Patent Publication Number: US-2022221152-A1

Title: Fuel nozzle, fuel nozzle module having the same, and combustor

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
     This application claims priority to Korean Patent Application No. 10-2021-0003238, filed on Jan. 11, 2021, the disclosure of which is incorporated by reference herein in its entirety. 
     BACKGROUND 
     Field 
     Apparatuses and methods consistent with exemplary embodiments relate to a fuel nozzle, a fuel nozzle module having the same, and a combustor. 
     Description of the Related Art 
     A gas turbine is a power engine configured to mix and combust compressed air compressed by a compressor with fuel and rotate a turbine with a high-temperature gas generated by combustion. The gas turbine is used to drive a generator, an aircraft, a ship, a train, or the like. 
     The gas turbine includes a compressor, a combustor, and a turbine. The compressor sucks and compresses external air and delivers the compressed air to the combustor. The air compressed by the compressor is in a high-pressure and high-temperature state. The combustor mixes the compressed air compressed by the compressor with fuel and combusts the mixture to produce combustion gas which is discharged to the turbine. A turbine blade in the turbine is rotated by the combusted gas to generate power. The generated power is used in various fields such as power generation and driving of a mechanical device. 
     SUMMARY 
     Aspects of one or more exemplary embodiments provide a fuel nozzle, a fuel nozzle module having the same, and a combustor, which can solve a problem of combustion instability caused by a high-frequency resonance in fuel containing hydrogen. 
     Additional aspects will be set forth in part in the description which follows and, in part, will become apparent from the description, or may be learned by practice of the exemplary embodiments. 
     According to an aspect of an exemplary embodiment, there is provided a fuel nozzle including: a fuel flow path through which a fuel flows, and a plurality of fuel plenums including a plurality of micro-mixers including a mixing flow path through which a fluid in which the fuel and compressed air are mixed flows and a fuel supply hole for supplying the fuel to the mixing flow path, wherein the plurality of fuel plenums are formed in the fuel flow path to be spaced apart from each other. 
     The plurality of fuel plenums can include a first fuel plenum formed upstream of fuel flow and a second fuel plenum formed downstream of the fuel flow, and a diameter of a first mixing flow path constituting the first fuel plenum may be different from a diameter of a second mixing flow path constituting the second fuel plenum. 
     The diameter of the first mixing flow path can be smaller than the diameter of the second mixing flow path. 
     Each of the plurality of fuel plenums can include a plenum inlet for flowing the fuel into the fuel plenum, and sizes of the plenum inlets of each of the plurality of fuel plenums may be different. 
     The fuel may be a fuel including hydrogen. 
     According to an aspect of another exemplary embodiment, there is provided a fuel nozzle module including: a plurality of fuel nozzles, and a shroud formed to surround the plurality of fuel nozzles, each of the plurality of fuel nozzles can include a fuel flow path through which a fuel flows, and a plurality of fuel plenums including a plurality of micro-mixers including a mixing flow path through which a fluid in which the fuel and compressed air are mixed flows and a fuel supply hole for supplying the fuel to the mixing flow path, wherein the plurality of fuel plenums can be formed in the fuel flow path to be spaced apart from each other. 
     At least two of the plurality of fuel nozzles can include the plurality of fuel plenums formed in the fuel flow path to be spaced apart from each other, each of the plurality of fuel plenums can include a first fuel plenum formed upstream of fuel flow and a second fuel plenum formed downstream of the fuel flow, and an interval between the first fuel plenum and the second fuel plenum constituting one of the plurality of fuel nozzles can be different from an interval between the first fuel plenum and the second fuel plenum constituting the other fuel nozzles. 
     At least two of the plurality of fuel plenums can be formed to have different volumes. 
     At least two of the plurality of fuel nozzles can include the plurality of fuel plenums formed in the fuel flow path to be spaced apart from each other, each of the plurality of fuel plenums can include a first fuel plenum formed upstream of fuel flow and a second fuel plenum formed downstream of the fuel flow, and at least one of a volume of the first fuel plenum and a volume of the second fuel plenum constituting one of the plurality of fuel nozzles can be different from a volume of the first fuel plenum or a volume of the second fuel plenum constituting the other fuel nozzles. 
     The plurality of fuel plenums can include a first fuel plenum formed upstream of fuel flow and a second fuel plenum formed downstream of the fuel flow, and a diameter of a first mixing flow path constituting the first fuel plenum can be smaller than a diameter of a second mixing flow path constituting the second fuel plenum. 
     Each of the plurality of fuel plenums can include a plenum inlet for flowing the fuel into the fuel plenum, and sizes of the plenum inlets of each of the plurality of fuel plenums may be different. 
     The fuel may be a fuel including hydrogen. 
     According to an aspect of another exemplary embodiment, there is provided a combustor including: a combustion chamber assembly including a combustion chamber in which a mixing fluid is combusted, and a fuel nozzle module including a plurality of fuel nozzles for injecting the mixing fluid into the combustion chamber and a shroud formed to surround the plurality of fuel nozzles, each of the plurality of fuel nozzles includes a fuel flow path through which a fuel flows, and a plurality of fuel plenums including a plurality of micro-mixers including a mixing flow path through which a fluid in which the fuel and compressed air are mixed flows and a fuel supply hole for supplying the fuel to the mixing flow path, wherein the plurality of fuel plenums can be formed in the fuel flow path to be spaced apart from each other. 
     At least two of the plurality of fuel nozzles can include the plurality of fuel plenums formed in the fuel flow path to be spaced apart from each other, each of the plurality of fuel plenums can include a first fuel plenum formed upstream of fuel flow and a second fuel plenum formed downstream of the fuel flow, and an interval between the first fuel plenum and the second fuel plenum constituting one of the plurality of fuel nozzles including the plurality of fuel plenums can be different from an interval between the first fuel plenum and the second fuel plenum constituting the other fuel nozzles. 
     At least two of the plurality of fuel plenums can be formed to have different volumes. 
     At least two of the plurality of fuel nozzles can include the plurality of fuel plenums formed in the fuel flow path to be spaced apart from each other, each of the plurality of fuel plenums can include a first fuel plenum formed upstream of fuel flow and a second fuel plenum formed downstream of the fuel flow, and at least one of a volume of the first fuel plenum and a volume of the second fuel plenum constituting one of the plurality of fuel nozzles can be different from a volume of the first fuel plenum or a volume of the second fuel plenum constituting the other fuel nozzles. 
     The plurality of fuel plenums can include a first fuel plenum formed upstream of fuel flow and a second fuel plenum formed downstream of the fuel flow, and a diameter of a first mixing flow path constituting the first fuel plenum can be smaller than a diameter of a second mixing flow path constituting the second fuel plenum. 
     Each of the plurality of fuel plenums can include a plenum inlet for flowing the fuel into the fuel plenum, and sizes of the plenum inlets of each of the plurality of fuel plenums may be different. 
     The fuel can be a fuel including hydrogen. 
     According to one or more exemplary embodiments, it is possible to solve the problem of combustion instability due to the high-frequency resonance generated by fuel containing hydrogen. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The above and other aspects will become more apparent from the following description of the exemplary embodiments with reference to the accompanying drawings, in which: 
         FIG. 1  is a diagram showing an interior of a gas turbine according to an exemplary embodiment; 
         FIG. 2  is a diagram showing a burner module constituting a combustor according to an exemplary embodiment; 
         FIG. 3  is a diagram showing a lower surface of the burner module according to an exemplary embodiment; 
         FIG. 4  is a cross-sectional diagram taken along line I-I′ of  FIG. 3  showing a fuel nozzle module according to an exemplary embodiment; 
         FIG. 5  is a cross-sectional diagram showing a fuel nozzle according to an exemplary embodiment; 
         FIG. 6  is a cross-sectional diagram showing a modified example of the fuel nozzle according to another exemplary embodiment; and 
         FIGS. 7 to 10  are cross-sectional diagrams showing various forms of a fuel nozzle module according to another exemplary embodiment. 
     
    
    
     DETAILED DESCRIPTION 
     Various changes and various embodiments will be described in detail with reference to the accompanying drawings. It should be understood, however, that the various embodiments are not for limiting the scope of the disclosure to the specific embodiment, but they should be interpreted to include all modifications, equivalents, and alternatives of the embodiments included within the sprit and scope disclosed herein. 
     The terms used herein are used to describe only a specific exemplary embodiment, and are not intended to limit the scope of the disclosure. The singular forms include the plural forms unless the context clearly indicates otherwise. In the present disclosure, it should be understood that the terms “comprises” or “includes,” etc. specify the presence of features, integers, steps, operations, components, parts or a combination thereof described in the specification, but do not preclude the presence or addition possibility of one or more other features, integers, steps, operations, components, parts or a combination thereof. 
     Hereinafter, exemplary embodiments will be described in detail with reference to the accompanying drawings. It is noted that like reference numerals refer to like parts throughout the various figures and exemplary embodiments. In certain embodiments, a detailed description of known functions and configurations that may obscure the gist of the present disclosure will be omitted. For the same reason, some of the elements in the drawings are exaggerated, omitted, or schematically illustrated. 
       FIG. 1  is a diagram showing an interior of a gas turbine according to an exemplary embodiment,  FIG. 2  is a diagram showing a burner module constituting a combustor according to an exemplary embodiment, and  FIG. 3  is a diagram showing a lower surface of the burner module according to an exemplary embodiment. 
     Referring to  FIGS. 1 to 3 , a gas turbine  1000  includes a compressor  1100  configured to compress introduced air at high pressure, a combustor  1200  configured to mix the compressed air compressed by the compressor  1100  with fuel to combust the mixture, and a turbine  1300  configured to generate a rotation force with a combustion gas generated by the combustor  1200 . Here, an upstream and a downstream are defined based on a front and rear of fuel or air flow. 
     A thermodynamic cycle of the gas turbine can ideally comply with the Brayton cycle. The Brayton cycle is composed of four processes: isentropic compression (i.e., an insulation compression) process, static pressure rapid heat process, isentropic expansion (i.e., an insulation expansion) process, and static pressure heat dissipation process. That is, in the Brayton cycle, thermal energy may be released by combustion of fuel in the static pressure environment after ambient air is sucked and compressed at high pressure, the high-temperature combusted gas is expanded and converted into kinetic energy, and an exhaust gas with remaining energy is emitted to the atmosphere. As such, the cycle is composed of four processes: compression, heating, expansion, and heat-dissipation. 
     The gas turbine  1000  employing the Brayton cycle includes the compressor  1100 , the combustor  1200 , and the turbine  1300 . Although the following description will be described with reference to  FIG. 1 , the present disclosure may be widely applied to other turbine engines having similar configurations to the gas turbine  1000  illustrated in  FIG. 1 . 
     Referring to  FIG. 1 , the compressor  1100  of the gas turbine may suck and compress air to supply the air for combustion to the combustor  1200  and to supply the air for cooling to a high-temperature region of the gas turbine that is required to be cooled. Because the sucked air is compressed in the compressor  1100  through an insulation compression process, the pressure and temperature of the air passing through the compressor  1100  increase. 
     The compressor  1100  may be designed in a form of a centrifugal compressor or an axial compressor, and the centrifugal compressor is applied to a small gas turbine whereas a multistage axial compressor is applied to a large gas turbine illustrated in  FIG. 1  to compress a large amount of air. 
     The compressor  1100  is driven using a part of the power output from the turbine  1300 . To this end, as shown in  FIG. 1 , a rotary shaft of the compressor  1100  and a rotary shaft of the turbine  1300  are directly connected. In the case of the large gas turbine  1000 , almost half of the output produced by the turbine  1300  may be consumed to drive the compressor  1100 . Accordingly, improving the efficiency of the compressor  1100  has a direct effect on improving the overall efficiency of the gas turbine  1000 . 
     The combustor  1200  mixes the compressed air supplied from an outlet of the compressor  110  with fuel to combust the mixture at constant pressure to generate a combustion gas with high energy. The combustor  1200  is disposed on the downstream of the compressor  1100  and includes a plurality of burner modules  1210  annually disposed around the rotary shaft. 
     Referring to  FIG. 2 , the burner module  1210  can include a combustion chamber assembly  1220  including a combustion chamber  1240  in which fuel fluid is combusted, and a fuel nozzle assembly  1230  including a fuel nozzle module  2000  that injects the fuel fluid into the combustor chamber  1240 . 
     The gas turbine  1000  may use gas fuel including hydrogen or natural gas, liquefied fuel, or composite fuel that is a combination thereof. In order to create a combustion environment to reduce the amount of emissions such as carbon monoxide or nitrogen oxides, a gas turbine has a recent tendency to apply a premixed combustion scheme that is advantageous in reducing emissions through lowered combustion temperature and homogeneous combustion even though it is difficult to control the premixed combustion. 
     For the premix combustion, the compressed air introduced from the compressor  1100  is mixed with fuel in advance in the fuel nozzle assembly  1230 , and then enters the combustion chamber  1240 . When a premix gas is initially ignited by an igniter, and then combustion state is stabilized, the combustion state is maintained by supplying fuel and air. 
     The fuel nozzle assembly  1230  can include a fuel nozzle module  2000  including a plurality of fuel nozzles  2100 ,  2200 , and  2300 . The plurality of fuel nozzles  2100 ,  2200 , and  2300  mix fuel with air at an appropriate rate to form a fuel-air mixture having conditions suitable for combustion. The plurality of fuel nozzles  2100 ,  2200 , and  2300  can be implemented in a micro-mixed type. 
     The combustion chamber assembly  1220  includes the combustion chamber  1240  in which combustion is performed, a liner  1250  and a transition piece  1260 . 
     The liner  1250  disposed on a downstream side of the fuel nozzle assembly  1230  may have a dual structure of an inner liner  1251  and an outer liner  1252  in which the inner liner  1251  is surrounded by the outer liner  1252 . In this case, the inner liner  1251  is a hollow tubular member, and an internal space of the inner liner  1251  forms the combustion chamber  1240 . The inner liner  1251  is cooled by the compressed air introduced into an annular space inside the outer liner  1252  through a compressed air introduction hole (H). 
     The transition piece  1260  is disposed on a downstream side of the liner  1250  to guide the combustion gas generated in the combustion chamber  1240  to the turbine  1300  at high speed. The transition piece  1260  may have a dual structure of an inner transition piece  1261  and an outer transition piece  1262  in which the inner transition piece  1261  is surrounded by the outer transition piece  1262 . The inner transition piece  1261  is also formed of a hollow tubular member such that a diameter thereof gradually decreases from the liner  1250  toward the turbine  1300 . In this case, the inner liner  1251  and the inner transition piece  1261  can be coupled to each other by a plate spring seal. Because respective ends of the inner liner  1251  and the inner transition piece  1261  are fixed to the combustor  1200  and the turbine  1300 , respectively, the plate spring seal may have a structure capable of accommodating expansion of length and diameter by thermal expansion to support the inner liner  1251  and the inner transition piece  1261 . 
     As such, the inner liner  1251  and the inner transition piece  1261  have a structure surrounded by the outer liner  1252  and the outer transition piece  1262 , respectively, so that the compressed air may flow into the annular space between the inner liner  1251  and the outer liner  1252  and into the annular space between the inner transition piece  1261  and the outer transition piece  1262  through the compressed air introduction hole (H). The compressed air introduced into the annular space can cool the inner liner  1251  and the inner transition piece  1261 . 
     Meanwhile, the high-temperature and high-pressure combustion gas produced by the combustor  1200  is supplied to the turbine  1300  through the liner  1250  and the transition piece  1260 . As the insulation expansion of the combustion gas is made in the turbine  1300 , the combustion gas collides with a plurality of blades radially disposed on the rotary shaft of the turbine  1300  so that the thermal energy of the combustion gas is converted into mechanical energy that rotates the rotary shaft. A part of the mechanical energy obtained from the turbine  1300  is supplied as energy necessary for compressing the air in the compressor  1100 , and the remaining energy is used as available energy to drive a generator to produce power. 
     The combustor  1200  may further include casing  1270  and an end cover  1231  coupled to accommodate compressed air (A) flowing to the burner module  1210 . After the compressed air (A) flows into the annular space in the liner  1250  or the transition piece  1260  through the compressed air introduction hole (H), the flowing direction thereof is changed by the end cover  1231  to the inside of the fuel nozzle module  2000 . The fuel can be supplied to the fuel nozzle module  2000  through a fuel flow path  1232  and can be mixed with the compressed air. 
     Referring to  FIG. 3 , the fuel nozzle module  2000  includes the plurality of fuel nozzles  2100 ,  2200 , and  2300 , and each of the fuel nozzles  2100 ,  2200 , and  2300  can include a plurality of micro-mixers. The micro-mixer can be configured to include a mixing flow path  2101  and a fuel supply hole  2102 . 
     The plurality of fuel nozzles  2100 ,  2200 , and  2300  can be arranged radially on the upstream of the combustion chamber  1240 , and a shroud  1234  is formed to surround the plurality of fuel nozzles  2100 ,  2200 , and  2300 . The shroud  1234  and the plurality of fuel nozzles  2100 ,  2200 , and  2300  form the fuel nozzle module  2000 . 
       FIG. 4  is a cross-sectional diagram taken along line I-I′ of  FIG. 3  showing the fuel nozzle module  2000  according to an exemplary embodiment, and  FIG. 5  is a cross-sectional diagram showing a fuel nozzle  2100  according to an exemplary embodiment. 
     Referring to  FIGS. 4 and 5 , the fuel nozzle module  2000  includes the plurality of fuel nozzles  2100 ,  2200 , and  2300 , and each of the plurality of fuel nozzles  2100 ,  2200 , and  2300  includes at least two fuel plenums  2110  and  2120 . The at least two fuel plenums  2110  and  2120  can be formed on one fuel flow path  1232  to be spaced apart from each other. 
     Here, the plurality of fuel nozzles  2100 ,  2200 , and  2300  can have the same shape, and the description of the fuel nozzle  2100  can be equally applied to the fuel nozzles  2200  and  2300 . 
     A fuel (F) can be supplied to the fuel plenums  2110  and  2120  through the fuel flow path  1232  and can be introduced into the micro-mixer to be mixed with the compressed air (A). The fuel (F) can consist of only hydrogen, only natural gas, or a mixed firing that mixes the hydrogen and the natural gas. 
     For example, the compressed air (A) flows into a first mixing flow path  2101   a  formed in a first fuel plenum  2110 , and the fuel (F) supplied through the fuel flow path  1232  flows into the first fuel plenum  2110  through a first plenum inlet  2103   a  and is supplied to the first mixing flow path  2101   a  through the fuel supply hole  2102  to be mixed with the compressed air (A) to become a first mixing fluid (F+A) to flow into a second fuel plenum  2120 . 
     The first mixing fluid (F+A) flows into a second mixing flow path  2101   b  formed in the second fuel plenum  2120 , and the fuel (F) supplied through the fuel flow path  1232  flows into the second fuel plenum  2120  through a second plenum inlet  2103   b  and is supplied to the second mixing flow path  2101   b  through the fuel supply hole  2102  to be mixed with the first mixing fluid (F+A) to become a second mixing fluid (F+A) to flow into the combustion chamber  1240 . 
     For example, the first plenum inlet  2103   a  and the second plenum inlet  2103   b  may have different sizes. Therefore, because an amount of the fuel (F) flowing into each of the fuel plenums  2110  and  2120  is different, a fuel distribution ratio in the fuel plenums  2110  and  2120  can be different. 
     The fuel nozzle according to the exemplary embodiment includes at least two fuel plenums  2110  and  2120 , and the fuel (F) flows therein through the plenum inlets  2103   a  and  2103   b  formed in each fuel plenum, and in this case, an amount of the fuel flowing into each of the plenum inlets  2103   a  and  2103   b  can be adjusted. In other words, during actual operation, an amount of fuel flowing into the first plenum inlet  2103   a  is different from an amount of fuel flowing into the second plenum inlet  2103   b . As a result, the fuel distribution ratio to each of the fuel plenums  2110  and  2120  can be adjusted, and thus the fuel distribution ratio of the mixed fluid flowing into the combustion chamber  1240  through each fuel nozzle  2100 ,  2200 , and  2300  can be different, and the number of high frequency of each fuel nozzle  2100 ,  2200 , and  2300  generated by the fuel containing hydrogen can be different. Therefore, it is possible to solve the problem of combustion instability due to high-frequency resonance caused by the fuel containing hydrogen. 
       FIG. 6  is a cross-sectional diagram showing a modified example of the fuel nozzle according to an exemplary embodiment. Referring to  FIG. 6 , because the fuel nozzle according to the exemplary embodiment has the same structure as the fuel nozzle of  FIG. 5  except that a diameter (R 1 ) of the first mixing flow path  2101   a  and a diameter (R 2 ) of the second mixing flow path  2101   b  is different, a redundant description of the same configuration will be omitted. 
     For example, the diameter (R 1 ) of the first mixing flow path  2101   a  can be smaller than the diameter (R 2 ) of the second mixing flow path  2101   b . In this case, the first fuel plenum  2110  including the first mixing flow path  2101   a  and the second fuel plenum  2120  including the second mixing flow path  2101   b  may mix fluids, and each of the fuel plenums can perform other functions. 
     The first fuel plenum  2110  includes a mixing flow path having a small diameter to increase the speed of the mixed fluid so that the fluids can be mixed well. The second fuel plenum  2120  includes a mixing flow path having a large diameter to reduce the speed of the mixed fluid so that the flame in the combustion chamber  1240  can be maintained well. 
       FIGS. 7 to 10  are cross-sectional diagrams showing various forms of a fuel nozzle module according to another exemplary embodiment. 
     Exemplary embodiments of  FIGS. 7 to 10  are to solve the problem of combustion instability due to the high-frequency resonance by adjusting the fuel distribution ratio in each fuel nozzle  2100 ,  2200 , and  2300  so that the frequency of the high frequency in each fuel nozzle  2100 ,  2200 , and  2300  is formed differently. 
     Referring to  FIG. 7 , each of the fuel nozzles  2100 ,  2200 , and  2300  constituting the fuel nozzle module  2000  includes at least two fuel plenums  2110  and  2120 , and an interval between the fuel plenums  2110  and  2120  of one fuel nozzle can be different from an interval between the fuel plenums of another fuel nozzle. 
     For example, at least one of an interval (L 1 ) between the fuel plenums  2110  and  2120  constituting the first fuel nozzle  2100 , an interval (L 2 ) between fuel plenums  2210  and  2220  constituting a second fuel nozzle  2200 , and an interval (L 3 ) between fuel plenums  2310  and  2320  constituting a third fuel nozzle  2300  can be formed differently.  FIG. 7  shows that all intervals are formed differently (i.e., L 1 ≠L 2 ≠L 3 ). 
     Referring to  FIGS. 8 to 10 , each of the fuel nozzles  2100 ,  2200 , and  2300  constituting the fuel nozzle module  2000  includes at least two fuel plenums  2110  and  2120 , and each volume of the plurality of fuel plenums constituting at least one fuel nozzle can be formed differently. 
     For example, a volume (V 1 ) of the first fuel plenum  2110  and a volume (V 2 ) of the second fuel plenum  2120  constituting the first fuel nozzle  2100  can be formed differently. Preferably, the volume (V 1 ) of the first fuel plenum  2110  can be formed larger than the volume (V 2 ) of the second fuel plenum  2120 . 
       FIG. 8  shows that in each of the fuel nozzles  2100 ,  2200 , and  2300 , the volumes (V 1 ) of the first fuel plenums  2110 ,  2210 , and  2310  are the same, and the volumes (V 2 ) of the second fuel plenums  2120 ,  2220 , and  2320  are the same, but the volumes (V 1 ) of the first fuel plenums  2110 ,  2210 , and  2310  are larger than the volumes (V 2 ) of the second fuel plenums  2120 ,  2220 , and  2320  (i.e., V 1 &gt;V 2 ). 
       FIG. 9  shows that in each of the fuel nozzles  2100 ,  2200 , and  2300 , the volumes (V 2 ) of the second fuel plenums  2120 ,  2220 , and  2320  are the same, but all volumes (V 11 , V 12 , and V 13 ) of the first fuel plenums  2110 ,  2210 , and  2310  are different (i.e., V 11 ≠V 12 ≠V 13 ≠V 2 ). 
       FIG. 10  shows that in each of the fuel nozzles  2100 ,  2200 , and  2300 , the volumes (V 1 ) of the first fuel plenums  2110 ,  2210 , and  2310  are the same, but all volumes (V 21 , V 22 , and V 23 ) of the second fuel plenums  2120 ,  2220 , and  2320  are different (i.e., V 21 ≠V 22 ≠V 23 ≠V 1 ). 
     The fuel nozzle module according to another exemplary embodiment can variously adjust the fuel distribution ratio of each of the fuel plenums by variously forming an interval between at least two fuel plenums constituting each of the fuel nozzles  2100 ,  2200 , and  2300 , a volume ratio of the fuel plenum, and the like. Therefore, the frequencies of the high frequency of each of the fuel nozzles  2100 ,  2200 , and  2300  generated by the fuel containing hydrogen can be formed differently, thereby solving the problem of combustion instability due to the high-frequency resonance. 
     While one or more exemplary embodiments have been described with reference to the accompanying drawings, it will be apparent to those skilled in the art that various modifications and variations can be made through addition, change, deletion, or substitution of components without departing from the spirit and scope of the disclosure described in the appended claims, and these modifications and changes fall within the spirit and scope of the disclosure as defined in the appended claims.