CN113251439B - Double-stage co-rotating head device for dual-fuel gas turbine - Google Patents
Double-stage co-rotating head device for dual-fuel gas turbine Download PDFInfo
- Publication number
- CN113251439B CN113251439B CN202110705839.5A CN202110705839A CN113251439B CN 113251439 B CN113251439 B CN 113251439B CN 202110705839 A CN202110705839 A CN 202110705839A CN 113251439 B CN113251439 B CN 113251439B
- Authority
- CN
- China
- Prior art keywords
- fuel
- stage
- swirler
- dual
- gaseous
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
-
- 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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a two-stage co-rotating head device for a dual-fuel gas turbine, which comprises a two-stage axial co-rotating swirler, a fuel nozzle and a premixing section, wherein the fuel nozzle comprises a centrifugal nozzle and a spray rod; the front end of the premixing section is connected to the air outlet end of the two-stage axial co-rotating cyclone; the air inlet end of the spray rod is arranged outside the two-stage axial co-rotation cyclone, and the air outlet pipe of the spray rod penetrates through the two-stage axial co-rotation cyclone and extends to one side, close to the rear end, of the inside of the premixing section; the centrifugal nozzle is arranged at the air outlet end of the spray rod and used for inputting liquid duty fuel to the rear end of the premixing section through the centrifugal nozzle. The invention adopts an innovative structural form of multi-path multi-structure fuel supply to realize good fuel concentration distribution; the full-state efficient work is realized, the high-efficient low-emission combustion of a combustion chamber is ensured, and meanwhile, the consideration of other performances such as point flameout, backfire prevention, coking ablation prevention, carbon deposition prevention and the like is realized.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a two-stage co-rotating head device for a dual-fuel gas turbine.
Background
Gas turbine combustors that burn both gaseous and liquid fuels can be used, i.e., dual fuel combustors. Because it can give consideration to both fuel combustion, it has a wider application field than a single-fuel gas turbine.
The dual fuel combustor needs to have good performance in both liquid and gaseous fuel combustion. The combustor head assembly includes a swirler and a fuel nozzle, and as liquid and gaseous fuels need to be considered, the requirements for the same are as follows:
1. when liquid fuel is adopted, atomization and evaporation need to be considered, and the nozzle is required to have good atomization performance to ensure flameout and combustion efficiency;
2. when the gaseous fuel is adopted, the prevention and control problems of combustion oscillation need to be considered while the premixing effect is required to be considered to reduce the emission;
3. the liquid fuel needs to consider tempering resistance, coking and ablation resistance and carbon deposition resistance;
4. the swirler needs to be compatible with both gaseous fuel and liquid fuel, and needs to form reasonable fuel distribution when the gaseous fuel is combusted or the liquid fuel is combusted.
At present, the dual-fuel combustion chamber with mature type in China also adopts the traditional combustion mode mainly based on diffusion combustion, and the mode has good combustion stability and flameout performance. However, the emission requirement is increasingly strict at present, and particularly the emission requirement is high when gaseous fuel is combusted, and the combustion mode cannot meet the requirement because the temperature of a main combustion zone is high and thermal NOx is not easy to control.
In addition, due to the fact that the density difference between the liquid fuel and the gaseous fuel is large, penetration and distribution of the fuel need to be considered, and fine design of injection of different fuels needs to be considered, so that good flameout and stability performance can be kept under different fuels.
Disclosure of Invention
It is an object of the present invention to provide a dual stage co-rotating head assembly for a dual fuel gas turbine engine that solves the above-mentioned problems of the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
a dual stage co-rotating head apparatus for a dual fuel gas turbine, comprising a dual stage axial co-rotating swirler, a fuel nozzle and a premixing section, the fuel nozzle comprising a centrifugal nozzle and a spray bar; the front end of the premixing section is connected to the air outlet end of the two-stage axial co-rotation swirler and used for inputting air and gaseous main-stage fuel into the premixing section through the two-stage axial co-rotation swirler; the gas inlet end of the spray rod is arranged outside the two-stage axial co-rotation swirler, and the gas outlet pipe of the spray rod penetrates through the two-stage axial co-rotation swirler and extends to one side, close to the rear end, of the interior of the premixing section so as to input gaseous on-duty fuel to the rear end of the premixing section through the spray rod and input liquid main-stage fuel into the premixing section through the spray rod; the centrifugal nozzle is arranged at the air outlet end of the spray rod and used for inputting liquid duty fuel to the rear end of the premixing section through the centrifugal nozzle.
Further preferably, an inner ring blade channel and an outer ring blade channel are arranged in the double-stage axial co-rotating cyclone and are used for being externally input into the premixing section through the inner ring blade channel and the outer ring blade channel.
Preferably, the two-stage axial co-rotating swirler is internally provided with an outer ring swirler blade and an inner ring swirler blade, the outer ring swirler blade and the inner ring swirler blade are both hollow blades provided with inner cavities, the outer ring swirler blade and the inner ring swirler blade are respectively provided with a gaseous main-stage fuel inlet communicated with the outside of the two-stage axial co-rotating swirler and the respective inner cavities, the outer ring swirler blade is provided with a first gaseous main fuel hole communicated with the inner cavity thereof, and the inner ring swirler blade is provided with a second gaseous main fuel hole communicated with the inner cavity thereof, so that gaseous main-stage fuel is input into the premixing section through the first gaseous main fuel hole and the second gaseous main fuel hole.
More preferably, the blade twist angle of the outer ring swirler vanes is greater than 55 degrees, and the light transmittance between any two adjacent outer ring swirler vanes is greater than 15%; the blade rotating directions of all the blades of the outer ring swirler are the same rotating direction.
Still further preferably, the blade twist angle of the inner ring swirler vanes is greater than 55 °, and the light transmittance between any two adjacent inner ring swirler vanes is 0; the blade rotating directions of all the inner ring swirler blades are the same.
It is further preferred that the air inlet end of the lance is provided with a gaseous on-duty fuel inlet, the air outlet end of the lance is provided with a plurality of circumferential gaseous fuel injection holes arranged axially therealong, and the gaseous on-duty fuel inlet communicates with all of the circumferential gaseous fuel injection holes for diffusively introducing gaseous on-duty fuel to the aft end of the premixing section.
It is further preferable that the air inlet end of the spray rod is provided with a liquid main fuel inlet, the middle part of the spray rod is provided with a plurality of circumferential liquid fuel injection holes, and the liquid main fuel inlet is communicated with all the circumferential liquid fuel injection holes so as to obliquely input liquid main stage fuel into the premixing section through the circumferential liquid fuel injection holes.
Still further preferably, the air inlet end of the spray rod is provided with a liquid duty fuel inlet which is communicated with the centrifugal nozzle and used for inputting the liquid duty fuel into the premixing section after the liquid duty fuel is subjected to rotary atomization through the centrifugal nozzle.
Still further preferably, a tangential hole, a transition section, a swirl groove, a swirl chamber and a centrifugal nozzle which are sequentially communicated are arranged in the centrifugal nozzle, and the air inlet end of the tangential hole is communicated with the liquid on-duty fuel inlet.
More preferably, the premixing section comprises a converging wall section and an outlet throat section which are connected with each other, and one end of the converging wall section is connected with the air outlet end of the double-stage axial same-rotation swirler; and the outlet throat section is provided with circumferential cooling holes.
Has the advantages that:
(1) according to the scheme, through reasonable technical measures, the technical problems that the concentration fields of liquid and gaseous fuels of the dual-fuel gas turbine are difficult to be well distributed, the diffusion combustion emission of the gaseous fuel is difficult to realize, and stable combustion needs to be realized by matching the dual fuels with a swirler are solved, the good fuel concentration distribution can be realized in two fuel combustion working modes, the low NOx emission in a natural gas fuel combustion mode is realized, and the good ignition and flameout performance is realized in two fuel working modes.
(2) The scheme of the invention fully considers the fuel emission requirement by means of the mode of liquid fuel large-state lean premixed combustion small-state diffusion combustion and gaseous fuel large-state premixed small-state diffusion combustion, and well realizes the low-emission combustion of the two fuels.
(3) According to the scheme, through the two-stage axial co-rotating swirler, the torsion angle of the outer ring large blade is combined with the light transmission of the blade, and meanwhile, the throttling regulation mode of the channel outlet throat section is adopted, so that the high flow rate of the outlet section of the premixing section is realized while the sufficient swirl strength is ensured, the flame stability can be ensured, and the tempering spontaneous combustion can be prevented.
(4) According to the technical scheme, the advantages and disadvantages of two fuel supply modes, namely the centrifugal nozzle and the direct injection type spray hole, are fully considered, and the liquid fuel is supplied by adopting the centrifugal nozzle and the direct injection type spray hole, so that atomization and evaporation are guaranteed; the gaseous fuel is low in density, mixing mainly depends on momentum, and the direct injection type spray holes are adopted for supplying, so that efficient and stable operation under the condition of using two kinds of fuels is guaranteed to the greatest extent.
(5) According to the invention, through the injection form of the circumferential liquid fuel injection hole with the angle, the liquid fuel and the premixing section are well premixed and matched at the same time; according to the design, the proper momentum ratio is ensured, the phenomenon that fuel droplets collide the wall is avoided, and the anti-backfire, anti-coking ablation and anti-carbon deposition effects can be effectively achieved.
(6) According to the technical scheme, gaseous fuel enters the two-stage co-rotating head device, and combustion pulsation quantity can be adjusted by adjusting the fuel oil proportion of the diffusion fuel supply path, so that prevention and control of oscillatory combustion are realized.
(7) The small-state ignition and flameout of the invention ensures that the two different fuels have good ignition and flameout performance by the supply and combustion of the diffusion fuel, the supply of the gaseous and liquid diffusion fuels by setting reasonable characteristic dimensions and reasonably controlling the penetration and mixing of the fuels.
Drawings
FIG. 1 is a schematic perspective view of a dual stage co-rotating head assembly according to the present invention;
FIG. 2 is a cross-sectional view of a dual stage co-rotating head set of the present invention;
FIG. 3 is a schematic perspective view of a dual stage axial co-rotating swirler in accordance with the present invention;
FIG. 4 is a sectional view taken along line A-A of the dual stage axial co-rotating swirler of FIG. 3 in accordance with the present invention;
FIG. 5 is a sectional view taken along line B-B of the dual stage axial co-rotating swirler of FIG. 3 in accordance with the present invention;
FIG. 6 is a cross-sectional view taken along line C-C of the dual stage axial co-rotating swirler of FIG. 3 in accordance with the present invention;
FIG. 7 is a cross-sectional view of a fuel nozzle of the present invention;
FIG. 8 is a schematic perspective view of the premixing section in the present invention;
FIG. 9 is a cross-sectional view of the premixing section in the present invention;
FIG. 10 is a cross-sectional view of a centrifugal nozzle in accordance with the present invention;
FIG. 11 is a schematic perspective view of a spray bar according to the present invention;
fig. 12 is a cross-sectional view of a spray bar of the present invention.
In the figure: 1-two-stage axial co-rotating swirler; 11-inner ring vane passages; 12-outer ring blade channels; 13-outer ring swirler vanes; 14-inner ring swirler vanes; 15-gaseous primary fuel inlet; 131-a first gaseous main-fuel orifice; 141-a second gaseous main-fuel orifice; 2-a fuel nozzle; 21-a spray rod; 211-gaseous on duty fuel inlet; 212-circumferential gaseous fuel annulus; 213-circumferential gaseous fuel injection hole; 214-liquid main fuel inlet; 215-liquid main fuel annular channel; 216-circumferential liquid fuel injection holes; 217-liquid duty fuel inlet; 22-centrifugal nozzle; 221-tangential holes; 222-a transition section; 223-a swirling groove; 224-a swirl chamber; 225-centrifugal nozzle; 3-a premixing section; 31-a converging wall section; 32-an outlet throat section; 321-circumferential cooling holes.
Detailed Description
Example (b):
as shown in fig. 1-12, the present embodiment provides a dual stage co-rotating head assembly for a dual fuel gas turbine, comprising a dual stage axial co-rotating swirler 1, a fuel nozzle 2 and a premixing section 3, the fuel nozzle 2 comprising a centrifugal nozzle 22 and a spray bar 21; the front end of the premixing section 3 is connected to the air outlet end of the two-stage axial co-rotation swirler 1 and is used for inputting air and gaseous main-stage fuel into the premixing section 3 through the two-stage axial co-rotation swirler 1; the air inlet end of the spray rod 21 is arranged outside the two-stage axial co-rotation swirler 1, the air outlet pipe of the spray rod 21 penetrates through the two-stage axial co-rotation swirler 1 and extends to one side, close to the rear end, of the inside of the premixing section 3, so that gaseous on-duty fuel is input to the rear end of the premixing section 3 through the spray rod 21, and liquid main-stage fuel is input into the premixing section 3 through the spray rod 21; the centrifugal nozzle 22 is arranged at the air outlet end of the spray rod 21 and used for inputting liquid duty-grade fuel to the rear end of the premixing section 3 through the centrifugal nozzle 22, the working condition requirements of an actual combustion chamber are considered, and different working modes are adopted to realize full-state efficient work; the combustion chamber can realize the consideration of other performances such as flameout, tempering resistance, coking and ablation resistance, carbon deposition resistance and the like while ensuring the high-efficiency low-emission combustion of the combustion chamber.
In this embodiment, it is further described that the two-stage axial co-rotating swirler 1 is provided with an inner ring blade passage 11 and an outer ring blade passage 12, and the two-stage axial co-rotating swirler is composed of the inner ring blade passage 11 and the outer ring blade passage 12, and is used for being externally input into the premixing section 3 through the inner ring blade passage 11 and the outer ring blade passage 12.
In this embodiment, it is further described that the two-stage axial co-rotating swirler 1 is provided with outer ring swirler vanes 13 and inner ring swirler vanes 14, the outer ring swirler vanes 13 and the inner ring swirler vanes 14 are both hollow vanes provided with inner cavities, the outer ring swirler vanes 13 and the inner ring swirler vanes 14 are both provided with gaseous main stage fuel inlets 15 communicating the outside of the two-stage axial co-rotating swirler 1 and the respective inner cavities, the outer ring swirler vanes 13 are provided with first gaseous main fuel holes 131 communicating the inner cavities thereof, the inner ring swirler vanes 14 are provided with second gaseous main fuel holes 141 communicating the inner cavities thereof, and the gaseous main stage fuel is input into the premixing section 3 through the first gaseous main fuel holes 131 and the second gaseous main fuel holes 141. The inner ring blade channel 11 and the outer ring blade channel 12 on the two-stage axial same-direction swirler 1 are both hollow blades, namely, the inner ring swirler blades 14 combined into the inner ring blade channel 11 are hollow blades, the outer ring swirler blades 13 combined into the outer ring blade channel 12 are hollow blades, and gaseous main-stage fuel enters through the gaseous main-stage fuel inlet 15 and then is sprayed in through the first gaseous main-fuel hole 131 and the second gaseous main-fuel hole 141.
Further in this embodiment, the blade twist angle of the outer ring swirler vanes 13 is greater than 55 °, and the light transmittance between any two adjacent outer ring swirler vanes 13 is greater than 15%; the blade rotation direction of all the outer ring swirler blades 13 is the same direction of rotation. More specifically, the blade twist angle of the inner ring swirler vanes 14 is greater than 55 °, and the light transmittance between any two adjacent inner ring swirler vanes 14 is 0; the vane rotation direction of all the inner ring swirler vanes 14 is the same direction of rotation. The outer ring swirler vanes 13 adopt a structural form that the torsion angle of the large vane torsion angle vanes is larger than 55 degrees and the light transmittance of the vanes is larger than 15%, the inner ring swirler vanes 14 adopt a structural form that the torsion angle of the large vane torsion angle vanes is larger than 55 degrees and the light transmittance of the vanes is larger than 15%, the rotation directions of the vanes rotate in the same direction, a combined throttling form is formed with an outlet throat section 32 of the premixing section 3 mentioned below, and the swirl strength is controlled at a required level through the geometric characteristic parameter relationship of the three sections.
It is further illustrated in the present embodiment that the air inlet end of the spray bar 21 is provided with a gaseous on-duty fuel inlet 211, the air outlet end of the spray bar 21 is provided with a plurality of circumferential gaseous fuel injection holes 213 arranged along the axial direction thereof, and the gaseous on-duty fuel inlet 211 communicates with all the circumferential gaseous fuel injection holes 213 for diffusively inputting the gaseous on-duty fuel to the rear end of the premixing section 3. Gaseous on-duty fuel is introduced into the spray rod 21 through the gaseous on-duty fuel inlet 211, a circumferential gaseous fuel annular cavity 212 is arranged in the spray rod, the gaseous on-duty fuel inlet 211 and the circumferential gaseous fuel annular cavity 212 form an on-duty gaseous fuel passage, and the on-duty gaseous fuel is injected into air in the premixing section through the circumferential gaseous fuel injection hole 213.
In this embodiment, it is further described that the air inlet end of the spray rod 21 is provided with a liquid main fuel inlet 214, the middle portion of the spray rod 21 is provided with a plurality of circumferential liquid fuel injection holes 216, and the liquid main fuel inlet 214 communicates with all the circumferential liquid fuel injection holes 216 to obliquely input liquid main stage fuel into the premixing section 3 through the circumferential liquid fuel injection holes 216. Also on spray bar 21 is a liquid main fuel supply passage consisting of liquid main fuel inlet 214, a liquid main fuel annulus 215 disposed within the spray bar, liquid main fuel inlet 214, liquid main fuel annulus 215 and circumferential liquid fuel injection holes 216.
In this embodiment, the air inlet end of the spray rod 21 is provided with a liquid on-duty fuel inlet 217, and the liquid on-duty fuel inlet 217 is communicated with the centrifugal nozzle 22, so that the liquid on-duty fuel is rotationally atomized by the centrifugal nozzle 22 and then is fed into the premixing section 3.
In this embodiment, it is further described that a tangential hole 221, a transition section 222, a swirl groove 223, a swirl chamber 224 and a centrifugal nozzle 225 are arranged in the centrifugal nozzle 22 and are sequentially communicated, and an air inlet end of the tangential hole 221 is communicated with the liquid on-duty fuel inlet 217. The fuel nozzle 2 is composed of a spray rod 21 and a centrifugal nozzle 22. The centrifugal nozzle 22 forms a rotary atomization flow path of the liquid fuel on duty through the tangential hole 221, the transition section 222, the swirl groove 223, the swirl chamber 224 and the centrifugal nozzle 225.
It is further illustrated in this embodiment that the premixing section 3 includes a converging wall section 31 and an outlet throat section 32 connected to each other, and one end of the converging wall section 31 is connected to the outlet end of the two-stage axial co-rotating swirler 1; the outlet throat section 32 is provided with circumferential cooling holes 321. The premixing section 3 is positioned at the rear end of the double-stage axial co-rotating swirler 1 and consists of a convergent wall section 31 and an outlet throat section 32, and gaseous main-stage fuel, liquid main-stage fuel and head air of the double-stage co-rotating head device are mixed in high quality to ensure high-efficiency combustion performance. The premixing section exit throat section 32 is provided with circumferential cooling holes 321 for cooling the rear end wall face.
The working process of the invention is as follows: head air of the double-stage co-rotating head device enters the head device through the inner ring blade channel 11 and the outer ring blade channel 12 of the double-stage axial co-rotating swirler 1, when gaseous fuel works, gaseous main-stage fuel is sprayed through the first gaseous main fuel holes 131 in the outer ring swirler blades 13 and the second gaseous main fuel holes 141 in the inner ring swirler blades 14, and is mixed with the head air in the premixing section 3; gaseous class fuel enters through gaseous class fuel inlet 211 on fuel nozzle 2 and is injected diffusely into the aft end of the header assembly, i.e., the aft end of premix section 3, through circumferential gaseous class fuel injection holes 213 on fuel nozzle 2. When working with liquid fuel, the liquid main stage fuel enters through the liquid main stage fuel inlet 214 on the fuel nozzle 2, is obliquely injected into the premixing section 3 through the circumferential liquid fuel injection holes 216, and is mixed with head air in the premixing section 3; the liquid class fuel enters through the liquid class fuel inlet 217 on the fuel nozzle 2 and at the front end of the spray rod 21, flows into the transition section 222 through the tangential hole 221 on the centrifugal nozzle 22, then enters the swirl chamber 224 through the swirl groove 223 in a rotating mode, and finally is sprayed into the rear end of the head device in a diffusion mode through the rotating atomization of the centrifugal nozzle 225.
The double-stage co-rotating head device has the following four working modes:
1 gaseous Fuel Low State mode of operation
The method refers to a transition process of a combustion chamber working by using gaseous fuel from ignition working to small load, in the process, only the gaseous duty-stage fuel is supplied to a double-stage co-rotating head device, and the fuel and air are supplied by a diffusion combustion supply mode.
The principle of the gaseous fuel small-state working mode is as follows: at this time, the fuel supply amount is small, and since the density of the gaseous fuel is low, all the fuel is injected into the premixing section 3 through the circumferential gaseous fuel injection hole 213 in a direct injection hole angled manner, so that fuel distribution with high concentration is formed at the rear end of the two-stage co-rotating head device, and the stable operation of the combustion chamber in an ignition and small-state operation mode is ensured.
2 gaseous Fuel high State operating mode
The fuel is supplied by only gaseous main-grade fuel in the mode, the fuel concentration is uniformly distributed in a premixing mode, and the fuel can be kept at a lower oil-gas ratio to ensure the emission performance of the combustion chamber.
The principle of the gaseous fuel large-state working mode is as follows: all fuels are uniformly mixed in a premixing mode, so that the uniformity of premixed flame in the combustion chamber is ensured, the combustion of a main combustion zone of the combustion chamber under a proper equivalence ratio is ensured, the generation of NOx is effectively controlled, and the auxiliary combustion chamber realizes good pollution emission.
Liquid fuel low regime mode of operation
The method refers to a transition process from ignition operation to small load operation in which the combustor operates by using liquid fuel, and only the liquid fuel is supplied to the head device on duty, and the fuel and air are supplied by means of diffusion combustion supply.
The principle of the small-state working mode of the liquid fuel is as follows: all fuels are subjected to swirl atomization through the centrifugal nozzle, so that the diffusion model and air are mixed at the rear end of the double-stage co-rotating head device, the atomization mixing quality is guaranteed through high-pressure swirl atomization of the centrifugal nozzle, and the ignition and flameout performance of a combustion chamber is effectively guaranteed.
4 liquid fuel large state working mode
This means that the combustion chamber is operated with liquid fuel, and under heavy load conditions, in which mode the fuel is supplied mainly by liquid main fuel, and liquid value class fuel, which is also supplied, but with a relatively low proportion. The combustion of the combustion chamber is mainly dominated by premixed combustion, and the diffusion combustion of the liquid duty fuel only accounts for a small part.
The principle of the large-state working mode of the liquid fuel is as follows: most of fuel is supplied through the circumferential liquid fuel injection holes 216, the mixing performance of the fuel and combustion air is good through the angled injection, and meanwhile, the fuel is ensured not to touch the wall, so that the problems of tempering, coking ablation, carbon deposition and the like during combustion are avoided while the high-efficiency combustion is realized; a small portion of the fuel is fed through the centrifugal nozzle 22, which ensures flame stability by means of diffusion.
The invention has the following beneficial effects:
(1) according to the scheme, through reasonable technical measures, the technical problems that the concentration fields of liquid and gaseous fuels of the dual-fuel gas turbine are difficult to be well distributed, the diffusion combustion emission of the gaseous fuel is difficult to realize, and stable combustion needs to be realized by matching the dual fuels with a swirler are solved, the good fuel concentration distribution can be realized in two fuel combustion working modes, the low NOx emission in a natural gas fuel combustion mode is realized, and the good ignition and flameout performance is realized in two fuel working modes.
(2) The scheme of the invention fully considers the fuel emission requirement by means of the mode of liquid fuel large-state lean premixed combustion small-state diffusion combustion and gaseous fuel large-state premixed small-state diffusion combustion, and well realizes the low-emission combustion of the two fuels.
(3) According to the scheme, through the two-stage axial co-rotating swirler, the torsion angle of the outer ring large blade is combined with the light transmission of the blade, and meanwhile, the throttling regulation mode of the channel outlet throat section is adopted, so that the high flow rate of the outlet section of the premixing section is realized while the sufficient swirl strength is ensured, the flame stability can be ensured, and the tempering spontaneous combustion can be prevented.
(4) According to the technical scheme, the advantages and disadvantages of two fuel supply modes, namely the centrifugal nozzle and the direct injection type spray hole, are fully considered, and the liquid fuel is supplied by adopting the centrifugal nozzle and the direct injection type spray hole, so that atomization and evaporation are guaranteed; the gaseous fuel is low in density, mixing mainly depends on momentum, and the direct injection type spray holes are adopted for supplying, so that efficient and stable operation under the condition of using two kinds of fuels is guaranteed to the greatest extent.
(5) According to the invention, through the injection form of the circumferential liquid fuel injection hole with the angle, the liquid fuel and the premixing section are well premixed and matched at the same time; according to the design, the proper momentum ratio is ensured, the phenomenon that fuel droplets collide the wall is avoided, and the anti-backfire, anti-coking ablation and anti-carbon deposition effects can be effectively achieved.
(6) According to the technical scheme, gaseous fuel enters the two-stage co-rotating head device, and combustion pulsation quantity can be adjusted by adjusting the fuel oil proportion of the diffusion fuel supply path, so that prevention and control of oscillatory combustion are realized.
(7) The small-state ignition and flameout of the invention ensures that the two different fuels have good ignition and flameout performance by the supply and combustion of the diffusion fuel, the supply of the gaseous and liquid diffusion fuels by setting reasonable characteristic dimensions and reasonably controlling the penetration and mixing of the fuels.
Finally, it should be noted that: the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A dual stage co-rotating head arrangement for a dual fuel gas turbine comprising a dual stage axial co-rotating swirler (1), a fuel nozzle (2) and a premixing section (3), the fuel nozzle (2) comprising a centrifugal nozzle (22) and a spray bar (21); the device is characterized in that the front end of the premixing section (3) is connected to the air outlet end of the two-stage axial co-rotating swirler (1) and used for inputting air and gaseous main fuel into the premixing section (3) through the two-stage axial co-rotating swirler (1); the gas inlet end of the spray rod (21) is arranged outside the two-stage axial co-rotation swirler (1), the gas outlet pipe of the spray rod (21) penetrates through the two-stage axial co-rotation swirler (1) and extends to one side, close to the rear end, of the interior of the premixing section (3) so as to input gaseous on-duty fuel to the rear end of the premixing section (3) through the spray rod (21) and input liquid main-stage fuel into the premixing section (3) through the spray rod (21); the centrifugal nozzle (22) is arranged at the air outlet end of the spray rod (21) and used for inputting liquid duty fuel to the rear end of the premixing section (3) through the centrifugal nozzle (22).
2. The dual stage co-rotating head arrangement for a dual fuel gas turbine as claimed in claim 1, wherein the dual stage axial co-rotating swirler (1) is provided with inner ring vane passages (11) and outer ring vane passages (12) therein for external input into the premixing section (3) through the inner ring vane passages (11) and outer ring vane passages (12).
3. The dual stage co-rotating head assembly for a dual fuel gas turbine engine of claim 1, it is characterized in that the double-stage axial same-rotation swirler (1) is internally provided with outer ring swirler vanes (13) and inner ring swirler vanes (14), the outer ring swirler vanes (13) and the inner ring swirler vanes (14) are both hollow vanes provided with inner cavities, and the outer ring swirler vanes (13) and the inner ring swirler vanes (14) are respectively provided with a gaseous main fuel inlet (15) which is communicated with the outside of the double-stage axial co-rotating swirler (1) and the inner cavities of the double-stage axial co-rotating swirler, the outer ring swirler vanes (13) are provided with first gaseous main fuel holes (131) which are communicated with the inner cavities of the outer ring swirler vanes, the inner ring swirler vanes (14) are provided with second gaseous main fuel holes (141) which are communicated with the inner cavities of the inner ring swirler vanes, for feeding gaseous main fuel into the premixing section (3) through the first gaseous main fuel hole (131) and the second gaseous main fuel hole (141).
4. The dual stage co-rotating head arrangement for a dual fuel gas turbine as claimed in claim 3, wherein the outer ring swirler vanes (13) have a vane twist angle greater than 55 °, a light transmission between any two adjacent outer ring swirler vanes (13) greater than 15%; the blade rotating directions of all the outer ring swirler blades (13) are the same.
5. The dual stage co-rotating head arrangement for a dual fuel gas turbine as claimed in claim 3 or 4 wherein the inner ring swirler vanes (14) have a vane twist angle greater than 55 °, with a light transmission between any two adjacent inner ring swirler vanes (14) of 0; the blade rotating directions of all the inner ring swirler blades (14) are the same.
6. The dual stage co-rotating head arrangement for a dual fuel gas turbine as claimed in claim 1, wherein the inlet end of the spray bar (21) is provided with a gaseous on-duty fuel inlet (211), the outlet end of the spray bar (21) is provided with a plurality of circumferential gaseous fuel injection holes (213) arranged axially along the spray bar, the gaseous on-duty fuel inlet (211) communicates with all circumferential gaseous fuel injection holes (213) for diffusively inputting the gaseous on-duty fuel to the rear end of the premixing section (3).
7. The dual stage co-rotating head arrangement for a dual fuel gas turbine as claimed in claim 1, wherein the air inlet end of the spray bar (21) is provided with a main liquid fuel inlet (214), the middle of the spray bar (21) is provided with a plurality of circumferential liquid fuel injection holes (216), and the main liquid fuel inlet (214) is communicated with all the circumferential liquid fuel injection holes (216) for inputting the main liquid stage fuel into the premixing section (3) through the circumferential liquid fuel injection holes (216) in an inclined manner.
8. The dual-stage co-rotating head device for the dual-fuel gas turbine as claimed in claim 1, wherein the air inlet end of the spray bar (21) is provided with a liquid duty fuel inlet (217), and the liquid duty fuel inlet (217) is communicated with the centrifugal nozzle (22) so as to feed the liquid duty fuel into the premixing section (3) after being subjected to rotary atomization through the centrifugal nozzle (22).
9. The dual-stage co-rotating head device for the dual-fuel gas turbine as claimed in claim 8, wherein a tangential hole (221), a transition section (222), a swirl groove (223), a swirl chamber (224) and a centrifugal nozzle (225) are arranged in the centrifugal nozzle (22) and are communicated with each other in sequence, and the air inlet end of the tangential hole (221) is communicated with the liquid on-duty fuel inlet (217).
10. The two-stage co-rotating head arrangement for a dual-fuel gas turbine as claimed in claim 1, characterized in that the premixing section (3) comprises a converging wall section (31) and an outlet throat section (32) connected to each other, one end of the converging wall section (31) being connected to the outlet end of the two-stage axial co-rotating swirler (1); and the outlet throat section (32) is provided with circumferential cooling holes (321).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110705839.5A CN113251439B (en) | 2021-06-24 | 2021-06-24 | Double-stage co-rotating head device for dual-fuel gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110705839.5A CN113251439B (en) | 2021-06-24 | 2021-06-24 | Double-stage co-rotating head device for dual-fuel gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113251439A CN113251439A (en) | 2021-08-13 |
| CN113251439B true CN113251439B (en) | 2021-11-16 |
Family
ID=77189665
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110705839.5A Active CN113251439B (en) | 2021-06-24 | 2021-06-24 | Double-stage co-rotating head device for dual-fuel gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113251439B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113719858B (en) * | 2021-08-26 | 2023-01-03 | 哈尔滨工程大学 | Natural gas high-efficiency stable-combustion low-emission combustion chamber head based on high-low rotational flow matching |
| CN114034061B (en) * | 2021-09-03 | 2023-06-23 | 东方电气集团科学技术研究院有限公司 | Liquid fuel nozzle for dual-fuel combustion chamber of dual-radial swirler |
| CN114526498B (en) * | 2022-04-21 | 2022-07-08 | 成都中科翼能科技有限公司 | Single-inlet double-oil-way composite atomizing nozzle |
| CN116293801B (en) * | 2023-03-06 | 2024-08-23 | 哈尔滨工程大学 | Premixing grade fuel and air reinforced mixing structure and shaft type cyclone |
Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101158479A (en) * | 2006-10-03 | 2008-04-09 | 通用电气公司 | Liquid fuel enhancement for natural gas swirl stabilized nozzle and method |
| CN101424407A (en) * | 2007-10-29 | 2009-05-06 | 通用电气公司 | Mager vorgemischte dual-fuel-ringrohrbrennkammer mit radial-mehrring-stufenduse |
| CN101726005A (en) * | 2008-10-31 | 2010-06-09 | 韩国电力公社 | Triple swirl gas turbine combustor |
| CN102105673A (en) * | 2008-06-27 | 2011-06-22 | 西港能源有限公司 | Fuel injection valve and method for co-injecting a liquid and a gaseous fuel into the combustion chamber of an internal combustion engine |
| CN102261673A (en) * | 2010-05-26 | 2011-11-30 | 通用电气公司 | Hybrid prefilming airblast, prevaporizing, lean-premixing dual-fuel nozzle for gas turbine combustor |
| CN103175223A (en) * | 2013-03-19 | 2013-06-26 | 哈尔滨工程大学 | Gas circuit axial grading type dual-fuel nozzle |
| CN103939943A (en) * | 2014-03-05 | 2014-07-23 | 哈尔滨工程大学 | Double-swirl dual-fuel nozzle used for chemical regenerative cycle |
| CN103939945A (en) * | 2014-03-05 | 2014-07-23 | 哈尔滨工程大学 | Rotatable dual-fuel nozzle used for chemical regenerative cycle |
| CN104154566A (en) * | 2014-07-08 | 2014-11-19 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Dual-fuel nozzle structure of gas turbine |
| CN204513461U (en) * | 2015-02-10 | 2015-07-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber dual fuel nozzle |
| CN204513460U (en) * | 2014-12-08 | 2015-07-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber inner and outer ring dual fuel nozzle |
| CN105180214A (en) * | 2015-09-23 | 2015-12-23 | 哈尔滨工程大学 | Double-fuel nozzle and cyclone integrated structure with low-heating-value gas combustion function |
| CN205481130U (en) * | 2016-02-06 | 2016-08-17 | 中国科学院工程热物理研究所 | Vortex premix burner |
| CN107208894A (en) * | 2015-01-29 | 2017-09-26 | 西门子能源公司 | Fuel injector including lobe mixer and vanes for injecting alternative fuels in a gas turbine |
| CN107575891A (en) * | 2017-07-25 | 2018-01-12 | 西北工业大学 | A kind of dual-fuel gas turbine low pollution combustor head construction |
| CN107687652A (en) * | 2017-07-25 | 2018-02-13 | 西北工业大学 | A kind of poor premix low pollution combustor head construction of dual-fuel gas turbine |
| CN107923617A (en) * | 2015-06-30 | 2018-04-17 | 安萨尔多能源英国知识产权有限公司 | Fuel injection position based on combustor flow path |
| CN107917442A (en) * | 2016-10-08 | 2018-04-17 | 安萨尔多能源瑞士股份公司 | Double fuel concentric nozzle for gas turbine |
| CN108443912A (en) * | 2018-02-08 | 2018-08-24 | 中国船舶重工集团公司第七0三研究所 | A kind of self-priming air-assisted atomization dual fuel nozzle |
| CN108700298A (en) * | 2016-03-03 | 2018-10-23 | 三菱重工业株式会社 | Burner and gas turbine |
| CN110529877A (en) * | 2019-07-31 | 2019-12-03 | 中国航发南方工业有限公司 | Multiphase fuel nozzle |
| CN112923397A (en) * | 2021-03-04 | 2021-06-08 | 西北工业大学 | Double-oil-way and double-air-way combined fuel nozzle |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7000403B2 (en) * | 2004-03-12 | 2006-02-21 | Power Systems Mfg., Llc | Primary fuel nozzle having dual fuel capability |
| RU2618801C2 (en) * | 2013-01-10 | 2017-05-11 | Дженерал Электрик Компани | Fuel nozzle, end fuel nozzle unit, and gas turbine |
| US10030869B2 (en) * | 2014-11-26 | 2018-07-24 | General Electric Company | Premix fuel nozzle assembly |
| WO2017116266A1 (en) * | 2015-12-30 | 2017-07-06 | General Electric Company | Liquid fuel nozzles for dual fuel combustors |
| CN112944395B (en) * | 2021-05-12 | 2021-09-07 | 成都中科翼能科技有限公司 | Combined premixer for gas turbine |
| CN113251440B (en) * | 2021-06-01 | 2021-11-30 | 成都中科翼能科技有限公司 | Multi-stage partition type combustion structure for gas turbine |
-
2021
- 2021-06-24 CN CN202110705839.5A patent/CN113251439B/en active Active
Patent Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101158479A (en) * | 2006-10-03 | 2008-04-09 | 通用电气公司 | Liquid fuel enhancement for natural gas swirl stabilized nozzle and method |
| CN101424407A (en) * | 2007-10-29 | 2009-05-06 | 通用电气公司 | Mager vorgemischte dual-fuel-ringrohrbrennkammer mit radial-mehrring-stufenduse |
| CN102105673A (en) * | 2008-06-27 | 2011-06-22 | 西港能源有限公司 | Fuel injection valve and method for co-injecting a liquid and a gaseous fuel into the combustion chamber of an internal combustion engine |
| CN101726005A (en) * | 2008-10-31 | 2010-06-09 | 韩国电力公社 | Triple swirl gas turbine combustor |
| CN102261673A (en) * | 2010-05-26 | 2011-11-30 | 通用电气公司 | Hybrid prefilming airblast, prevaporizing, lean-premixing dual-fuel nozzle for gas turbine combustor |
| CN103175223A (en) * | 2013-03-19 | 2013-06-26 | 哈尔滨工程大学 | Gas circuit axial grading type dual-fuel nozzle |
| CN103939943A (en) * | 2014-03-05 | 2014-07-23 | 哈尔滨工程大学 | Double-swirl dual-fuel nozzle used for chemical regenerative cycle |
| CN103939945A (en) * | 2014-03-05 | 2014-07-23 | 哈尔滨工程大学 | Rotatable dual-fuel nozzle used for chemical regenerative cycle |
| CN104154566A (en) * | 2014-07-08 | 2014-11-19 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Dual-fuel nozzle structure of gas turbine |
| CN204513460U (en) * | 2014-12-08 | 2015-07-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber inner and outer ring dual fuel nozzle |
| CN107208894A (en) * | 2015-01-29 | 2017-09-26 | 西门子能源公司 | Fuel injector including lobe mixer and vanes for injecting alternative fuels in a gas turbine |
| CN204513461U (en) * | 2015-02-10 | 2015-07-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber dual fuel nozzle |
| CN107923617A (en) * | 2015-06-30 | 2018-04-17 | 安萨尔多能源英国知识产权有限公司 | Fuel injection position based on combustor flow path |
| CN105180214A (en) * | 2015-09-23 | 2015-12-23 | 哈尔滨工程大学 | Double-fuel nozzle and cyclone integrated structure with low-heating-value gas combustion function |
| CN205481130U (en) * | 2016-02-06 | 2016-08-17 | 中国科学院工程热物理研究所 | Vortex premix burner |
| CN108700298A (en) * | 2016-03-03 | 2018-10-23 | 三菱重工业株式会社 | Burner and gas turbine |
| CN107917442A (en) * | 2016-10-08 | 2018-04-17 | 安萨尔多能源瑞士股份公司 | Double fuel concentric nozzle for gas turbine |
| CN107575891A (en) * | 2017-07-25 | 2018-01-12 | 西北工业大学 | A kind of dual-fuel gas turbine low pollution combustor head construction |
| CN107687652A (en) * | 2017-07-25 | 2018-02-13 | 西北工业大学 | A kind of poor premix low pollution combustor head construction of dual-fuel gas turbine |
| CN108443912A (en) * | 2018-02-08 | 2018-08-24 | 中国船舶重工集团公司第七0三研究所 | A kind of self-priming air-assisted atomization dual fuel nozzle |
| CN110529877A (en) * | 2019-07-31 | 2019-12-03 | 中国航发南方工业有限公司 | Multiphase fuel nozzle |
| CN112923397A (en) * | 2021-03-04 | 2021-06-08 | 西北工业大学 | Double-oil-way and double-air-way combined fuel nozzle |
Non-Patent Citations (1)
| Title |
|---|
| 双燃料喷嘴气体燃料路数值模拟与结构优化;徐海成;《燃气轮机技术》;20200916;全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113251439A (en) | 2021-08-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113251439B (en) | Double-stage co-rotating head device for dual-fuel gas turbine | |
| CN110657452B (en) | Low-pollution combustion chamber and combustion control method thereof | |
| CN102175045B (en) | Low-emission combustion chamber with main combustible stage head part multi-point slant oil taking | |
| CN101799174B (en) | Main combustible stage tangential oil supply premix and pre-evaporation combustion chamber | |
| EP1543272B1 (en) | Turbine engine fuel nozzle | |
| CN102506446B (en) | A fuel and air mixing device for a low-pollution combustor of a gas turbine | |
| CN106678875B (en) | A low-emission combustor with main combustion stage fueled by fuel injection pipes | |
| CN103017203B (en) | The fractional combustion chamber of a kind of main combustion stage loopful air inlet | |
| CN113310071A (en) | Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine | |
| CN102200291B (en) | Pneumatic primary level graded low-pollution combustion chamber | |
| US20080078182A1 (en) | Premixing device, gas turbines comprising the premixing device, and methods of use | |
| CN103697500B (en) | The premixed preevaporated low contamination combustion chamber of a kind of pair of pre-membrane type main combustion stage of oil circuit four eddy flow | |
| CN101709884A (en) | Premixing and pre-evaporating combustion chamber | |
| CN102022753A (en) | Low-pollution combustion chamber with premixed and pre-evaporated precombustion part | |
| CN101694301A (en) | Counter-flow flame combustion chamber | |
| CN114034061B (en) | Liquid fuel nozzle for dual-fuel combustion chamber of dual-radial swirler | |
| CN107687652B (en) | A lean-premixed low-polluting combustor head structure for a dual-fuel gas turbine | |
| CN106016364A (en) | A unit two-swirl premixed combustion nozzle for a gas turbine dry-type low-pollution combustor | |
| CN105823087B (en) | A kind of main combustion stage uses the low pollution combustor of effervescent atomizer | |
| CN108844097B (en) | Low-pollution combustion chamber for multi-point lean oil direct injection | |
| CN115289473B (en) | Gas-powder dual fuel burner | |
| CN115342384B (en) | Lean oil premixing integrated head structure of combustion chamber of gas turbine | |
| CN115342383B (en) | A low-pollution combustor head structure of a gas turbine using a mixing swirler | |
| CN109708148B (en) | Gas turbine combustor doublestage radial swirler | |
| CN205825112U (en) | A kind of two points of swirl-flow premixed burner noz(zle)s of gas turbine dry low pollution combustor unit |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Fan Zhencen Inventor after: Zhao Ruwei Inventor after: Wang Ming Inventor after: Liu Baoqi Inventor after: Chen Liujun Inventor after: Dai Mao Lin Inventor after: Yan Tengchong Inventor after: Wang Long Inventor after: Yang Zhi Inventor after: Wang Liangcheng Inventor before: Fan Zhencen Inventor before: Liu Baoqi Inventor before: Chen Liujun Inventor before: Dai Mao Lin Inventor before: Yan Tengchong Inventor before: Wang Long Inventor before: Yang Zhi Inventor before: Wang Liangcheng Inventor before: Zhao Ruwei |