JP2002213746A - Burner, premix fuel nozzle of combustor, and an combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a burner, in which discharge of NOx generated from combustion of a liquid fuel can be reduced. SOLUTION: A main burner 20 comprises a main fuel-supply pipe 21 disposed along the air-flow path, and a main swirler 30 to produce a swirled air-flow around the main fuel-supply pipe 21. In the main fuel supply pipe 21, a liquid-fuel supply path 22 connected to a liquid fuel supply source and a gas-fuel supply path 23 connected to a gas fuel supply source are formed. The liquid fuel and the gas fuel supplied to the pipe 21 are injected in the air-flow to be burned to perform a dual fuel combustion. In the burner 20, a liquid-fuel flow-path part 31 communicating with the supply path 22 is formed in the inside of the main swirler 30, and a slit 32 for injecting the liquid from the flow-path part 31 to the air-flow is formed to open in the main swirler 30.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a burner for burning a liquid fuel alone or a combination of a liquid fuel and a gas fuel, a premixing nozzle of a combustor, and a combustor. The present invention relates to a technique suitable for use in reducing the amount of NOx emitted by a fuel cell.

[0002]

2. Description of the Related Art In recent years, gas turbines and other devices which compress a gas serving as a working fluid by a compressor, heat the gas, and expand the generated high-temperature and high-pressure gas in the turbine to extract the shaft output to the outside have been recently used. Due to environmental problems, reduction of emissions such as nitrogen oxides (NOx) is required.
Such a gas turbine includes a compressor, a combustor, and a turbine as main components, and the compressor and the turbine are directly connected to each other via a main shaft. A combustor is connected to the discharge port of the compressor, and the working fluid discharged from the compressor is
The combustor heats up to a predetermined turbine inlet temperature. The high-temperature, high-pressure working fluid supplied to the turbine passes through the space between the stationary blade and the moving blade attached to the main shaft in the casing and expands, whereby the main shaft rotates to obtain an output. In the case of a gas turbine, a shaft output obtained by subtracting the power consumed by the compressor is obtained, so that it can be used as a drive source by connecting a generator or the like to the other end of the main shaft.

In the above-described gas turbine and the like, a burner that atomizes liquid fuel such as oil and burns it alone, or a dual fuel-fired burner that burns liquid fuel and gas fuel in combination is used for the combustor. Some have been used. Therefore, a conventional combustor used for a gas turbine or the like is shown in FIG. 7 and its configuration will be briefly described. This combustor 10 has a premixing nozzle 12 installed along the axial center of a cylindrical body (hereinafter referred to as an inner cylinder) 11 on the inside. The premixing nozzle 12 is provided with a pilot burner 13 at a central portion, and a plurality of (eight sets in the illustrated example) main burners 1 are arranged at equal pitches so as to surround the pilot burner 13. I have. Therefore, the pilot burner 13
Of the inner cylinder 11 coincides with the axial center of the inner cylinder 11.

The pilot burner 13 of the premix nozzle 12
Is a pilot fuel pipe 14 and a pilot swirler 15
And is provided. The pilot fuel pipe 14 has one end connected to a fuel supply source (not shown) and the other end connected to the inner cylinder 11.
The pilot fuel nozzle 14a opens to the combustion chamber 10a of the combustor 10 formed by the above. The pilot swirler 15 is provided on the outer peripheral portion of the pilot fuel pipe 14 and imparts a swirl to an air flow (indicated by an outline arrow) passing therethrough. In this pilot burner 13,
The pilot fuel supplied from the pilot fuel nozzle 14a burns in the combustion chamber 10a using the swirling airflow as combustion air. The flame of the pilot burner 13 formed in this manner is used as a fire for the main burner 1 described later.

The main burner 1 of the premix nozzle 12 has a main fuel supply pipe (fuel supply pipe) 2 connected to a fuel supply source (not shown) and air passing through an outer peripheral portion of the main fuel supply pipe 2. And a main swirler (swirler blade) 5 for imparting swirl to the flow. The plurality of main burners 1 have the same configuration. The main burner 1 ejects the fuel introduced through the main fuel supply pipe 2 into the air flow from the fuel outlet, and premixes the fuel and the air flow to form a premixed gas. The premixed gas flows from each of the main burners 1 as a swirling flow to flow out around the pilot burner 13, and the above-described pilot burner 1
The flame of No. 3 is burned as a fire. Note that reference numeral 16 in FIG.
Is an outer cylinder which is disposed outside the inner cylinder 11 and forms an airflow introduction path which is inverted by 180 degrees.

[0006] For such a conventional main burner 1, for example, a dual fuel-fired burner as shown in Fig. 8 is used, and its configuration will be briefly described below. The main burner 1 has a liquid fuel supply passage 3 inside a main fuel supply pipe 2 disposed along a passage of an air flow as a fuel nozzle.
And a gas fuel supply passage 4. Each of the passages is provided with a liquid fuel ejection port 3 a and a gas fuel ejection port 4 a for ejecting fuel into an air flow. Around the fuel supply pipe 2, a main swirler 5 for turning the passing airflow is disposed.

In the main burner 1 configured as described above, the liquid fuel is atomized and ejected from the liquid fuel injection port 3a into the swirling airflow passing through the main swirler 5. Further, since the gas fuel is jetted from the gas fuel jet port 4a into the swirling airflow, the atomized liquid fuel and the gas fuel can be burned together. In the case of the combustor 10 used in a gas turbine, usually, gas fuel is mainly used and the liquid fuel is combusted supplementarily. However, in the combustor used in fields other than the gas turbine, only the liquid fuel is used. Some burn.

[0008]

By the way, in the above-mentioned conventional main burner 1, the liquid fuel is supplied to the air flow passing through the main swirler 5 from the liquid fuel injection port 3a opened near the tip of the main fuel supply pipe 2. The fuel is sprayed, and N atom is obtained by burning atomized liquid fuel.
Ox is reduced. However, since the atomization of the liquid fuel is limited only by injecting the liquid fuel into the air flow from the hole of the liquid fuel injection port 3a, the above-described main burner 1 of the conventional configuration has a limitation in reducing the NOx. Was.

SUMMARY OF THE INVENTION The present invention has been made in view of the above circumstances, and provides a premixing nozzle and a combustor which achieves a reduction in NOx emission of a burner for burning liquid fuel and also has such a burner. It is the purpose.

[0010]

The present invention employs the following means in order to solve the above-mentioned problems. In the burner according to the first aspect, a fuel supply pipe having a liquid fuel supply passage connected to a liquid fuel supply source is arranged along a flow path of the air flow, and the air flow is provided around the fuel supply pipe. A swirler blade for swirling, wherein the burner blows liquid fuel supplied to the fuel supply pipe into the air flow and burns the fuel, and communicates with the liquid fuel supply passage inside the swirler blade. A liquid fuel flow path is formed, and a liquid fuel supply port for ejecting liquid fuel from the liquid fuel flow path to the air flow is provided in the swirler blade.

According to such a burner, since the liquid fuel supply port opened to the swirler blade is provided, the kinetic energy of the air flowing along the swirler blade is effectively used to promote the atomization of the liquid fuel, By burning the liquid fuel which has been further atomized, the emission amount of NOx can be reduced.

According to a second aspect of the present invention, there is provided a burner in which a fuel supply pipe having a liquid fuel supply passage connected to a liquid fuel supply source and a gas fuel supply passage connected to a gas fuel supply source is provided with an air flow passage. And a swirler vane for swirling the air flow around the fuel supply pipe. The liquid fuel and the gas fuel supplied to the fuel supply pipe are jetted into the air flow and burned. A liquid fuel passage that communicates with the liquid fuel supply passage inside the swirler vane, and a liquid that ejects liquid fuel from the liquid fuel passage to the air flow. A fuel supply port is provided so as to open to the swirler blade.

According to such a burner, since the liquid fuel supply port which opens to the swirler blade is provided, the kinetic energy of the air flowing along the swirler blade is effectively used to promote the atomization of the liquid fuel, By burning the liquid fuel which has been further atomized, the emission amount of NOx can be reduced.

In the above-mentioned burner according to claim 1 or 2, the liquid fuel supply port preferably includes a slit opening at a trailing edge of the swirler blade, and one or more slits opening at a blade surface of the swirler blade. Small holes,
Alternatively, there is a slit that opens along the wing surface of the swirler wing. In the burner according to claim 1 or 2, the swirler blade may be made of a sintered metal. Further, in the above-described burner, a connecting vane is provided between the swirler vanes, and a connecting passage portion communicating with the liquid fuel passage portion is formed in the connecting vane. A liquid fuel supply port for injecting liquid fuel into the connecting vane may be provided in the connecting vane.

[0015] The premixing nozzle of the combustor according to claim 8 is a pilot burner arranged on a central axis, and arranged as a main burner around the pilot burner. And a burner.

According to such a premixing nozzle of the combustor, since the main burner having the liquid fuel supply port opened to the swirler blade is employed, the kinetic energy of the air flowing along the swirler blade is effectively used. Thus, the atomization of the liquid fuel is promoted, and the combustion of the further atomized liquid fuel makes it possible to reduce the emission amount of NOx.

According to a ninth aspect of the present invention, there is provided a combustor comprising: the premixing nozzle according to the eighth aspect; and a cylinder housing the premixing nozzle.

According to such a combustor, since the premixing nozzle of the combustor having the liquid fuel supply port opened to the swirler blade is employed, the kinetic energy of the air flowing along the swirler blade is effectively utilized. To promote the atomization of liquid fuel,
Combustion of liquid fuel that has been further atomized makes NO
x emission can be reduced.

[0019]

DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described below with reference to the drawings. As described in the related art, the gas turbine, the jet engine, and the like each include a compressor, a combustor, and a turbine as main components. The compressor introduces and compresses a gas serving as a working fluid, that is, air, and supplies the compressed air to the combustor. As this compressor, an axial compressor directly connected to a turbine by a main shaft is used. The compressor compresses air (atmosphere) sucked from a suction port and supplies it to a combustor connected to a discharge port. This air stream burns fuel in the combustor,
The generated high-temperature and high-pressure gas is supplied to the turbine.

Here, a configuration example of a combustor which is a component of a gas turbine, a jet engine, and the like will be described with reference to FIG. This combustor 10 has a premixing nozzle 12 installed along the axial center of a cylindrical body (hereinafter referred to as an inner cylinder) 11 on the inside. The premixing nozzle 12 has a pilot burner 13 disposed at a central portion coinciding with the center axis thereof, and a plurality (for example, eight sets) of main burners 20 are arranged at equal pitches so as to surround the pilot burner 13. Has been established. Therefore, the center axis of the pilot burner 13 coincides with the axis center of the inner cylinder 11.

The pilot burner 13 of the premix nozzle 12
Is a pilot fuel pipe 14 and a pilot swirler 15
And is provided. One end of the pilot fuel pipe 14 is connected to a pilot fuel supply source (not shown), and the other end is a pilot fuel nozzle 14 a that opens to a combustion chamber 10 a of the combustor 10 formed by the inner cylinder 11. The pilot swirler 15 is provided on an outer peripheral portion of the pilot fuel pipe 14, and gives a swirl to a passing air flow (indicated by a white arrow) to provide a pilot fuel nozzle 14.
It blows out around a. In the pilot burner 13, the pilot fuel supplied from the pilot fuel nozzle 14a burns in the combustion chamber 10a using the swirling airflow as combustion air. The flame of the pilot burner 13 formed in this way is used as a fire for the main burner 20 described later.

The main burner 20 of the premix nozzle 12 is
A main fuel supply pipe (fuel supply pipe) 21 connected to a main fuel supply source (not shown), and a main swirler (swirler blade) 30 for giving a swirl to an airflow passing through an outer peripheral portion of the main fuel supply pipe 21 are provided. It is provided and comprised. The plurality of main burners 20 have the same configuration.

Next, the configuration of the main burner 20 will be described in detail. <First Embodiment> A main burner 20 shown in FIG. 1 is a so-called dual fuel-fired burner. A liquid fuel supply passage connected to a liquid fuel supply source (not shown) is provided inside a main fuel supply pipe 21. 22 and a gas fuel supply passage 23 also connected to a gas fuel supply source (not shown) are formed independently of each other. The main fuel supply pipe 21 is arranged along the flow path of the air flow indicated by the white arrow, and a plurality of main swirlers 30 for rotating the air flow are arranged around the main fuel supply pipe 21 in the circumferential direction.

The liquid fuel supply passage 22 is a gas fuel supply passage 2 provided along the axial center of the main fuel supply pipe 21.
3 is provided on the outer peripheral side. Also, main swirler 3
0 is connected to a main fuel supply pipe 21, and inside the main swirler 30, a liquid fuel supply passage 22 is provided.
A space communicating with the liquid fuel passage 31 is formed as a liquid fuel passage 31. The liquid fuel flow path 31 is provided with a slit 32 that opens to the trailing edge of the main swirler 30 as a liquid fuel supply port for ejecting liquid fuel from the liquid fuel flow path 31 to the air flow. A gas fuel supply port 24 is provided at the tip of the gas fuel supply passage 23 to eject gas fuel into the swirling airflow that has passed through the main swirler 30.

With the main burner 20 having the above-described configuration, one of the gas fuels is guided to the gas fuel supply port 24 through the gas fuel supply passage 23, and the air that has turned into a swirling flow from the gas fuel supply port 24. Spouts into the flow. The other liquid fuel is guided through the liquid fuel supply passage 22 to the liquid fuel flow path 31 in the main swirler 30, and is jetted into the air flow over a wide range from the slit 32 opened at the trailing edge. For this reason, the atomization of the liquid fuel ejected from the slit 32 is promoted by effectively utilizing the kinetic energy of the air flow that is swirled by passing through the main swirler 30. The liquid fuel atomized in this manner is uniformly premixed with the gas fuel ejected from the gas fuel supply port 24 by the swirling flow of the air flow.
Emissions can be reduced.

<Second Embodiment> Next, a second embodiment of the burner according to the present invention will be described with reference to FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description thereof will be omitted. In this embodiment, a plurality of small holes 33 opening on the blade surface of the main swirler 30 are provided instead of the slit 32 opening on the trailing edge. These small holes 33 penetrate the main swirler 30 from the liquid fuel flow path 31 and are provided on both wing surfaces, and are preferably arranged side by side in the radial direction as shown. In the illustrated example, three small holes 33 are arranged in a line on a straight line orthogonal to the air flow. However, the present invention is not limited to this. It may be arranged in a straight line or curved line with respect to the air flow so as to be located on the wake side,
Alternatively, it can be arranged in two rows or more.

In the main burner 20 having such a structure, the liquid fuel is guided to the liquid fuel flow passage 31 in the main swirler 30 through the liquid fuel supply passage 22, and then the small holes 33 opened on the blade surface. From a wide range to the air stream. For this reason, the liquid fuel ejected from the small holes 33 can promote the atomization by effectively utilizing the kinetic energy of the air flow which is swirled by flowing along the main swirler 30, and further more. Atomization is promoted. The liquid fuel atomized in this way is uniformly premixed with the gas fuel ejected from the gas fuel supply port 24 by the swirling air flow, so that the amount of NOx emitted by combustion can be reduced.

<Third Embodiment> Next, a third embodiment of the burner according to the present invention will be described with reference to FIG. The same parts as those in the first embodiment are denoted by the same reference numerals, and detailed description thereof will be omitted. In this embodiment, instead of the slit 32 opening on the trailing edge, the slit 3 opening on the blade surface of the main swirler 30 is used.
4 are provided. The slit 34 is formed by substantially continuously providing the plurality of small holes 33 in the above-described second embodiment. Therefore, the slits 34 are provided on both wing surfaces through the main swirler 30 from the liquid fuel flow path 31 and are preferably vertically elongated in the radial direction as shown. In the illustrated example, the outer side in the radial direction of the slit 34 is linearly inclined so as to be located on the downstream side of the air flow. However, the present invention is not limited to this. It may be a shape or a curve, or a plurality of shapes may be arranged.

In the main burner 20 having such a configuration, the liquid fuel is guided to the liquid fuel flow passage 31 in the main swirler 30 through the liquid fuel supply passage 22, and then the liquid fuel passes through the slit 34 opened on the blade surface. Spouts into the air stream over a wide area. For this reason, the liquid fuel ejected from the slit 34 flows along the main swirler 30 to effectively utilize the kinetic energy of the air flow that is turned into a swirling flow, so that the atomization can be promoted, and the atomization can be further improved. Atomization is promoted. In addition, such a slit 34 is
As described in the first embodiment, the liquid film is easily formed as compared with the case where the liquid is ejected from the small holes 33. Therefore, the atomization can be further promoted as compared with the case where the liquid fuel supply port of the small holes 33 is used. is there. The liquid fuel thus atomized is
Since the gas fuel ejected from the gas fuel supply port 24 is uniformly premixed by the swirling flow of the air flow, the amount of NOx emitted by combustion can be reduced.

<Fourth Embodiment> Next, a fourth embodiment of a burner according to the present invention will be described with reference to FIG. The same parts as those in the above-described first embodiment are denoted by the same reference numerals, and detailed description thereof will be omitted. In this embodiment, the main swirler 3 is made entirely of a porous sintered metal.
0A is adopted. A liquid fuel flow path 31 communicating with the liquid fuel supply passage 22 is formed inside the main swirler 30A, and the liquid fuel guided to the liquid fuel flow path 31 passes through so as to exude the porosity of the sintered metal. Thus, it is configured that the air is jetted and supplied from almost the entire surface of the wing surface. That is, the liquid fuel supply port in this case has a large number of pores in the sintered metal.

Even in the main burner 20 having such a configuration, the liquid fuel is guided to the liquid fuel passage 31 in the main swirler 30A through the liquid fuel supply passage 22, and then the air flow is spread over a wide range from the blade surface. Supplied to spout. For this reason, the liquid fuel ejected from the main swirler 30A not only passes through the narrow porous flow path, but also effectively utilizes the kinetic energy of the air flow that is swirled by flowing along the main swirler 30A to form fine particles. Can be promoted, and further atomization can be promoted. The liquid fuel atomized in this manner is uniformly premixed with the gas fuel ejected from the gas fuel supply port 24 by the swirling flow of the air flow.
Emissions can be reduced.

<Fifth Embodiment> Next, a burner according to a fifth embodiment of the present invention will be described with reference to FIG. The same reference numerals are given to the same parts as those in the above-described embodiments, and the detailed description will be omitted. In this embodiment, adjacent main swirlers 30 are connected by connecting vanes 35, and a connecting passage portion 36 communicating with the liquid fuel passage portion 31 is formed in the connecting vanes 35. And the connecting wing 35
A liquid fuel supply port 37 for ejecting the liquid fuel from the connection flow path portion 36 to the air flow is provided on the wing surface of the blade. The illustrated example shows a case where the present invention is applied to the second embodiment shown in FIG. 3. Therefore, the liquid fuel supply port 37 opened to the connecting blade 36 has a plurality of small holes.

However, the fifth embodiment described here can be applied to other than the illustrated second embodiment. Therefore, the liquid fuel supply port 37 also has a plurality of small holes other than the illustrated small holes. Also, a slit opening on the trailing edge as in the first embodiment described above, a slit opening on the wing surface as in the third embodiment, a sintered metal porosity as in the fourth embodiment, etc. Can be adopted. Also,
Different materials such as small holes and slits may be combined. In the illustrated example, the connecting wings 35 are arranged in a single annular shape. However, modified examples such as, for example, arranging in two annular shapes are possible.

According to the burner 20 having such a configuration, the atomized liquid fuel is ejected not only radially but also annularly, so that the fuel distribution at the outlet of the main swirler 30 is further uniformized. Will be done. Therefore, it is possible to burn uniformly premixed fuel in the premix nozzle, so that reduction of NOx can be further promoted. The provision of the connecting vanes 36 increases the pressure loss of the airflow, but this problem may be dealt with by increasing the diameter of the main swirler 30.

In the premixing nozzle 12 having the above-described main burner 20 as a component, the liquid fuel introduced through the liquid fuel supply pipe 22 is atomized and ejected from the liquid fuel supply port 22, and the gas fuel is similarly discharged. The gas fuel introduced through the supply pipe 23 gushes from the gas fuel supply port 24. The liquid fuel and gas fuel thus ejected are premixed with the swirling airflow passing through the main swirler 30 to form a premixed gas that is uniformly distributed. This premix is
The fuel flows out into the combustion chamber 10a of the combustor 10, flows out from each main burner 20 around the pilot burner 13 in the combustion chamber 10a, and burns using the flame of the pilot burner 13 described above as a fire. The reference numeral 16 in the figure denotes the inner cylinder 11
Is an outer cylinder that is disposed outside of the outer cylinder and forms an airflow introduction path that is inverted by 180 degrees.

In each of the above embodiments, an example of application to a dual-fired burner using both liquid fuel and gas fuel has been described. However, the present invention is not limited to this, and only liquid fuel is used. It can also be applied to a burner that burns. In this case, only the liquid fuel supply passage is provided in the fuel supply pipe, and the gas fuel supply passage 2 shown in FIG.
3 and the gas fuel supply port 24 become unnecessary. Further, in each of the above-described embodiments, an example in which the present invention is applied to the main burner of the premix nozzle is described. However, such a burner can of course be applied to a pilot burner.

In each of the above embodiments, the combustor 1
The configuration of the premix nozzle 12 is not limited to zero, and other configurations such as the number of the pilot burners 13 and the main burners 20 in the premix nozzle 12 can be used as appropriate. Other than this, any configuration may be adopted as long as it does not deviate from the gist of the present invention, and it goes without saying that the above-described configurations may be appropriately selectively combined.

[0038]

According to the above-described burner of the present invention, it is possible to promote the atomization of the liquid fuel by effectively utilizing the kinetic energy of the air flow, and to make the concentration distribution of the premixed gas to be burned uniform. Therefore, the emission amount of NOx generated by combustion can be reduced. Therefore, even in the premixing nozzle and the combustor using such a burner, the concentration distribution of the premixed gas can be made uniform, and the NOx emission can be suppressed low.

[Brief description of the drawings]

1A and 1B are diagrams showing a first embodiment of a burner according to the present invention, wherein FIG. 1A is a sectional view of a main part, and FIG. 1B is a sectional view taken along line AA of FIG.

FIG. 2 is a cross-sectional view showing a configuration example of a combustor using the burner of the present invention shown in FIG.

FIGS. 3A and 3B are views showing a second embodiment according to the burner of the present invention, wherein FIG. 3A is a sectional view of a main part, and FIG. 3B is a sectional view taken along line BB of FIG.

FIGS. 4A and 4B are views showing a third embodiment of the burner according to the present invention, wherein FIG. 4A is a sectional view of a main part, and FIG. 4B is a sectional view taken along line CC of FIG.

FIGS. 5A and 5B are views showing a fourth embodiment of the burner of the present invention, wherein FIG. 5A is a sectional view of a main part, FIG. 5B is a sectional view taken along line DD of FIG. It is the elements on larger scale of the main swirler made from sintered metal.

FIGS. 6A and 6B are views showing a fifth embodiment according to the burner of the present invention, wherein FIG. 6A is a sectional view of a main part, FIG. It is an enlarged view seen from arrow F.

7A and 7B are diagrams showing a configuration example of a conventional combustor, wherein FIG. 7A is a cross-sectional view of a main part, and FIG.

FIGS. 8A and 8B are views showing a conventional example of a burner, in which FIG. 8A is a sectional view of a main part, and FIG.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 10 Combustor 12 Premixing nozzle 13 Pilot burner 20 Main burner (burner) 21 Main fuel supply pipe (fuel supply pipe) 22 Liquid fuel supply passage 23 Gas fuel supply passage 24 Gas fuel ejection port 30 and 30A Main swirler (swirler blade) 31 liquid fuel flow path 32 slit (liquid fuel supply port) 33 small hole (liquid fuel supply port) 34 slit (liquid fuel supply port) 35 connecting blade 36 connecting flow path 37 liquid fuel supply port

Continued on the front page (51) Int.Cl. ⁷ Identification symbol FI Theme coat II (reference) F23R 3/36 F23R 3/36 (72) Inventor Masaaki Negoro 2-1-1, Araimachi Shinhama, Takasago-shi, Hyogo Mitsubishi Heavy Industries, Ltd. F-term in Takasago Research Laboratory (reference) 3K052 AA06 BA31 3K091 AA01 BB01 CC02 CC06 CC23

Claims (9)

[Claims] 1. A swirler blade for arranging a fuel supply pipe having a liquid fuel supply passage connected to a liquid fuel supply source along a flow path of an air flow, and swirling the air flow around the fuel supply pipe. A burner for injecting liquid fuel supplied to the fuel supply pipe into the air flow and burning the liquid fuel, wherein a liquid fuel passage communicating with the liquid fuel supply passage inside the swirler blades A burner, wherein a liquid fuel supply port for ejecting liquid fuel from the liquid fuel flow path to the air flow is formed in the swirler blade. 2. A fuel supply pipe having a liquid fuel supply passage connected to a liquid fuel supply source and a gas fuel supply passage connected to a gas fuel supply source is arranged along a flow path of an air flow. A swirler vane for swirling the air flow is provided around a fuel supply pipe, and a dual fuel-fired burner that jets liquid fuel and gas fuel supplied to the fuel supply pipe into the air flow and burns the fuel. Forming a liquid fuel flow path communicating with the liquid fuel supply passage inside the swirler blade, and connecting the liquid fuel supply port for ejecting liquid fuel from the liquid fuel flow path to the air flow with the swirler blade; A burner characterized in that the burner is provided with an opening. 3. The burner according to claim 1, wherein the liquid fuel supply port is a slit that opens to a trailing edge of the swirler blade. 4. The burner according to claim 1, wherein the liquid fuel supply port is one or a plurality of small holes that open on the blade surface of the swirler blade. 5. The burner according to claim 1, wherein the liquid fuel supply port is a slit that opens along a blade surface of the swirler blade. 6. The burner according to claim 1, wherein the swirler blade is made of a sintered metal. 7. A connecting wing is provided between the swirler wings,
A connection flow path communicating with the liquid fuel flow path is formed in the connection wing, and a liquid fuel supply port for ejecting liquid fuel from the connection flow path to the air flow is provided by opening the connection wing. The burner according to any one of claims 3 to 6, wherein: 8. A pilot burner disposed on a central axis, and a burner according to claim 1 disposed around the pilot burner as a main burner. Features a premix nozzle for combustors. 9. A combustor comprising: the premixing nozzle according to claim 8; and a cylinder housing the premixing nozzle.