas turbine unit 10.As shown in the figure, burner assembly 20 has cylinder form basically, yet also it is contemplated that to have other shape.As hereinafter discussing, burner assembly 20 reception compressed air 18 and fuel 24 are so that form fuel-air mixture.Burner assembly 20 fire fuel-air mixture is to produce exhaust or burning gases 26, combustion gases drive turbine 28 then.In exemplary device, be that a plurality of burners 20 are supplied with fuel 24 by fuels sources 30.For example, fuels sources 30 is fuel manifolds, and it imports different burner assemblies with fuel.Fuels sources 30 (being fuel manifold) is subjected to fuel-control unit 32 controls.In exemplary embodiment, for example use valve system to control respectively fuel 24 is carried in the different parts of burner assembly 20.Therefore, the fuel of aequum can be fed in the different parts of burner assembly 20 in separate mode in the required time.
After forming, burning gases 26 flow through turbine 28 in a plurality of burner assemblies 20, and burning gases air stream drives turbine 28.Advantageously, the rotation of turbine 28 produces power, to cause the generator amature rotation, for example can produce electric power.Selectable, also can make the rotation generation power of turbine 28 come the driven machine element.
Fig. 2 is the part summary sectional view according to the single-stage trapped vortex combustor assembly 34 of the exemplary embodiment of present technique.More definite say, Fig. 2 has provided the burner pot of one of burner assembly 20 that is similar among Fig. 1 to be discussed or the detail section of burner assembly 34.Continue above-mentioned argumentation, fuels sources 30 and fuel-control unit 32 import to fuel 24 the different distributor gears or the plenum chamber of burner assembly.Fuel 24 can be a kind of in the multiple possible fuel, and for example propane, natural gas, hydrogen or synthesis gas also can comprise dilution, for example nitrogen, steam or carbon dioxide (CO2).Can certainly imagine the fuel of other type.In exemplary assembly, fuel 24 is fed into the diffuser casing 36 of burner assembly 34, elementary premixing cavity (i.e. first premixing cavity 38) and secondary premixing cavity (promptly second mixing chamber 40) again.These zones are that suitable fuel or fuel-air mixture are supplied with in combustion chamber 42 then, hereinafter will further discuss.
Together with other approach, fuel 24 can be fed into combustion chamber 42 through diffuser casing 36.Enter the secondary conbustion zone or second combustion zone 46 of combustion chamber 42 through a plurality of slits 48 from the fuel 24 of a plurality of inlet tubes 44 of diffuser casing 36.Advantageously, carrying diffused fuel 24 to be considered to by a plurality of slits 48 can be so that minimizes with respect to the thermal gradient on the surface that limits combustion chamber 42.As hereinafter will further discussing, make that from the fuel 24 of diffuser casing 36 fuel-air mixture abundance degree increases in the combustion chamber 42, its prerequisite is that this fuel-air mixture abundance degree is required and/or conditions permit.
In exemplary burner assembly 34, some in the fuel 24 of introducing are inflated before entering combustion chamber 42.For example fuel 24 is advanced by a plurality of inlet tubes 50 of elementary premixing cavity 38.This is inflated to occurring in first pre-mixing apparatus 52 of small part.As hereinafter will further discussing, pre-mixing apparatus 52 mixes air and fuel 24 to produce fuel-air mixture.For to fuel 24 inflations, advance through airflow chamber 56 by the compressed air that compressor 14 (see figure 1)s produce, be divided into two parts then, i.e. the first air-flow part 58 and the second air-flow part 60.The compressed-air actuated first air-flow part 58 enters elementary premixing cavity 38.Pre-mixing apparatus 52 promotes the inflation of fuel 24; In other words, pre-mixing apparatus 52 makes fuel 24 mix with this first air-flow part 58, has the primary fuel-air mixture or first fuel air mixture 62 of first fuel-air ratio with generation.In case after mixing, the mobile drive primary fuel-air mixture 62 of the first air-flow part 58 enters into combustion chamber 42 then towards a plurality of slits 64.Exactly, a plurality of slits 64 are positioned at towards the combustion chamber 42 center, for supplying with in the primary combustion zone or first combustion zone 66 of the combustion chamber 42 that also is positioned at 42 centers towards the combustion chamber.In exemplary embodiment, are thin relatively mixtures from the fuel-air mixture of elementary premixing cavity 38.
When second fuel-air mixture 72 is directed to the combustion chamber, particularly during secondary conbustion zone 46, this second fuel-air mixture 72 will be advanced in the mode of eddy current.In exemplary burner assembly, the mixture that is imported into (i.e. second fuel-air mixture 72) is limited in the secondary conbustion zone 46 of U-shaped, and this U-shaped shape induces eddy current 76.For example, axially advance from 74 fuel-air mixtures 72 that import that enter the mouth and to pass secondary conbustion zone 46 and collide on the sidewall on opposite, cause second fuel-air mixture 72 to inlet 74 negative line feeds.When more fuel-air mixture 72 from entering the mouth 74 when importing, this process repeats to take place, then eddy current 76 is held.Advantageously, exemplary assembly comprises slit 78, and it promotes to produce eddy current at secondary conbustion zone 46.In addition, as hereinafter will further discussing, can raise by importing fuel 24 by the fuel-air ratio of the fuel-air mixture of vortes interference by diffuser casing 36 and its corresponding inlet 44.
In exemplary burner assembly 34, premixing cavity 38,40 and diffuser casing 36 42 are separated from the combustion chamber by end board assembly 80.End board assembly 80 comprises first dish 82, and this first dish 82 is arranged between combustion chamber 42 and elementary premixing cavity 38, diffuser casing 36 and the secondary premixing cavity 40, and end board assembly 80 also comprises second dish 84, and it is around first dish 82.In exemplary embodiment, first dish is different each other with the material of second dish, adopts the material that is suitable for different running environment most, hereinafter will further discuss.For example in exemplary burner, the structure of first dish 82 is firmer, to adapt to the higher combustion temperature in the combustion chamber.
Be in operation, particularly when starting gas turbine unit, fuel 24 imported to the secondary conbustion zone 46 of combustion chamber 42 by diffuser casing 36, and by being installed in first igniter, 86 igniting on the chamber wall 88.Alternately, in certain embodiments, burner assembly can comprise that flame tube interconnector is to replace the igniter in each burner assembly.Flame tube interconnector is the pipe that the flame that produces after the fire fuel can be delivered to another burner from a burner assembly.Under any circumstance fuel is all lighted by incendiary source.Then, secondary fuel-air mixture 72 is directed to secondary conbustion zone 46.As mentioned above, the U-shaped shape place of secondary conbustion zone 46 makes the fuel-air mixture that is in secondary conbustion zone 46 inside produce eddy current 76.Advantageously, this eddy current promotes to mix from the fuel 24 of diffuser casing 36 and secondary fuel-air mixture 72, and to produce flame and combustion product, this combustion product may comprise unburned fuel and fuel-air mixture.But it should be noted that importing is then optional from the fuel 24 of diffuser casing 36.Under any circumstance, igniter 86 (or incendiary source) is lighted the fuel that is subjected to vortes interference in secondary conbustion zone 46, discusses as mentioned.Believe that in combustion chamber 42, the fuel-air mixture of lighting produces flame and combustion product 90, this flame and combustion product propagate into primary combustion zone 66 and light primary fuel-air mixture 62, and this primary fuel-air mixture is than lean mixtures.Flame 90 can be used as the guiding of the fuel-air mixture in the primary combustion zone 66.This flame is considered to make primary fuel-air mixture to form more stable burning, thereby flame can make burner assembly carry out thin and stable operation, thereby for example is reduced in the discharge capacity of the NOx that produces in the burning.In addition, combustion product 90 enters primary combustion zone and influence fuel-air mixture herein.
Advantageously, it is controlled that fuel 24 flows to diffuser casing 36, elementary premixed manifold 38 and secondary premixed manifold 40, to change quality that needs fuel-air mixture and the quantity under the specific operating position.For example, when gas turbine unit started, fuel 24 was fed into combustion chamber 42 and igniting by diffuser casing 36.Little by little, secondary fuel-air mixture 72 is introduced into and mixes with fuel 24 in the combustion chamber from secondary premixing cavity 40.Owing to light the dense fuel-air mixture 72 that flame ignition that the fuel 24 supplied with by diffuser casing 36 produces enters by secondary premixing cavity 40.In case stable, the fuel of supplying with by diffuser casing 36 24 will reduce gradually, and the stream of the fuel-air mixture 72 by secondary premixing cavity 40 will increase gradually.
Similarly, thin fuel-air mixture helps reducing the discharge capacity of NOx.Therefore unthickened fuel-the air mixture 62 of elementary premixing cavity 38 is incorporated into combustion chamber 42 also by the flame ignition that produces from secondary conbustion zone 46.By the control quality of fuel, can realize that different standards makes gas turbine unit effectively move.Burning (at secondary and primary combustion zone) in the combustion chamber 42 produces first burning gases 92, and burning gases 92 flow to turbine.Chamber wall 96 and a plurality of slits 94 of coiling on 100 promote that air-flow enters combustion chamber 42, help to reduce the discharge capacity of NOx thus.In addition, chamber wall 88 and 96 comprises shock ply 102.This shock ply 102 has a plurality of holes, and these holes help the compressed air stream against the exterior combustion chamber wall, and it helps the cooling combustion locular wall again.
Fig. 3 is the part summary sectional view according to the second entrapment vortex combustor assembly 104 of the exemplary embodiment of present technique.Second entrapment vortex combustor assembly 104 comprises the first order trapped vortex combustor assembly 34 among Fig. 2, and it is connected on the second level trapped vortex combustor assembly 106.Second level trapped vortex combustor assembly 106 comprises combustion gas chamber 108, the 3rd premixing cavity 110 and combustion chamber, downstream 112.Advantageously, the position of second level trapped vortex combustor assembly is nearer relatively apart from turbine inlet, so that the improvement that the NOx discharge capacity reduces.
First burning gases 92 from first order trapped vortex combustor assembly 34 are propagated to second level trapped vortex combustor assembly 106.The opening 114 that these burning gases 92 are flowed through on the end plate 116 enters combustion chamber, downstream 112.
As mentioned above, second level burner assembly 106 also comprises the 3rd premixing cavity 110.Fuels sources 30 and fuel-control unit 32 are that the inlet tube 120 of the 3rd premixing cavity 110 is supplied with fuel 24.Compressed air 122 air chamber 124 of flowing through enters the 3rd premixing cavity 110.As mentioned above, the 3rd pre-mixing apparatus 128 helps fuel 24 to mix the 3rd fuel-air mixture 130 that has the 3rd fuel-air ratio with generation with compressed air 122.Then, this fuel-air mixture 130 is fed into the 3rd combustion zone 132 of combustion chamber 112 by a plurality of slits 134.
Be in operation, be similar to first-stage burning device assembly, fuel-air mixture 130 enters the 3rd combustion zone 132.Be connected secondary igniter 136 (the being incendiary source) fire fuel-air mixture 130 in the combustion zone 132 of combustion chamber, the second level 112 on the chamber wall 137.As mentioned above, incendiary source can comprise igniter or flame tube interconnector.Lighting of fuel-air mixture 130 produces burning gases 138.As shown in Figure 2, the U-shaped shape of combustion zone 132 promotes burning gases 138 to produce eddy current 140.This eddy current helps the mixing of first burning gases 92 in the combustion chamber 112 of burning gases 138 and second level burner assembly again, to produce second burning gases 142.As mentioned above, a plurality of slits 144 on chamber wall 146 and the dish 150 help air-flow, and this air-flow reduces the discharging of NOx again. Chamber wall 137 and 146 also provides shock ply 152.As mentioned above, shock ply 152 helps to form air draught along the chamber wall outer surface, and this air draught helps the cooling of chamber wall again.The progression of burner assembly can be not limited to two-stage, and in certain embodiments, burner assembly can comprise required multistage progression.
Fig. 4 is the front view of the end plate 116 of second level trapped vortex combustion chamber among Fig. 3.End plate 116 comprises opening 114, freely flows to the combustion chamber 112 of second level burner assembly 106 to help first combustion gas mixt 92.Just as one of ordinary skill in the knowledge, higher relatively from the temperature of the burning gases 92 of first-stage burning chamber 42, and end plate 116 needs to adapt to these burning gases 92, to reduce the possibility of damaging.Therefore opening 114 is carried out following design, be that it helps burning gases 92 freely to flow to the combustion chamber 112 of second level burner assembly 106, and help mixing of the flame that produces because of fire fuel-air mixture 130 and burning gases 138 and first burning gases 92 simultaneously.In fact, exemplary end plate comprises finger piece 117, and it partly helps the mixing of burning gases 92 in flame and combustion product 138 and the combustion chamber 112.As shown in the figure, these finger pieces 117 to the inner surface that curls up by end plate 116 of small part limits.
Get in touch Fig. 2 as seen, Fig. 5 has described the flow chart in example process aspect present technique, that set up thin and stable fuel-air mixture for burning in the single stage burner assembly of combustion gas turbine.This process comprises through diffuser casing 36 fuel 24 is supplied to combustion chamber 42, to start gas turbine unit, shown in step 154.Igniter 86 fire fuel 24 are to produce combustion product 92, shown in step 156.Then, fuel-air mixture 72 is fed into combustion chamber 42 as follows, promptly produces eddy current 76 in combustion chamber 42.Eddy current 76 helps mixing of fuel-air mixture 72 and fuel 24 by diffuser casing 36, to produce flame and combustion product 90, shown in step 158.Flow from the fuel-air mixture 72 of secondary premixing cavity increases gradually, and reduces gradually from the flow of the fuel 24 of diffuser casing 36, shown in step 160.This process further comprises primary fuel-air mixture 62 is supplied to combustion chamber 42 by elementary premixing cavity 38, shown in step 162.As mentioned above, the eddy current 76 of the flame of secondary conbustion zone and combustion product 90 also helps lighting primary fuel-air mixture 62 in primary combustion zone 66, to produce burning gases 92, shown in step 164.
Get in touch Fig. 3 as seen, Fig. 6 has described the flow chart in example process aspect present technique, that set up thin and stable fuel-air mixture for burning in the two stage burner assembly of combustion gas turbine.This process is included in the combustion chamber 42 of first-stage burning device assembly 34 and lights unthickened fuel-air mixture 62, to produce first burning gases 92.This process further comprises the combustion chamber 112 that the burning gases 92 from the combustion chamber of first-stage burning device assembly 34 is supplied to second level burner assembly 106, shown in step 166.Further, the fuel-air mixture 130 that produces in the premixing cavity 110 of second level burner assembly 106 is fed into combustion chamber 112 as follows, and promptly 112 inside produce eddy current 140 in the combustion chamber, shown in step 168.The fuel-air mixture 130 of 112 inside, secondary igniter ignition combustion chambers 136 is to produce flame and burning gases 138, shown in step 170.Eddy current 140 helps mixing of burning gases 138 and first burning gases 92, to produce second burning gases 142, shown in step 172.Then the burning gases 142 from the combustion chamber 112 of second level burner assembly 106 are supplied to turbine, to start this turbine, shown in step 174.
Here only discuss and illustrate some feature of the present invention, those skilled in the art can understand many modifications and changes.Therefore it will be appreciated that and be intended to cover all by subsidiary claims this type of is positioned at the modifications and changes of connotation of the present invention.
The tabulation of Yuan spare:
10 gas turbine system layouts
12 shells (Zhu body-gas turbine system)
14 Ya contracting machines
16 atmospheric airs
18 Ya contracting air
20 burner assemblies
22 gas turbine unit longitudinal axis
24 fuel
26 burning gases
28 turbine assemblies
30 fuel-control units
32 turbine blades
34 single-stage trapped vortex combustor assemblies
36 diffuser casings
38 elementary premixing cavitys
40 level premixing cavitys
42 combustion chambers
44 fuel inlet pipe-diffuser casings
The 46 second combustion chambers-first order
48 slits-diffuser casing
50 fuel inlet pipes-elementary premixing cavity
52 first pre-mixing apparatus
56 air chambers
58 compressed air are to elementary premixing cavity
60 compressed air are to secondary premixing cavity
62 primary fuels-air mixture
64 slits-elementary premixing cavity
66 primary combustion zones-first district
68 fuel inlet pipes-secondary premixing cavity
70 second pre-mixing apparatus
72 secondary fuel-air mixture
74 slits-secondary premixing cavity
76 secondary fuel-air mixture eddy current
78 slits
80 end plates-combustion chamber
82 first plates-end plate
84 second plates-end plate
86 first igniters
88 chamber walls
90 combustion products-second combustion zone
92 first burning gases
94 cooling slits
96 chamber walls
100 inner discs
102 alluviation cooling layers
104 second entrapment vortex combustor assemblies
106 second level burner assemblies
108 combustion gas chamber
110 the 3rd premixing cavitys-second level
112 combustion chambers-the second level
114 openings-end plate
116 end plates-combustion chamber, the second level
117 finger pieces-end plate
120 fuel inlet pipe-Di, three premixing cavitys, the second level
122 compressed air are to second level burner assembly
124 air chambers
128 the 3rd pre-mixing apparatus
130 the 3rd fuel-air mixtures
132 the 3rd combustion zones-combustion chamber, the second level
134 slits-the 3rd premixing cavity
136 secondary igniters
137 chamber walls
138 burning gases-the 3rd fuel-air mixture
140 burning gases eddy current
141 slits
142 second burning gases-second level burner assembly
144 cooling slits
146 chamber walls
150 inner discs
152 shock plies-second level burner assembly
154 supply to combustion chamber (first order) with fuel by diffuser casing
156 igniter fuels
158 supply to combustion chamber (first order) with secondary fuel-air mixture
160 increase secondary fuel-air mixture flow and reduce current fuel flow rate by diffuser casing
162 supply to combustion chamber (first order) with primary fuel-air mixture
164 light lean mixtures
166 supply to second level burner assembly with first burning gases from first-stage burning device assembly
168 supply to combustion chamber (second level) with the 3rd fuel-air mixture
170 light the 3rd fuel-air mixture to produce burning gases
172 will mix from the burning gases and first burning gases of the 3rd fuel-air mixture, to produce second burning gases
174 supply to turbine with burning gases
Claims (10)
1. a burner assembly that uses with gas turbine unit (34), this assembly comprises:
Combustion chamber (42) with first combustion zone (66) and second combustion zone (46);
Be configured to receive fuel (24) and first premixing cavity (38) of air (58) to help first fuel-air mixture (62) to have first fuel-air ratio, wherein first premixing cavity (38) carries out fluid with combustion chamber (42) in first combustion zone (66) and is connected; And
Be configured to receive fuel (24) and air (60) and have second premixing cavity (40) of second fuel-air ratio to help second fuel-air mixture (72), wherein second premixing cavity (40) carries out fluid with combustion chamber (42) in second combustion zone (46) and is connected, and wherein second combustion zone (46) are at first combustion zone (66) radial outside.
2. burner assembly as claimed in claim 1, wherein second combustion zone (46) are configured to produce the eddy current (76) of second fuel-air mixture (72).
3. burner assembly as claimed in claim 1 further comprises the diffuser casing (36) that is configured to receive fuel (24) and fuel (24) is supplied to secondary conbustion zone (46).
4. burner assembly as claimed in claim 1 comprises being arranged near second combustion zone (46) and being configured to light the incendiary source (86) of second fuel-air mixture (72).
5. burner assembly as claimed in claim 1, wherein the wall of combustion chamber (96) comprises a plurality of slits (94), to help air flow combustion chamber (42).
6. burner assembly as claimed in claim 1 further comprises the shock ply (102) that is configured to compressed air (42) outer surface water conservancy diversion along the combustion chamber.
7. method that is used to gas turbine unit that burning gases (92) are provided, this method comprises:
Fuel (24) and compressed air (58) are supplied to first premixing cavity (38) of burner assembly (34);
In first premixing cavity (38), produce first fuel-air mixture (62) with first fuel-air ratio by supplying with the fuel (24) and the compressed air (58) that come;
First fuel-air mixture (62) is supplied to first combustion zone (66) of the combustion chamber (42) of burner assembly (34);
Fuel (24) and compressed air (60) are supplied to second premixing cavity (40) of burner assembly (34);
In second premixing cavity (40), produce second fuel-air mixture (72) with second fuel-air ratio by supplying with the fuel (24) and the compressed air (60) that come;
Second fuel-air mixture (72) is supplied to second combustion zone (46) of the combustion chamber (42) of burner assembly (34), and wherein second combustion zone (46) are arranged in first combustion zone (66) radial outside; And
In second combustion zone (46), produce the eddy current (76) of second fuel-air mixture (72).
8. method as claimed in claim 7 further comprises second combustion zone (46) that fuel (24) is provided to the diffuser casing (36) of burner assembly (34) and fuel (24) is supplied to the combustion chamber (42) of burner assembly (34).
9. method as claimed in claim 8 further comprises fire fuel (24) and second fuel-air mixture (72), to produce flame and burning gases (90).
10. method as claimed in claim 8 further comprises with flame (90) and lights first fuel-air mixture (62), to produce first burning gases (92).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/994833 | 2004-11-22 | ||
| US10/994,833 US20060107667A1 (en) | 2004-11-22 | 2004-11-22 | Trapped vortex combustor cavity manifold for gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1779328A true CN1779328A (en) | 2006-05-31 |
Family
ID=35562442
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200510087541.3A Pending CN1779328A (en) | 2004-11-22 | 2005-07-22 | Trapped vortex combustor cavity manifold for gas turbine engine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20060107667A1 (en) |
| EP (1) | EP1659338A1 (en) |
| JP (1) | JP2006145194A (en) |
| CN (1) | CN1779328A (en) |
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| CN102087026A (en) * | 2009-12-08 | 2011-06-08 | 通用电气公司 | Fuel injection in secondary fuel nozzle |
| CN103244968A (en) * | 2012-02-07 | 2013-08-14 | 通用电气公司 | Combustor assembly with trapped vortex cavity |
| CN102713203B (en) * | 2009-09-13 | 2015-07-22 | 贫焰公司 | Method of fuel staging in combustion apparatus |
| CN106062481A (en) * | 2013-11-25 | 2016-10-26 | 特-可再生能源企业有限公司 | Apparatus for firing and combustion of syngas |
| CN115075945A (en) * | 2022-07-01 | 2022-09-20 | 星辰萌想科技(北京)有限公司 | Gas turbine using solid fuel |
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| US7603841B2 (en) * | 2001-07-23 | 2009-10-20 | Ramgen Power Systems, Llc | Vortex combustor for low NOx emissions when burning lean premixed high hydrogen content fuel |
| JP2007113888A (en) * | 2005-10-24 | 2007-05-10 | Kawasaki Heavy Ind Ltd | Combustor structure of gas turbine engine |
| US20070204624A1 (en) * | 2006-03-01 | 2007-09-06 | Smith Kenneth O | Fuel injector for a turbine engine |
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- 2004-11-22 US US10/994,833 patent/US20060107667A1/en not_active Abandoned
-
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- 2005-07-08 EP EP05254296A patent/EP1659338A1/en not_active Withdrawn
- 2005-07-21 JP JP2005210786A patent/JP2006145194A/en not_active Withdrawn
- 2005-07-22 CN CN200510087541.3A patent/CN1779328A/en active Pending
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Also Published As
| Publication number | Publication date |
|---|---|
| US20060107667A1 (en) | 2006-05-25 |
| EP1659338A1 (en) | 2006-05-24 |
| JP2006145194A (en) | 2006-06-08 |
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Open date: 20060531 |