CN113091094B - Gas turbine combustor nozzle and method for premixing fuel and air in nozzle - Google Patents
Gas turbine combustor nozzle and method for premixing fuel and air in nozzle Download PDFInfo
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- CN113091094B CN113091094B CN202110523325.8A CN202110523325A CN113091094B CN 113091094 B CN113091094 B CN 113091094B CN 202110523325 A CN202110523325 A CN 202110523325A CN 113091094 B CN113091094 B CN 113091094B
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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 conveying main pipe, a fuel runner and a fuel air premixing pipe. The fuel delivery manifold is provided with a plurality of fuel outlet holes, and each fuel outlet hole corresponds to at least one fuel flow passage. The fuel-air premixing pipes are provided with a plurality of fuel spray holes, fuel enters from the fuel conveying main pipe, enters into the fuel flow passage through the fuel spray 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 combustion chamber nozzle and the method for premixing fuel and air in the nozzle 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, fuel and air premixing uniformity is a critical factor in controlling combustion NOx emissions. Since the combustion chamber of a gas turbine is mainly thermal NOx, the generation amount and the combustion temperature are closely related. Thus, when the average combustion temperature is the same, the uniformity of mixing of fuel and air causes the local combustion temperatures in different regions to deviate from the average temperature, with some places being higher and some places being lower. In the higher temperature region, thermal NOx is generated in large amounts, ultimately resulting in a large increase in the NOx emissions at the outlet.
The prior art gas turbine combustion chamber nozzle generally adopts to open fuel spray holes on swirler vanes, as shown in a specific structure of a lean premixed combustion chamber of a gas turbine, 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 wall surfaces of each vane are provided with a plurality of premixed fuel spray holes 004, the vane blind holes 003 are communicated with the premixed fuel spray holes 004, the premixed fuel enters a premixed fuel cavity from a premixed fuel introducing pipe 005, and enters a swirler channel 006 through the swirler vane blind holes 003 on the vanes and the premixed fuel spray holes 004 on the vanes, so that the fuel is mixed with air at the downstream of the swirler.
The disadvantage of this prior art is that, due to the limitation of machining, the number of fuel holes in the rotating blades cannot be excessive and the positions of the openings cannot be too close to the inner and outer surfaces of the premixing passage, thus resulting in a higher fuel concentration near the inner and outer wall surfaces of the premixing passage, a higher flame combustion temperature, a more concentrated heat release, and a higher NOx emission during the operation of the engine at base load.
Disclosure of Invention
To solve the above problems, the present application proposes a gas turbine combustor nozzle and a method of premixing fuel and air in the nozzle.
Therefore, the present application aims to provide a gas turbine combustor nozzle, which precisely adjusts the mixture equivalence ratio of each fuel gas premixing tube through a multi-premixing tube structure in the nozzle, and ensures that the whole nozzle premixing section has good fuel and air premixing uniformity.
A gas turbine combustor nozzle comprises a fuel conveying main pipe, a fuel runner and a fuel air premixing section,
the fuel delivery manifold is provided with a plurality of fuel outlet holes,
each fuel outlet corresponds to at least one fuel runner;
the fuel air premixing pipes are provided with fuel spray holes;
the fuel enters from the fuel conveying main pipe, enters into the fuel runner through the fuel outlet hole, enters into the fuel air premixing pipe through the fuel spray hole, and is mixed with air entering 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 swirl structure, and the swirl structure ejects the mixture in a rotary airflow mode.
Optionally, the fuel air premix tube includes an output pipe portion that deflects as the swirl structure at a predetermined angle in a circumferential direction such that the mixture ejected from the fuel air premix tube forms a swirling air flow in a predetermined circumferential direction.
Optionally, each output pipe of the fuel air premix tube deflects clockwise or counter-clockwise in a circumferential direction.
Optionally, the fuel air premix tube includes a middle tube portion upstream of the output tube portion, the output tube portion being deflected relative to the middle tube portion.
Optionally, the intermediate tube portion of the fuel air premix tube includes a Laval nozzle structure.
Optionally, the fuel-air premixing tube includes an input tube portion located upstream of the intermediate tube portion, and the fuel nozzle is disposed in the input tube portion.
Optionally, the fuel nozzle is disposed on a side surface of the input pipe portion, so that a direction in which the fuel enters the fuel-air premixing pipe is perpendicular to a direction in which the air flows along the fuel-air premixing pipe.
Optionally, the fuel spray holes include a first fuel spray hole and a second fuel spray hole, and the first fuel spray hole and the second fuel spray hole are staggered on a circumferential plane.
Optionally, the fuel flow channels are radially arranged outwards from the fuel delivery manifold.
Optionally, the fuel outlet holes are distributed in a circular ring shape along the circumferential direction.
Optionally, the plurality of fuel air premix 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 combustion chamber.
Optionally, the gas turbine combustor nozzle further comprises a rectifying hole and an outer wall,
the outer wall is arranged at the downstream of the rectifying hole and surrounds a nozzle chamber;
air enters the fuel air premix tube from the rectifying hole;
the outlet end of the fuel flow channel is arranged on the outer wall;
the fuel enters the nozzle chamber through the fuel runner and then enters the fuel-air premixing tube through the fuel spray hole.
Optionally, the gas turbine combustor nozzle is manufactured by adopting an additive manufacturing processing technology method.
To achieve the above object, the present invention also provides a method for premixing fuel and air in a gas turbine combustor nozzle, comprising:
the fuel is introduced from the fuel delivery manifold,
enters the fuel flow passage through the fuel outlet hole,
the air entering the fuel air premixing tube through the fuel spray holes is mixed with the air entering in advance to form a mixture, and the mixture is sprayed out of the fuel air premixing tube.
Optionally, air enters the fuel air premix tube from the rectifying holes.
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 varying the size of the inner diameter of the fuel air premix tube.
Optionally, the flow rate of the fuel into the fuel-air premix tube is varied by adjusting the size of the fuel injection holes on the fuel-air premix tube.
Optionally, the rotation strength of the fuel entering the fuel-air premixing tube is changed by adjusting the distance between the fuel spray hole and the central line of the fuel-air premixing tube.
The gas turbine combustor nozzle and the method for premixing fuel and air in the nozzle have the beneficial effects 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 enable fuel and air to be mixed rapidly, and compared with a traditional nozzle premixing structure for spraying by the blades of the cyclone, the axial length of the special premixing structure can be shortened by 30-50%.
3. The structure of the combustion chamber is simpler by the circumferential deflection at the outlet of the premix tube instead of the swirler structure.
4. The multi-premix tube structure has certain capability of absorbing thermoacoustic oscillations, and contributes to improving the thermoacoustic oscillation characteristics of the combustion chamber.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain 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 a gas turbine combustor nozzle of the present invention;
FIG. 4 is a cross-sectional view of a fuel air premix tube of a gas turbine combustor nozzle of the present invention;
FIG. 5 is a cross-sectional view of a fuel air premix tube of a 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 a fuel air premix tube of a gas turbine combustor nozzle of the present invention;
FIG. 8 is a cross-sectional view III of a fuel air premix tube of a gas turbine combustor nozzle of the present invention;
FIG. 9 is a cross-sectional view of a fuel air premix tube of a gas turbine combustor nozzle of the present invention;
FIG. 10 is a second cross-sectional view of a fuel air premix tube of a gas turbine combustor nozzle of the present invention;
FIG. 11 is a flow chart of a fuel and air premixing method according to example 6 of the present invention;
FIG. 12 is a flow chart of a fuel and air premixing method according to example 7 of the present invention;
FIG. 13 is a flow chart of a fuel and air premixing method according to example 8 of the present invention;
FIG. 14 is a flow chart of a fuel and air premixing method according to example 9 of the present invention;
FIG. 15 is a flow chart of a fuel and air premixing method according to example 10 of the present invention;
FIG. 16 is a flow chart of a fuel and air premixing method according to example 11 of the present invention.
Detailed Description
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
The invention is described in further detail below in connection with specific examples which are not to be construed as limiting the scope of the invention as claimed.
Example 1
As shown in fig. 3-4, the gas turbine combustor nozzle 100 is divided into three sections, namely a fuel delivery manifold 1, a fuel runner 2, and a fuel air premix tube 3.
The diameter of the fuel conveying main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlet holes 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel conveying main pipe 1, the fuel outlet holes 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet hole 12 corresponds to at least one fuel runner 2. The fuel flow channels 2 are arranged in a radial manner by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel flow channels 2 on the same layer have the same axial angle with the fuel delivery manifold 1.
The fuel air premixing tubes 3 are distributed in a plurality of rows from the center to the outer side along the radial direction of the nozzle 100 and are parallel to each other. A fuel injection hole 31 for injecting fuel into the fuel-air premixing tube 3 is provided upstream of the fuel-air premixing tube 3.
The gas turbine combustor nozzle 100 also includes a swirl hole 4 and an outer wall 5. The rectifying holes 4 are arranged on the surface of the cone on the inner side of the fuel flow channel 2, and are uniformly distributed in a plurality of rows from inside to outside along the radial direction by taking the axial direction of the fuel conveying main pipe 1 as the center. The air is quickly split after entering the gas turbine combustor nozzle 100 through the rectifying hole 4 at the air suction end, and is uniformly mixed with the fuel in the fuel-air premixing tube 3.
The outer wall 5 is disposed downstream of the orifice 4, forming a nozzle chamber 6 around the nozzle 100. Air enters the fuel air premix tube 3 from the rectification holes 4; the outlet end of the fuel flow passage 2 is arranged around the circumference of the outer wall 5. Fuel enters the nozzle chamber 6 through the fuel flow passage 2 and then enters the fuel-air premixing tube 3 through the fuel injection holes 31 (see fig. 5).
Alternatively, 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 combustion chamber.
Alternatively, the gas turbine combustor nozzle 100 is manufactured using additive manufacturing processes.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters from the fuel conveying main pipe 1, enters the fuel flow channel 2 through the fuel outlet hole 12, enters the fuel air premixing tube 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 tube 3.
Example 2
As shown in fig. 3-4, the gas turbine combustor nozzle 100 is divided into three sections, namely a fuel delivery manifold 1, a fuel runner 2, and a fuel air premix tube 3.
The diameter of the fuel conveying main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlet holes 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel conveying main pipe 1, the fuel outlet holes 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet hole 12 corresponds to at least one fuel runner 2. The fuel flow channels 2 are arranged in a radial manner by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel flow channels 2 on the same layer have the same axial angle with the fuel delivery manifold 1.
The fuel air premixing tubes 3 are distributed in a plurality of rows from the center to the outer side along the radial direction of the nozzle 100 and are parallel to each other. A fuel injection hole 31 for injecting fuel into the fuel-air premixing tube 3 is provided upstream of the fuel-air premixing tube 3.
Alternatively, 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 combustion chamber.
Alternatively, the gas turbine combustor nozzle 100 is manufactured using additive manufacturing processes.
In this embodiment, as shown in fig. 5, the fuel air premixing tube 3 includes an output tube portion 32, and the output tube portion 32 is deflected at a predetermined angle α in a clockwise or counterclockwise direction along the circumferential direction to form a swirling structure. FIG. 6 shows an exterior view of the nozzle with the outlet duct 32 deflected at an angle α in a clockwise direction from the direction of inflow of air from the gas turbine combustor nozzle. This structure can form a circumferential swirling flow of the fuel-air mixture ejected from the output pipe portion 32 of the fuel-air premixing tube 3 in the downstream space direction, enhancing the premixing effect of the fuel and air.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters from the fuel conveying main pipe 1, enters the fuel flow channel 2 through the fuel outlet hole 12, enters the fuel air premixing tube 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 tube 3. The output pipe 32 of the fuel air premixing tube 3 can spray rotary airflow downstream by deflecting an angle alpha, so that the premixing effect of fuel and air is effectively enhanced. Meanwhile, the structure can jet out rotary air flow, and can replace a cyclone structure in the traditional scheme, so that the mechanical structure of the combustion chamber is simpler.
Example 3
As shown in fig. 3-4, the gas turbine combustor nozzle 100 is divided into three sections, namely a fuel delivery manifold 1, a fuel runner 2, and a fuel air premix tube 3.
The diameter of the fuel conveying main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlet holes 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel conveying main pipe 1, the fuel outlet holes 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet hole 12 corresponds to at least one fuel runner 2. The fuel flow channels 2 are arranged in a radial manner by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel flow channels 2 on the same layer have the same axial angle with the fuel delivery manifold 1.
The fuel air premixing tubes 3 are distributed in a plurality of rows from the center to the outer side along the radial direction of the nozzle 100 and are parallel to each other. A fuel injection hole 31 for injecting fuel into the fuel-air premixing tube 3 is provided upstream of the fuel-air premixing tube 3.
Alternatively, 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 combustion chamber.
Alternatively, the gas turbine combustor nozzle 100 is manufactured using additive manufacturing processes.
In this embodiment, as shown in fig. 7, the fuel air premixing tube 3 includes a middle tube portion 33 located upstream of the output tube portion 32, the output tube portion 32 deflects with respect to the middle tube portion 33, and the output tube portion 32 deflects in a circumferential clockwise or counterclockwise direction by a preset angle α, forming a swirling structure. This structure can form a circumferential swirling flow of the fuel-air mixture ejected from the output pipe portion 32 of the fuel-air premixing tube 3 in the downstream space direction, enhancing the premixing effect of the fuel and air.
Fig. 7 shows the angle of deflection α of the outlet pipe 32 of each fuel premix pipe 3 relative to the intermediate pipe 33.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters from the fuel conveying main pipe 1, enters the fuel flow channel 2 through the fuel outlet hole 12, enters the fuel air premixing tube 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 tube 3. The output pipe 32 of the fuel air premixing tube 3 can spray rotary airflow downstream by deflecting an angle alpha, so that the premixing effect of fuel and air is effectively enhanced. Meanwhile, the structure can jet out rotary air flow, and can replace a cyclone structure in the traditional scheme, so that the mechanical structure of the combustion chamber is simpler.
Example 4
As shown in fig. 3-4, the gas turbine combustor nozzle 100 is divided into three sections, namely a fuel delivery manifold 1, a fuel runner 2, and a fuel air premix tube 3.
The diameter of the fuel conveying main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlet holes 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel conveying main pipe 1, the fuel outlet holes 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet hole 12 corresponds to at least one fuel runner 2. The fuel flow channels 2 are arranged in a radial manner by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel flow channels 2 on the same layer have the same axial angle with the fuel delivery manifold 1.
The fuel air premixing tubes 3 are distributed in a plurality of rows from the center to the outer side along the radial direction of the nozzle 100 and are parallel to each other. A fuel injection hole 31 for injecting fuel into the fuel-air premixing tube 3 is provided upstream of the fuel-air premixing tube 3.
Alternatively, 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 combustion chamber.
Alternatively, the gas turbine combustor nozzle 100 is manufactured using additive manufacturing processes.
In this embodiment, as shown in fig. 7, in order to further promote uniform mixing of the fuel and air, the middle pipe portion 33 of the fuel-air premixing pipe 3 is a rahal nozzle structure B. The Lafaer spray tube type structure B is an integral structure composed of a shrinkage tube on the left side and an expansion tube on the right side. The structure can change the speed of the air flow due to the change of the spray sectional area. In this embodiment, the shrink tube may further promote a uniform degree of mixing of the fuel and air, and the subsequent expansion structure may be advantageous in reducing the flow pressure loss of the fuel-air premix tube 3.
Alternatively, the throat area of the Laval nozzle may be adjusted to control the mixture ratio in each fuel-air premixing tube 3.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters from the fuel conveying main pipe 1, enters the fuel flow channel 2 through the fuel outlet hole 12, enters the fuel air premixing tube 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 tube 3. The Laval-structured nozzle B of the output pipe 32 of the fuel-air premixing tube 4 effectively increases the degree of mixing of fuel and air by the contracting and expanding structure and reduces the flow pressure loss of the mixture to the fuel-air premixing tube.
Example 5
As shown in fig. 3-4, the gas turbine combustor nozzle 100 is divided into three sections, namely a fuel delivery manifold 1, a fuel runner 2, and a fuel air premix tube 3.
The diameter of the fuel conveying main pipe 1 is changed from small to large according to the fuel flow direction, a plurality of fuel outlet holes 12 are circumferentially arranged on a cylindrical structure with a fixed radius of the fuel conveying main pipe 1, the fuel outlet holes 12 are uniformly distributed in a circular ring shape at equal intervals, and each fuel outlet hole 12 corresponds to at least one fuel runner 2. The fuel flow channels 2 are arranged in a radial manner by taking the axis of the fuel conveying main pipe 1 as a geometric center. The fuel flow channels 2 on the same layer have the same axial angle with the fuel delivery manifold 1.
The fuel air premixing tubes 3 are distributed in a plurality of rows from the center to the outer side along the radial direction of the nozzle 100 and are parallel to each other. A fuel injection hole 31 for injecting fuel into the fuel-air premixing tube 3 is provided upstream of the fuel-air premixing tube 3.
Alternatively, 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 combustion chamber.
Alternatively, the gas turbine combustor nozzle 100 is manufactured using additive manufacturing processes.
In the present embodiment, as shown in fig. 8, the fuel-air premixing tube 3 includes a middle tube portion 33 upstream of the output tube portion 32, and an input tube portion 34 upstream of the middle tube portion 33. Fig. 9 is a cross-sectional view of a fuel-air premixing tube, in which two fuel injection holes 31, namely a first fuel injection hole 331 and a second fuel injection hole 332, are provided in the inlet tube portion 34, and are arranged offset from each other on the circumferential plane of the fuel-air premixing tube 3. Fuel enters the fuel-air premixing tube 3 from both directions f1 and f2 through the first fuel injection hole 331 and the second fuel injection hole 332, respectively. As shown in fig. 10, the eccentricity of the first fuel injection hole 331 and the center line of the fuel-air premixing tube 3 is L1, and the eccentricity of the second fuel injection hole 332 and the center line of the fuel-air premixing tube 3 is L2. By adjusting L1 and L2, the fuel bundle rotation intensity can be changed.
Alternatively, the directions f1 and f2 in which the fuel enters the fuel-air premixing tube 3 are perpendicular to the direction in which the air flows along the fuel-air premixing tube 3.
When the gas turbine combustion chamber nozzle is in an operating state, fuel enters from the fuel conveying main pipe 1, enters the fuel flow channel 2 through the fuel outlet hole 12, enters the fuel air premixing tube 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 tube 3. This design allows the fuel to create a swirling flow of fuel gas in the fuel-air premix tube 3 and to be ejected from the output pipe 32 of the fuel-air premix tube 3, effectively accelerating the mixing speed and uniformity of the fuel and air.
Example 6
A method of premixing fuel and air in a gas turbine combustor nozzle is also disclosed.
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 path 2 through the fuel outlet 12 in the fuel delivery manifold 1.
Step S2: the fuel enters the fuel-air premixing tube 3 through the fuel injection hole 31.
Step S3: the fuel entering the fuel-air premixing tube 3 is mixed with air previously entered therein to form a mixture, and the mixture is ejected from the fuel-air premixing tube 3.
According to the embodiment of the invention, fuel enters the nozzle 100 from the fuel conveying main pipe 1, enters the fuel-air premixing tube 3 through the fuel flow channel 2, enters the fuel-air premixing tube 3 through the fuel spray hole 31 to be mixed with air, and finally, the mixture formed by mixing the fuel and the air enters the combustion chamber through the output pipe part 32 of the fuel-air premixing tube 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 rectification holes 4.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow path 2 through the fuel outlet 12 in the fuel delivery manifold 1.
Step S2: the fuel enters the fuel-air premixing tube 3 through the fuel injection hole 31.
Step S3: the fuel entering the fuel-air premixing tube 3 is mixed with air previously entered therein to form a mixture, and the mixture is ejected from the fuel-air premixing tube 3.
In the embodiment of the invention, fuel enters the nozzle from the fuel conveying main pipe 1, enters the fuel-air premixing tube 3 through the fuel flow channel 2, enters the fuel-air premixing tube 3 through the fuel spray hole 31 to be mixed with air, and finally, the mixture formed by mixing the fuel and the air enters the combustion chamber through the output pipe part 32 of the fuel-air premixing tube 3. The design effectively improves the premixing uniformity of the fuel and the air through the double-flow-path structure of the fuel and the air.
Example 8
The output pipe 32 of the fuel air premixing tube 3 is of a Laval nozzle structure.
As shown in fig. 13, the method includes:
step S5: the throat of the Laval nozzle structure is sized to promote fuel and air mixing.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow path 2 through the fuel outlet 12 in the fuel delivery manifold 1.
Step S2: the fuel enters the fuel-air premixing tube 3 through the fuel injection hole 31.
Step S3: the fuel entering the fuel-air premixing tube 3 is mixed with air previously entered therein to form a mixture, and the mixture is ejected from the fuel-air premixing tube 3.
According to the embodiment of the invention, the throat size of the Laval structure spray pipe C is set, so that the mixing of fuel and air is promoted, and the premixing uniformity of the fuel and air in the spray nozzle is improved.
Example 9
As shown in fig. 14, the method includes:
step S6: the inner diameter of the fuel-air premixing tube 3 is adjusted.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow path 2 through the fuel outlet 12 in the fuel delivery manifold 1.
Step S2: the fuel enters the fuel-air premixing tube 3 through the fuel injection hole 31.
Step S3: the fuel entering the fuel-air premixing tube 3 is mixed with air previously entered therein to form a mixture, and the mixture is ejected from the fuel-air premixing 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 tube 3 and the flow rate 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 premixing tube 3 is adjusted.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow path 2 through the fuel outlet 12 in the fuel delivery manifold 1.
Step S2: the fuel enters the fuel-air premixing tube 3 through the fuel injection hole 31.
Step S3: the fuel entering the fuel-air premixing tube 3 is mixed with air previously entered therein to form a mixture, and the mixture is ejected from the fuel-air premixing tube 3.
According to the embodiment of the invention, the flow rate of the fuel entering the fuel-air premixing tube 3 is changed by adjusting the size of the fuel spray hole 31 on the fuel-air premixing tube 3, so that the ratio of the fuel to the air is effectively controlled, and the mixing uniformity of the fuel and air mixture is optimized.
Example 11
As shown in fig. 16, the method includes:
step S8: the distance between the fuel injection hole 31 and the center line of the fuel air pre-mixing pipe 3 is adjusted.
Step S1: fuel enters the nozzle 100 from the fuel delivery manifold 1 and enters the fuel flow path 2 through the fuel outlet 12 in the fuel delivery manifold 1.
Step S2: the fuel enters the fuel-air premixing tube 3 through the fuel injection hole 31.
Step S3: the fuel entering the fuel-air premixing tube 3 is mixed with air previously entered therein to form a mixture, and the mixture is ejected from the fuel-air premixing tube 3.
In the embodiment of the invention, the rotation intensity of the fuel entering the fuel-air premixing tube 3 is changed by adjusting the distance between the fuel spray hole 31 and the central line of the fuel-air premixing tube 3, so as to control the mixing speed and uniformity of the fuel and the air.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (20)
1. A gas turbine combustor nozzle (100) is characterized by comprising a fuel conveying main pipe (1), a fuel runner (2) and a fuel air premixing pipe (3),
the fuel delivery manifold (1) is provided with a plurality of fuel outlet holes (12);
each fuel outlet hole (12) corresponds to at least one fuel runner (2);
the fuel air premixing tube (3) is provided with a plurality of fuel spray holes (31), wherein the fuel air premixing tube (3) comprises an output tube part (32), an intermediate tube part (33) positioned upstream of the output tube part (32) and an input tube part (34) positioned upstream of the intermediate tube part (33), and the fuel spray holes (31) are arranged on the side surface of the input tube part (34);
fuel enters from the fuel conveying main pipe (1), enters into the fuel flow channel (2) through the fuel outlet hole (12), enters into the fuel air premixing tube (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 tube (3);
the gas turbine combustor nozzle (100) further comprises a rectifying hole (4) and an outer wall (5),
the outer wall (5) is arranged at the downstream of the rectifying hole (4) and surrounds a nozzle chamber (6);
air enters the fuel air premixing tube (3) from the rectifying hole (4);
the outlet end of the fuel runner (2) is arranged on the outer wall (5);
the fuel enters the nozzle chamber (6) through the fuel runner (2) and then enters the fuel-air premixing tube (3) through the fuel spray hole (31).
2. The gas turbine combustor nozzle (100) of claim 1, wherein the fuel air premix tube (3) is provided with a swirl structure that ejects the mixture in a swirling flow.
3. The gas turbine combustor nozzle (100) of claim 2, wherein the fuel air premix tube (3) comprises an output tube portion (32), the output tube portion (32) being deflected at a predetermined angle in a circumferential direction as the swirl structure such that the mixture ejected from the fuel air premix tube (3) forms a swirling air flow in a predetermined circumferential direction.
4. A gas turbine combustor nozzle (100) according to claim 3, wherein each output pipe (32) of the fuel air premix tube (3) is deflected clockwise or counter-clockwise in circumferential direction.
5. The gas turbine combustor nozzle (100) of claim 3, wherein the fuel air premix tube (3) comprises an intermediate tube portion (33) upstream of the output tube portion (32), the output tube portion (32) being deflected relative to the intermediate tube portion (33).
6. The gas turbine combustor nozzle (100) of claim 3, wherein the intermediate tube portion (33) of the fuel air premix tube (3) comprises a raval nozzle structure.
7. The gas turbine combustor nozzle (100) of claim 5, wherein the fuel air premix tube (3) comprises an inlet tube portion (34) upstream of the intermediate tube portion (33), the fuel injection orifice (31) being disposed in the inlet tube portion (34).
8. The gas turbine combustor nozzle (100) of claim 7, wherein the fuel injection holes (31) are disposed on a side of the input pipe portion (34) such that a direction in which the fuel enters the fuel-air premix pipe (3) is perpendicular to a direction in which air flows along the fuel-air premix pipe (3).
9. The gas turbine combustor nozzle (100) of claim 7, wherein the fuel injection holes (31) comprise first fuel injection holes (311) and second fuel injection holes (312), the first fuel injection holes (311) and the second fuel injection holes (312) being staggered in a circumferential plane.
10. The gas turbine combustor nozzle (100) of claim 1, wherein the fuel flow channels (2) are radially arranged outwardly from the fuel delivery manifold (1).
11. The gas turbine combustor nozzle (100) of claim 1, wherein the fuel outlets (12) are circumferentially distributed in a ring shape.
12. The gas turbine combustor nozzle (100) of claim 1, wherein the plurality of fuel air premix tubes (3) are parallel to each other.
13. The gas turbine combustor nozzle of any one of claims 1-7, wherein 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 combustor.
14. The gas turbine combustor nozzle (100) of claim 1, wherein the gas turbine combustor nozzle (100) is manufactured using an additive manufacturing process.
15. A method of premixing fuel and air in a gas turbine combustor nozzle, the method being applied to a gas turbine combustor nozzle (100) as claimed in any one of claims 1 to 14, comprising:
the fuel enters from the fuel conveying main pipe (1), enters into the fuel flow channel (2) through the fuel outlet hole (12), enters into the fuel air premixing tube (3) through the fuel spray hole (31) and is mixed with air which enters in advance to form a mixture, and the mixture is sprayed out from the fuel air premixing tube (3).
16. The method as recited in claim 15, comprising:
air enters the fuel air premixing tube (3) from the rectifying hole (4).
17. The method as recited in claim 15, 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.
18. The method as recited in claim 15, comprising:
the flow rate of the mixture is adjusted by varying the size of the inner diameter of the fuel-air premixing tube (3).
19. The method as recited in claim 15, comprising:
by adjusting the size of the fuel injection holes (31) on the fuel air premix tube (3), the flow rate of the fuel into the fuel air premix tube (3) is changed.
20. The method as recited in claim 15, comprising:
the rotation intensity of the fuel entering the fuel air premixing tube (3) is changed by adjusting the distance between the fuel spray hole (31) and the central line of the fuel air premixing tube (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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| CN113091094B true CN113091094B (en) | 2023-05-23 |
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| CN113551263B (en) * | 2021-07-21 | 2023-02-24 | 中国联合重型燃气轮机技术有限公司 | Nozzle head for gas turbine and nozzle for gas turbine |
| CN113483358B (en) * | 2021-07-21 | 2023-02-21 | 中国联合重型燃气轮机技术有限公司 | Nozzle head for gas turbine and nozzle for gas turbine |
| CN113483359B (en) * | 2021-07-21 | 2023-02-24 | 中国联合重型燃气轮机技术有限公司 | Nozzle head for gas turbine and nozzle for gas turbine |
| CN113739205B (en) * | 2021-09-06 | 2022-12-23 | 中国联合重型燃气轮机技术有限公司 | Gas turbine, and method and device for controlling combustion chamber of gas turbine |
| KR102599921B1 (en) * | 2022-03-21 | 2023-11-07 | 두산에너빌리티 주식회사 | Nozzle for combustor, combustor, and gas turbine including the same |
| CN114857619B (en) * | 2022-04-29 | 2024-01-26 | 江苏中科能源动力研究中心 | Micro-mixed combustion chamber of gas turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US5408830A (en) * | 1994-02-10 | 1995-04-25 | General Electric Company | Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines |
| US20120180487A1 (en) * | 2011-01-19 | 2012-07-19 | General Electric Company | System for flow control in multi-tube fuel nozzle |
| CN102878580B (en) * | 2012-09-12 | 2015-04-22 | 中国科学院工程热物理研究所 | Lean premixed combustion chamber for gas turbine |
| JP6228434B2 (en) * | 2013-11-15 | 2017-11-08 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
| CN107110505B (en) * | 2014-10-20 | 2020-12-18 | 安萨尔多能源公司 | Gas turbine unit with multi-fluid fuel supply and method for supplying a burner of a gas turbine unit |
| JP6822894B2 (en) * | 2017-04-28 | 2021-01-27 | 三菱パワー株式会社 | Fuel injector and gas turbine |
| KR102046457B1 (en) * | 2017-11-09 | 2019-11-19 | 두산중공업 주식회사 | Combustor and gas turbine including the same |
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