CN113091094A - Gas turbine combustor nozzle and method of premixing fuel and air in the nozzle - Google Patents
Gas turbine combustor nozzle and method of premixing fuel and air in the nozzle Download PDFInfo
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- CN113091094A CN113091094A CN202110523325.8A CN202110523325A CN113091094A CN 113091094 A CN113091094 A CN 113091094A CN 202110523325 A CN202110523325 A CN 202110523325A CN 113091094 A CN113091094 A CN 113091094A
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- fuel
- air
- gas turbine
- nozzle
- 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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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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 invention provides a gas turbine combustor nozzle and a method for premixing fuel and air in the nozzle. The gas turbine combustor nozzle comprises a fuel delivery manifold, a fuel flow passage and a fuel-air premixing tube. The fuel delivery manifold is provided with a plurality of fuel outlets, each fuel outlet corresponding to at least one fuel flow passage. The fuel air premixing pipes are provided with fuel spray holes, fuel enters from the fuel conveying main pipe, enters into the fuel flow channel through the fuel outlet holes, enters into the fuel air premixing pipes through the fuel spray holes and is mixed with air entering in advance to form a mixture, and the mixture is sprayed out from the fuel air premixing pipes. The gas turbine combustor nozzle and the method for premixing fuel and air in the nozzle provided by the embodiment of the invention can ensure that the whole nozzle has good fuel and air premixing uniformity.
Description
Technical Field
The invention relates to the field of gas turbines, in particular to a gas turbine combustor nozzle and a method for premixing fuel and air in the nozzle.
Background
In a gas turbine DLN (Dry Low NOx) combustor, uniformity of fuel and air premixing is a key factor in controlling combustion NOx emissions. Since thermal NOx is mainly generated in the combustion chamber of the gas turbine, the amount of generation thereof is closely related to the combustion temperature. Thus, when the average combustion temperatures are the same, the different uniformity of mixing of the fuel and air results in localized combustion temperatures in different regions that deviate from the average temperature, which is higher in some places and lower in some places. In the region of higher temperature, thermal NOx is generated in a large amount, and finally, the amount of NOx discharged from the outlet is greatly increased.
A nozzle of a combustion chamber of a gas turbine in the prior art generally adopts fuel injection holes formed in swirler vanes, for example, a lean premixed combustion chamber of a gas turbine is disclosed in cn201210337011.x, which is specifically configured as shown in fig. 1-2, each vane 002 of a swirler assembly 001 of the lean premixed combustion chamber of the gas turbine is axially provided with a swirler vane blind hole 003, two side walls of each vane are provided with a plurality of premixed fuel injection holes 004, the vane blind hole 003 is communicated with the premixed fuel injection holes 004, premixed fuel enters a fuel cavity from a premixed fuel introducing pipe 005, and enters a swirler passage 006 through the swirler vane blind hole 003 on the vane and the premixed fuel injection holes 004 on the vane, so that the fuel is mixed with air at the downstream of the swirler.
The prior art has the disadvantages that the number of fuel holes on the rotary blade cannot be too large and the positions of the holes cannot be too close to the inner surface and the outer surface of the premixing channel due to the limitation of machining, so that the fuel concentration near the inner wall surface and the outer wall surface of the premixing channel is higher, the flame combustion temperature is high, the heat release is more concentrated, and the NOx emission is higher when the combustion engine operates at the basic load.
Disclosure of Invention
To address the above-mentioned problems, the present application provides a gas turbine combustor nozzle and a method of premixing fuel and air in the nozzle.
Therefore, the purpose of the application is to provide a gas turbine combustor nozzle, and the mixture equivalence ratio of each fuel gas premixing pipe is accurately adjusted through a multiple premixing pipe structure in the nozzle, so that the whole nozzle premixing section is ensured to have good fuel and air premixing uniformity.
A gas turbine combustor nozzle comprises a fuel delivery main pipe, a fuel flow passage and a fuel-air premixing section,
the fuel delivery manifold is provided with a plurality of fuel exit orifices,
each fuel outlet corresponds to at least one fuel flow channel;
the fuel-air premixing pipes are provided with fuel spray holes;
the fuel enters from the fuel delivery manifold, enters the fuel flow channel through the fuel outlet, enters the fuel air premixing pipe through the fuel spray holes and is mixed with the air which enters in advance to form a mixture, and the mixture is sprayed out from the fuel air premixing pipe.
Optionally, the fuel-air premixing tube is provided with a swirling structure, and the swirling structure ejects the mixture in a swirling airflow manner.
Optionally, the fuel-air premixing tube includes an output tube portion, the output tube portion is deflected at a preset angle in a circumferential direction as the swirling structure, so that the mixture jetted out from the fuel-air premixing tube forms a swirling air flow in the preset circumferential direction.
Optionally, each outlet duct portion of the fuel-air premix duct is deflected clockwise or counterclockwise in the circumferential direction.
Optionally, the fuel-air pre-mix tube includes an intermediate tube portion upstream of the outlet tube portion, the outlet tube portion being offset relative to the intermediate tube portion.
Optionally, the intermediate tube portion of the fuel-air premix tube includes a laval nozzle structure.
Optionally, the fuel-air pre-mix tube includes an inlet tube portion upstream of the intermediate tube portion, the fuel orifices being disposed in the inlet tube portion.
Optionally, the fuel injection holes are arranged on the side surface of the input pipe part, so that the direction of the fuel entering the fuel-air premixing pipe is perpendicular to the direction of the air flowing along the fuel-air premixing pipe.
Optionally, the fuel injection holes include first fuel injection holes and second fuel injection holes, and the first fuel injection holes and the second fuel injection holes are arranged in a staggered manner in the circumferential plane.
Optionally, the fuel flow channels radiate outwardly from the fuel delivery manifold.
Optionally, the fuel outlets are distributed in a circumferential ring shape.
Optionally, the plurality of fuel-air pre-mix tubes are parallel to each other.
Optionally, the fuel-air equivalence ratio of the mixture in the fuel-air premix tube is the same as the fuel-air equivalence ratio of the mixture in the combustor.
Optionally, the gas turbine combustor nozzle further comprises a flow straightening hole and an outer wall,
the outer wall is arranged downstream of the flow-shaping orifice and surrounds a nozzle chamber;
air enters the fuel-air premix tube from the flow shaping hole;
the outlet end of the fuel flow passage is arranged on the outer wall;
the fuel enters the nozzle cavity through the fuel flow channel and enters the fuel-air premixing tube through the fuel jet hole.
Optionally, the gas turbine combustor nozzle is manufactured by an additive manufacturing process.
To achieve the above object, the present invention further provides a method for premixing fuel and air in a nozzle of a gas turbine combustor, comprising:
the fuel enters from the fuel delivery manifold,
enters the fuel flow channel through the fuel outlet hole,
entering the fuel-air premix tube through the fuel orifices mixes with air previously entering therein to form a mixture that is ejected from the fuel-air premix tube.
Optionally, air enters the fuel-air premix tube from the flow shaping orifice.
Optionally, the output pipe part of the fuel-air premixing pipe is of a laval nozzle structure,
by varying the throat size of the Laval nozzle structure, mixing of the fuel with the air is facilitated.
Optionally, the flow rate of the mixture is adjusted by changing the size of the inner diameter of the fuel-air premix tube.
Optionally, the flow of fuel into the fuel-air premix tube is varied by adjusting the size of fuel orifices on the fuel-air premix tube.
Optionally, the rotational strength of the fuel entering the fuel-air premix tube is varied by adjusting the distance between the fuel spray holes and the centerline of the fuel-air premix tube.
The gas turbine combustor nozzle and the method for premixing fuel and air in the nozzle have the advantages that:
1. the nozzle adopts a plurality of mutually independent premixing tube structures, the air quantity in each premixing tube can be accurately adjusted, the premixing uniformity of fuel and air in each premixing tube is controlled, and the premixing effect is optimized.
2. The nozzle can quickly mix fuel and air, and compared with a special premixing structure of the nozzle for the vane injection of a traditional swirler, the axial length of the special premixing structure can be shortened by 30-50%.
3. The structure of the combustion chamber is simpler by replacing the structure of a swirler by circumferential deflection at the outlet of the premixing tube.
4. The multi-premix tube structure has certain capability of absorbing thermo-acoustic oscillation, and is beneficial to improving the thermo-acoustic oscillation characteristic of the combustion chamber.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a prior art gas turbine combustor nozzle;
FIG. 2 is a prior art gas turbine combustor nozzle;
FIG. 3 is a schematic view of the structure of the gas turbine combustor nozzle of the present invention;
FIG. 4 is a cross-sectional view of a fuel air premix tube of the gas turbine combustor nozzle of the present invention;
FIG. 5 is a first cross-sectional view of a fuel air premix tube of the gas turbine combustor nozzle of the present invention;
FIG. 6 is a side view of a gas turbine combustor nozzle of the present invention;
FIG. 7 is a second cross-sectional view of the fuel air premix tube of the gas turbine combustor nozzle of the present invention;
FIG. 8 is a third cross-sectional view of the fuel air premix tube of the gas turbine combustor nozzle of the present invention;
FIG. 9 is a cross-sectional view one of the fuel air premix tubes of the gas turbine combustor nozzle of the present invention;
FIG. 10 is a cross-sectional view of the fuel air premix tube of the gas turbine combustor nozzle of the present invention;
FIG. 11 is a flowchart of a fuel and air premixing method according to embodiment 6 of the present invention;
FIG. 12 is a flowchart of a fuel and air premixing method in accordance with embodiment 7 of the present invention;
FIG. 13 is a flowchart of a fuel and air premixing method according to embodiment 8 of the present invention;
FIG. 14 is a flowchart of a fuel and air premixing method in accordance with embodiment 9 of the present invention;
FIG. 15 is a flowchart of a fuel and air premixing method in accordance with embodiment 10 of the present invention;
FIG. 16 is a flow chart of a fuel and air premixing method in accordance with embodiment 11 of the present invention.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The present invention is described in further detail below with reference to specific examples, which are not to be construed as limiting the scope of the invention as claimed.
Example 1
As shown in fig. 3 to 4, the gas turbine combustor nozzle 100 is divided into three parts, namely, a fuel delivery manifold 1, a fuel flow passage 2, and a fuel-air premixing tube 3.
The diameter of the fuel delivery main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlets 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel delivery main pipe 1, the fuel outlets 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet 12 corresponds to at least one fuel flow channel 2. The fuel flow channels 2 are radially arranged by taking the axis of the fuel delivery main pipe 1 as a geometric center. The fuel flow channels 2 on the same circle layer have the same axial angle with the fuel delivery manifold 1.
The number of the fuel-air premixing pipes 3 is several, and they are distributed uniformly from the center to the outer side along the radius direction of the nozzle 100, and they are parallel to each other. Upstream of the fuel-air premixing tube 3, fuel injection holes 31 are provided for injecting fuel into the fuel-air premixing tube 3.
The gas turbine combustor nozzle 100 also includes a flow straightener bore 4 and an outer wall 5. The flow-adjusting holes 4 are arranged on the surface of the conical body on the inner side of the fuel flow channel 2, and are uniformly distributed along the radial direction from inside to outside in a plurality of rows by taking the axial direction of the fuel conveying main pipe 1 as the center. Air enters the gas turbine combustor nozzle 100 from the rectifying hole 4 at the air suction end and then is quickly divided, and the air and the fuel are uniformly mixed in the fuel-air premixing pipe 3.
The outer wall 5 is arranged downstream of the flow-shaping orifice 4, forming a nozzle chamber 6 around the nozzle 100. Air enters the fuel-air premix tube 3 from the flow-shaping orifice 4; the outlet end of the fuel flow channel 2 is arranged around the circumference of the outer wall 5. Fuel enters the nozzle chamber 6 through the fuel flow passages 2 and enters the fuel air premix tube 3 through the fuel orifices 31 (see FIG. 5).
Alternatively, the fuel-air equivalence ratio of the mixture in the fuel-air premix tube 3 is the same as the fuel-air equivalence ratio of the mixture in the combustion chamber.
Optionally, the gas turbine combustor nozzle 100 is manufactured using an additive manufacturing process.
When the nozzle of the combustion chamber of the gas turbine is in a working state, fuel enters from the fuel delivery main pipe 1, enters the fuel flow channel 2 through the fuel outlet 12, enters the fuel-air premixing pipe 3 through the fuel spray holes 31, and is mixed with air entering in advance to form a mixture, and the mixture is sprayed out from the fuel-air premixing pipe 3.
Example 2
As shown in fig. 3 to 4, the gas turbine combustor nozzle 100 is divided into three parts, namely, a fuel delivery manifold 1, a fuel flow passage 2, and a fuel-air premixing tube 3.
The diameter of the fuel delivery main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlets 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel delivery main pipe 1, the fuel outlets 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet 12 corresponds to at least one fuel flow channel 2. The fuel flow channels 2 are radially arranged by taking the axis of the fuel delivery main pipe 1 as a geometric center. The fuel flow channels 2 on the same circle layer have the same axial angle with the fuel delivery manifold 1.
The number of the fuel-air premixing pipes 3 is several, and they are distributed uniformly from the center to the outer side along the radius direction of the nozzle 100, and they are parallel to each other. Upstream of the fuel-air premixing tube 3, fuel injection holes 31 are provided for injecting fuel into the fuel-air premixing tube 3.
Alternatively, the fuel-air equivalence ratio of the mixture in the fuel-air premix tube 3 is the same as the fuel-air equivalence ratio of the mixture in the combustion chamber.
Optionally, the gas turbine combustor nozzle 100 is manufactured using an additive manufacturing process.
In the present embodiment, as shown in fig. 5, the fuel-air pre-mix tube 3 includes an output duct portion 32, and the output duct portion 32 is deflected at a predetermined angle α in a clockwise or counterclockwise direction in the circumferential direction to form a swirl structure. Fig. 6 shows a nozzle external view of the direction of air inflow from the gas turbine combustor nozzle after the outlet duct portion 32 has been deflected clockwise at an angle α. This structure makes the fuel-air mixture injected from the delivery pipe portion 32 of the fuel-air premixing pipe 3 form a circumferential swirling air flow in the downstream spatial direction, thereby enhancing the premixing effect of fuel and air.
When the nozzle of the combustion chamber of the gas turbine is in a working state, fuel enters from the fuel delivery main pipe 1, enters the fuel flow channel 2 through the fuel outlet 12, enters the fuel-air premixing pipe 3 through the fuel spray holes 31, and is mixed with air entering in advance to form a mixture, and the mixture is sprayed out from the fuel-air premixing pipe 3. The output pipe part 32 of the fuel-air premixing pipe 3 is deflected by an angle alpha, and the structure can spray rotary airflow to the downstream, so that the premixing effect of fuel and air is effectively enhanced. Meanwhile, the structure can spray rotary airflow, and can replace a swirler structure in the traditional scheme, so that the mechanical structure of the combustion chamber is simpler.
Example 3
As shown in fig. 3 to 4, the gas turbine combustor nozzle 100 is divided into three parts, namely, a fuel delivery manifold 1, a fuel flow passage 2, and a fuel-air premixing tube 3.
The diameter of the fuel delivery main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlets 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel delivery main pipe 1, the fuel outlets 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet 12 corresponds to at least one fuel flow channel 2. The fuel flow channels 2 are radially arranged by taking the axis of the fuel delivery main pipe 1 as a geometric center. The fuel flow channels 2 on the same circle layer have the same axial angle with the fuel delivery manifold 1.
The number of the fuel-air premixing pipes 3 is several, and they are distributed uniformly from the center to the outer side along the radius direction of the nozzle 100, and they are parallel to each other. Upstream of the fuel-air premixing tube 3, fuel injection holes 31 are provided for injecting fuel into the fuel-air premixing tube 3.
Alternatively, the fuel-air equivalence ratio of the mixture in the fuel-air premix tube 3 is the same as the fuel-air equivalence ratio of the mixture in the combustion chamber.
Optionally, the gas turbine combustor nozzle 100 is manufactured using an additive manufacturing process.
In the present embodiment, as shown in fig. 7, the fuel-air pre-mix pipe 3 includes an intermediate pipe portion 33 located upstream of the output pipe portion 32, the output pipe portion 32 is deflected with respect to the intermediate pipe portion 33, and the output pipe portion 32 is deflected at a predetermined angle α in a circumferential clockwise or counterclockwise direction, forming a swirl structure. This structure makes the fuel-air mixture injected from the delivery pipe portion 32 of the fuel-air premixing pipe 3 form a circumferential swirling air flow in the downstream spatial direction, thereby enhancing the premixing effect of fuel and air.
Fig. 7 shows the angle of deflection a of the outlet duct portion 32 of each fuel premix tube 3 relative to the intermediate duct portion 33.
When the nozzle of the combustion chamber of the gas turbine is in a working state, fuel enters from the fuel delivery main pipe 1, enters the fuel flow channel 2 through the fuel outlet 12, enters the fuel-air premixing pipe 3 through the fuel spray holes 31, and is mixed with air entering in advance to form a mixture, and the mixture is sprayed out from the fuel-air premixing pipe 3. The output pipe part 32 of the fuel-air premixing pipe 3 is deflected by an angle alpha, and the structure can spray rotary airflow to the downstream, so that the premixing effect of fuel and air is effectively enhanced. Meanwhile, the structure can spray rotary airflow, and can replace a swirler structure in the traditional scheme, so that the mechanical structure of the combustion chamber is simpler.
Example 4
As shown in fig. 3 to 4, the gas turbine combustor nozzle 100 is divided into three parts, namely, a fuel delivery manifold 1, a fuel flow passage 2, and a fuel-air premixing tube 3.
The diameter of the fuel delivery main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlets 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel delivery main pipe 1, the fuel outlets 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet 12 corresponds to at least one fuel flow channel 2. The fuel flow channels 2 are radially arranged by taking the axis of the fuel delivery main pipe 1 as a geometric center. The fuel flow channels 2 on the same circle layer have the same axial angle with the fuel delivery manifold 1.
The number of the fuel-air premixing pipes 3 is several, and they are distributed uniformly from the center to the outer side along the radius direction of the nozzle 100, and they are parallel to each other. Upstream of the fuel-air premixing tube 3, fuel injection holes 31 are provided for injecting fuel into the fuel-air premixing tube 3.
Alternatively, the fuel-air equivalence ratio of the mixture in the fuel-air premix tube 3 is the same as the fuel-air equivalence ratio of the mixture in the combustion chamber.
Optionally, the gas turbine combustor nozzle 100 is manufactured using an additive manufacturing process.
In the present embodiment, as shown in fig. 7, in order to further promote uniform mixing of fuel and air, the intermediate pipe portion 33 of the fuel-air pre-mixing pipe 3 has a laval nozzle structure B. The Laval nozzle type structure B is an integrated structure formed by a contraction pipe on the left side and an expansion pipe on the right side. The structure can change the speed of the airflow due to the change of the spray cross section area. In this embodiment, the converging tube further promotes the uniformity of fuel and air mixing, and the subsequent diverging configuration facilitates reducing flow pressure loss of the fuel-air pre-mix tube 3.
Alternatively, the throat area of the laval nozzle may be adjusted to control the mixture ratio in each fuel-air premix tube 3.
When the nozzle of the combustion chamber of the gas turbine is in a working state, fuel enters from the fuel delivery main pipe 1, enters the fuel flow channel 2 through the fuel outlet 12, enters the fuel-air premixing pipe 3 through the fuel spray holes 31, and is mixed with air entering in advance to form a mixture, and the mixture is sprayed out from the fuel-air premixing pipe 3. The laval nozzle B of the outlet pipe portion 32 of the fuel-air premixing pipe 4 effectively increases the mixing degree of fuel and air by the contraction and expansion structure, and reduces the flow pressure loss of the mixture to the fuel-air premixing pipe.
Example 5
As shown in fig. 3 to 4, the gas turbine combustor nozzle 100 is divided into three parts, namely, a fuel delivery manifold 1, a fuel flow passage 2, and a fuel-air premixing tube 3.
The diameter of the fuel delivery main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlets 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel delivery main pipe 1, the fuel outlets 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet 12 corresponds to at least one fuel flow channel 2. The fuel flow channels 2 are radially arranged by taking the axis of the fuel delivery main pipe 1 as a geometric center. The fuel flow channels 2 on the same circle layer have the same axial angle with the fuel delivery manifold 1.
The number of the fuel-air premixing pipes 3 is several, and they are distributed uniformly from the center to the outer side along the radius direction of the nozzle 100, and they are parallel to each other. Upstream of the fuel-air premixing tube 3, fuel injection holes 31 are provided for injecting fuel into the fuel-air premixing tube 3.
Alternatively, the fuel-air equivalence ratio of the mixture in the fuel-air premix tube 3 is the same as the fuel-air equivalence ratio of the mixture in the combustion chamber.
Optionally, the gas turbine combustor nozzle 100 is manufactured using an additive manufacturing process.
In the present embodiment, as shown in fig. 8, the fuel-air pre-mix pipe 3 includes an intermediate pipe portion 33 upstream of the output pipe portion 32, and an input pipe portion 34 upstream of the intermediate pipe portion 33. Fig. 9 is a cross-sectional view of the fuel-air premix tube, and two fuel injection holes 31, i.e., a first fuel injection hole 331 and a second fuel injection hole 332, are provided in the inlet pipe portion 34 and are arranged offset from each other in the circumferential plane of the fuel-air premix tube 3. Fuel enters the fuel-air premix tube 3 from both directions f1 and f2 through the first fuel orifices 331 and the second fuel orifices 332, respectively. As shown in FIG. 10, the eccentricity of the first fuel nozzle holes 331 from the centerline of the fuel-air premix tube 3 is L1, and the eccentricity of the second fuel nozzle holes 332 from the centerline of the fuel-air premix tube 3 is L2. By adjusting L1 and L2, the fuel bundle rotation intensity can be changed.
Alternatively, the directions f1 and f2 of fuel entering the fuel-air premix tube 3 are perpendicular to the direction of air flow along the fuel-air premix tube 3.
When the nozzle of the combustion chamber of the gas turbine is in a working state, fuel enters from the fuel delivery main pipe 1, enters the fuel flow channel 2 through the fuel outlet 12, enters the fuel-air premixing pipe 3 through the fuel spray holes 31, and is mixed with air entering in advance to form a mixture, and the mixture is sprayed out from the fuel-air premixing pipe 3. The design can make the fuel form a rotating fuel air flow in the fuel-air premixing pipe 3 and be sprayed out from the output pipe part 32 of the fuel-air premixing pipe 3, and the mixing speed and uniformity of the fuel and the air are effectively accelerated.
Example 6
The invention also discloses a method for premixing fuel and air in the nozzle of the combustion chamber of the gas turbine.
As shown in fig. 11, the method includes:
step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow channels 2 through the fuel outlets 12 in the fuel delivery manifold 1.
Step S2: the fuel passes through the fuel injection holes 31 and enters the fuel-air pre-mix tube 3.
Step S3: the fuel entering the fuel-air premix tube 3 is mixed with air previously entering therein to form a mixture, which is ejected from the fuel-air premix tube 3.
In the embodiment of the invention, fuel enters the nozzle 100 from the fuel delivery manifold 1, enters the fuel-air premixing pipe 3 through the fuel flow channel 2, enters the fuel-air premixing pipe 3 through the fuel spray holes 31 to be mixed with air, and finally, a mixture formed by mixing the fuel and the air enters the combustion chamber through the output pipe part 32 of the fuel-air premixing pipe 3, so that the premixing uniformity of the fuel and the air is effectively improved.
Example 7
As shown in fig. 12, the method includes:
step S4: air enters the fuel-air premix tube 3 from the flow straightening holes 4.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow channels 2 through the fuel outlets 12 in the fuel delivery manifold 1.
Step S2: the fuel passes through the fuel injection holes 31 and enters the fuel-air pre-mix tube 3.
Step S3: the fuel entering the fuel-air premix tube 3 is mixed with air previously entering therein to form a mixture, which is ejected from the fuel-air premix tube 3.
In the embodiment of the invention, fuel enters the nozzle from the fuel delivery manifold 1, enters the fuel-air premixing pipe 3 through the fuel flow channel 2, enters the fuel-air premixing pipe 3 through the fuel spray holes 31 to be mixed with air, and finally, a mixture formed by mixing the fuel and the air enters the combustion chamber through the output pipe part 32 of the fuel-air premixing pipe 3. The design effectively improves the premixing uniformity of the fuel and the air through a double-flow-path structure of the fuel and the air.
Example 8
The delivery pipe portion 32 of the fuel-air pre-mix pipe 3 is a laval nozzle structure.
As shown in fig. 13, the method includes:
step S5: the throat size of the laval nozzle structure is set to promote mixing of the fuel and air.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow channels 2 through the fuel outlets 12 in the fuel delivery manifold 1.
Step S2: the fuel passes through the fuel injection holes 31 and enters the fuel-air pre-mix tube 3.
Step S3: the fuel entering the fuel-air premix tube 3 is mixed with air previously entering therein to form a mixture, which is ejected from the fuel-air premix tube 3.
According to the embodiment of the invention, the size of the throat part of the nozzle C with the Laval structure is set, so that the mixing of fuel and air is promoted, and the premixing uniformity of the fuel and the air in the nozzle is improved.
Example 9
As shown in fig. 14, the method includes:
step S6: the inner diameter of the fuel-air premix tube 3 is adjusted.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow channels 2 through the fuel outlets 12 in the fuel delivery manifold 1.
Step S2: the fuel passes through the fuel injection holes 31 and enters the fuel-air pre-mix tube 3.
Step S3: the fuel entering the fuel-air premix tube 3 is mixed with air previously entering therein to form a mixture, which is ejected from the fuel-air premix tube 3.
According to the embodiment of the invention, the mixing uniformity of the fuel and air mixture in the nozzle is further optimized by adjusting the inner diameter of the fuel-air premixing pipe 3 and the flow velocity of the mixture.
Example 10
As shown in fig. 15, the method includes:
step S7: the size of the fuel injection holes 31 on the fuel-air pre-mix tube 3 is adjusted.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow channels 2 through the fuel outlets 12 in the fuel delivery manifold 1.
Step S2: the fuel passes through the fuel injection holes 31 and enters the fuel-air pre-mix tube 3.
Step S3: the fuel entering the fuel-air premix tube 3 is mixed with air previously entering therein to form a mixture, which is ejected from the fuel-air premix tube 3.
According to the embodiment of the invention, the size of the fuel spray holes 31 on the fuel-air premixing pipe 3 is adjusted, the flow of the fuel entering the fuel-air premixing pipe 3 is changed, the proportion of the fuel and the air is effectively controlled, and the mixing uniformity of the fuel and the air mixture is optimized.
Example 11
As shown in fig. 16, the method includes:
step S8: the distance between the fuel nozzle holes 31 and the centerline of the fuel-air pre-mix tube 3 is adjusted.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow channels 2 through the fuel outlets 12 in the fuel delivery manifold 1.
Step S2: the fuel passes through the fuel injection holes 31 and enters the fuel-air pre-mix tube 3.
Step S3: the fuel entering the fuel-air premix tube 3 is mixed with air previously entering therein to form a mixture, which is ejected from the fuel-air premix tube 3.
According to the embodiment of the invention, the distance between the fuel spray holes 31 and the center line of the fuel-air premixing pipe 3 is adjusted to change the rotating strength of the fuel entering the fuel-air premixing pipe 3, so that the mixing speed and uniformity of the fuel and the air are controlled.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. 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 (21)
1. A gas turbine combustor nozzle (100) comprising a fuel delivery manifold (1), fuel flow passages (2), and a fuel-air pre-mix tube (3),
the fuel delivery main pipe (1) is provided with a plurality of fuel outlets (12);
each fuel outlet hole (12) corresponds to at least one fuel flow channel (2);
the fuel-air premixing pipes (3) are multiple, and the fuel-air premixing pipes (3) are provided with fuel spray holes (31);
fuel enters from the fuel delivery manifold (1), enters the fuel flow channel (2) through the fuel outlet hole (12), enters the fuel-air premixing pipe (3) through the fuel spray hole (31) and is mixed with air entering in advance to form a mixture, and the mixture is sprayed out from the fuel-air premixing pipe (3).
2. Gas turbine combustor nozzle (100) according to claim 1, characterized in that the fuel-air pre-mix tube (3) is provided with a swirl structure which ejects the mixture in a swirling air flow.
3. The gas turbine combustor nozzle (100) of claim 2, characterized in that the fuel-air pre-mix tube (3) includes an output duct portion (32), the output duct portion (32) being deflected in a circumferential direction at a predetermined angle as the swirl structure, such that the mixture ejected from the fuel-air pre-mix tube (3) forms a swirling air flow in a predetermined circumferential direction.
4. A gas turbine combustor nozzle (100) as in claim 3, wherein each outlet duct portion (32) of the fuel-air pre-mix duct (3) is deflected clockwise or counter-clockwise in a circumferential direction.
5. A gas turbine combustor nozzle (100) as in claim 3, wherein the fuel-air pre-mix tube (3) comprises an intermediate tube section (33) upstream of the output tube section (32), the output tube section (32) being offset with respect to the intermediate tube section (33).
6. A gas turbine combustor nozzle (100) as in claim 3, wherein the intermediate duct portion (33) of the fuel-air pre-mix duct (3) comprises a laval nozzle structure.
7. A gas turbine combustor nozzle (100) as in claim 3, wherein the fuel-air pre-mix tube (3) comprises an inlet tube portion (34) upstream of the intermediate tube portion (33), the fuel orifices (31) being disposed in the inlet tube portion (34).
8. The gas turbine combustor nozzle (100) of claim 7, where the fuel orifices (31) are disposed on a side of the inlet duct portion (34) such that the direction of the fuel entering the fuel-air premix tube (3) is perpendicular to the direction of air flow along the fuel-air premix tube (3).
9. The gas turbine combustor nozzle (100) of claim 7, characterized in that the fuel orifices (31) include first fuel orifices (311) and second fuel orifices (312), the first fuel orifices (311) and the second fuel orifices (312) being staggered in a circumferential plane.
10. The gas turbine combustor nozzle (100) of claim 1, wherein the fuel flow passages (2) radiate outwardly from the fuel delivery manifold (1).
11. A gas turbine combustor nozzle (100) as claimed in claim 1, wherein the fuel exit holes (12) are circumferentially distributed in a circular ring shape.
12. The gas turbine combustor nozzle (100) of claim 1, characterized in that the plurality of fuel-air pre-mix tubes (3) are parallel to each other.
13. A gas turbine combustor nozzle as claimed in any one of claims 1 to 7, characterised in that the fuel-air equivalence ratio of the mixture in the fuel-air premixing tube (3) is the same as the fuel-air equivalence ratio of the mixture in the combustor.
14. The gas turbine combustor nozzle (100) of claim 1, characterized in that the gas turbine combustor nozzle (100) further comprises a flow straightener hole (4) and an outer wall (5),
the outer wall (5) is arranged downstream of the flow-straightening orifice (4) and surrounds a nozzle chamber (6);
air enters the fuel-air premix tube (3) from the flow-shaping orifice (4);
the outlet end of the fuel flow channel (2) is arranged on the outer wall (5);
the fuel enters the nozzle chamber (6) through the fuel flow passage (2) and enters the fuel-air premixing tube (3) through the fuel injection holes (31).
15. The gas turbine combustor nozzle (100) of claim 1, characterized in that the gas turbine combustor nozzle (100) is made using an additive manufacturing process.
16. A method of premixing fuel and air in a gas turbine combustor nozzle, comprising:
fuel enters from a fuel delivery manifold (1), enters a fuel flow channel (2) through a fuel outlet hole (12), enters the fuel-air premixing pipe (3) through the fuel spray holes (31) and is mixed with air entering in advance to form a mixture, and the mixture is sprayed out from the fuel-air premixing pipe (3).
17. The method of claim 16, comprising:
air enters the fuel-air premix tube (3) from the flow-shaping orifice (4).
18. The method of claim 16, comprising:
the output pipe part (32) of the fuel-air premixing pipe (3) is of a Laval nozzle structure,
by varying the throat size of the Laval nozzle structure, mixing of the fuel with the air is facilitated.
19. The method of claim 16, comprising:
the flow rate of the mixture is adjusted by varying the size of the inner diameter of the fuel-air premix tube (3).
20. The method of claim 16, comprising:
varying the flow of the fuel into the fuel-air premix tube (3) by adjusting the size of fuel orifices (31) on the fuel-air premix tube (3).
21. The method of claim 16, comprising:
the distance between the fuel spray holes (31) and the center line of the fuel-air premixing pipe (3) is adjusted to change the rotation strength of the fuel entering the fuel-air premixing pipe (3).
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| CN202110523325.8A CN113091094B (en) | 2021-05-13 | 2021-05-13 | Gas turbine combustor nozzle and method for premixing fuel and air in nozzle |
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| CN202110523325.8A CN113091094B (en) | 2021-05-13 | 2021-05-13 | Gas turbine combustor nozzle and method for premixing fuel and air in nozzle |
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| CN114857619A (en) * | 2022-04-29 | 2022-08-05 | 江苏中科能源动力研究中心 | Micro-mixing combustion chamber of gas turbine |
| US20230296252A1 (en) * | 2022-03-21 | 2023-09-21 | Doosan Enerbility Co., Ltd | Combustor nozzle, combustor, and gas turbine including the same |
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