JP7344652B2 - gas burner equipment - Google Patents

Description

The present disclosure relates to a gas burner device that supplies gas fuel and combustion air to a combustion space.

Some gas burners that mix combustion air with gas fuel and combust the mixture include a gas fuel nozzle and a combustion air nozzle disposed around the gas fuel nozzle. The injection opening of the gas fuel nozzle and the outlet of the combustion air nozzle face a combustion space, for example a combustion chamber of a boiler. The gas fuel injected from the injection port of the gas fuel nozzle causes the combustion air flowing out of the combustion air nozzle outlet to be drawn into the combustion space by the vortex formed near the injection port and mixed with the gas fuel. The combustion state of the gas fuel ignited in the combustion space continues.

Patent Document 1 describes a low-calorie gas burner device for self-combusting low-calorie gas, in which a flame-holding ring is formed at the tip of the gas burner and projects at right angles to the fuel gas flow, and a vortex flow generated downstream of the flame-holding ring It is disclosed that low calorie gas can be self-combusted by flame holding. The flame-holding rings are attached at regular intervals around the entire circumference of the tip for the purpose of inhibiting the promotion of combustion.

Utility Model Publication No. 61-063521

Gas burners designed to handle high loads can stably burn gas fuel because vortices are formed during high or medium loads. However, in the above-mentioned gas burner, when the load is low, the flow rate of the gas fuel flowing inside the gas fuel nozzle and injected from the injection port of the gas fuel nozzle is low, and the flow of the gas fuel becomes a laminar flow, so the formation of vortex flow is prevented. This is difficult, and there is a risk that the combustion air and gas fuel may not be sufficiently mixed in the combustion space, making it impossible to stably burn the gas fuel. Note that the low-calorie gas of Patent Document 1 has low combustion energy, but does not have a low flow rate. Patent Document 1 does not mention the above-mentioned problem when the gas burner is under low load.

In view of the above-mentioned circumstances, it is an object of at least one embodiment of the present invention to provide a gas burner device that can stably burn gas fuel even under low load.

(1) A gas burner device according to at least one embodiment of the present invention includes:
a gas fuel nozzle for supplying gas fuel to the combustion space;
a combustion air nozzle for supplying combustion air to the combustion space, the combustion air nozzle disposed around the gas fuel nozzle;
A flame stabilizer including an outer flame stabilizer that projects outward from the tip of the gas fuel nozzle and that extends continuously along the outer periphery of the injection port of the gas fuel nozzle. and.

According to configuration (1) above, gas fuel is supplied to the combustion space from the gas fuel nozzle. In addition, combustion air is supplied to the combustion space from a combustion air nozzle disposed around the gas fuel nozzle to a region radially outward of a region of the combustion space to which the gas fuel is supplied. The gas burner device includes a flame stabilizer including an outer flame stabilizer that protrudes outward from the tip of the gas fuel nozzle, so that the combustion air flowing around the outer flame stabilizer moves the outer flame stabilizer toward the inside. After flowing in a winding manner, it flows radially inward. The combustion air flowing radially inward and the gas fuel injected from the injection port of the gas fuel nozzle form a vortex downstream of the injection port even during low load. By mixing the combustion air drawn radially inward by the vortex and the gas fuel, the gas fuel can be stably combusted. Further, according to the above configuration, the outer flame stabilizing member extends continuously along the outer peripheral edge of the injection port of the gas fuel nozzle, so that a vortex can be generated over a wide range. Therefore, according to the above configuration, gas fuel can be stably combusted even under low load.

(2) In some embodiments, in the gas burner device according to (1) above, the flame stabilizer is an inner flame stabilizer that protrudes inward from the tip of the gas fuel nozzle. The gas fuel nozzle further includes an inner flame stabilizing member extending continuously along an inner peripheral edge of the injection port of the gas fuel nozzle.

According to the configuration (2) above, the flame stabilizer includes the inner flame stabilizer that protrudes inward from the tip of the gas fuel nozzle, so that the periphery of the inner flame stabilizer is maintained even under low load. The flow of flowing gaseous fuel is disturbed. When the flow of gas fuel flowing around the inner flame stabilizing member is disturbed, the gas fuel stays near the injection port of the gas fuel nozzle, so the ignition area can be brought closer to the injection port of the gas fuel nozzle, and the gas fuel Stable combustion can be achieved. If the ignition region is located downstream from the injection port of the gas fuel nozzle, gas fuel cannot be stably supplied to the ignition region, so there is a risk that the combustion flame will blow out. Further, according to the above configuration, the inner flame stabilizing member extends continuously along the inner peripheral edge of the injection port of the gas fuel nozzle, so that a large amount of gas fuel is provided near the injection port of the gas fuel nozzle. Since the gas can be retained, the ignition region can be brought closer to the injection port of the gas fuel nozzle more reliably, and the gas fuel can be burned more stably. Therefore, according to the above configuration, gas fuel can be stably combusted even under low load.

(3) In some embodiments, in the gas burner device described in (2) above, the inner flame stabilizing member has a circular cross-sectional shape.

According to the configuration (3) above, since the inner flame stabilizing member has a circular cross-sectional shape, it is possible to disturb the flow of gas fuel flowing around the inner flame stabilizing member, and the inner flame stabilizing member It is possible to suppress the pressure loss of the gas flowing around it. By suppressing gas pressure loss, gas fuel can be burned more stably.

(4) In some embodiments, in the gas burner device according to any one of (1) to (3) above, the outer flame stabilizing member extends from the end face of the tip toward the combustion space side. , extends such that the radial distance from the axis of the injection port increases.

According to the configuration (4) above, the outer flame stabilizing member extends from the end face of the tip portion toward the combustion space side so that the radial distance from the axis of the injection port increases, so that the outer flame stabilizing member Most of the combustion air flowing around the flame stabilizing member can be made to flow radially inward on the downstream side of the outer flame stabilizing member, making it possible to more effectively generate a vortex flow. Therefore, according to the above configuration, gas fuel can be burned more stably.

(5) In some embodiments, in the gas burner device according to any one of (1) to (4) above, the injection ports of the gas fuel nozzle extend in directions parallel to each other. It has a rectangular ring shape including a pair of long sides and a pair of short sides connected to the pair of long sides.

According to configuration (5) above, the injection port of the gas fuel nozzle has a rectangular annular shape including a pair of long sides and a pair of short sides. Here, the gas fuel and combustion air flowing around the corners of the injection port have a lower flow velocity than the gas fuel and combustion air flowing around the center of the long side and the center of the short side, so the vortex flow It is difficult to cause According to the above configuration, since the outer flame stabilizing member extends continuously along the outer peripheral edge of the injection port of the gas fuel nozzle, it is possible to generate a vortex over a wide range. Therefore, according to the above configuration, gas fuel can be stably combusted even downstream of the corner portion.

(6) In some embodiments, in the gas burner device according to (5) above, the outer flame stabilizing member continuously extends over the entire length of the outer peripheral edge of at least one of the pair of long sides. do.

According to the configuration (6) above, the outer flame stabilizing member extends continuously over the entire length of the outer peripheral edge of at least one of the pair of long sides, so that a vortex can be generated over a wide range, and A vortex can be generated more stably downstream of the corner. Therefore, according to the above configuration, gas fuel can be stably combusted even downstream of the corner portion.

(7) In some embodiments, in the gas burner device according to (5) or (6) above, the flame stabilizer is an inner holder that protrudes inward from the tip of the gas fuel nozzle. It further includes an inner flame stabilizing member that is a flame member and extends continuously along the inner peripheral edge of the injection port of the gas fuel nozzle, and the inner flame stabilizing member includes at least one of the pair of long sides. It extends continuously over the entire length of one inner peripheral edge.

According to the configuration (7) above, the inner flame stabilizing member extends continuously over the entire length of the inner peripheral edge of at least one of the pair of long sides, so that a large amount of gas is generated near the injection port of the gas fuel nozzle. The fuel can be retained, and the ignition region can be more reliably brought closer to the injection port of the gas fuel nozzle. Further, according to the above configuration, the flow of the gas fuel flowing around the corner portion can be disturbed, so the gas fuel can be burned more stably. Therefore, according to the above configuration, gas fuel can be stably combusted even under low load.

(8) In some embodiments, the gas burner device according to any one of (1) to (7) above, wherein the gas fuel nozzle is a first gas contained in the combustion air nozzle. a second gas fuel nozzle housed within the combustion air nozzle in which the first gas fuel nozzle is housed and arranged in parallel with the first gas fuel nozzle; The first gas fuel nozzle includes a first injection port having a rectangular annular shape including a first long side and a second long side extending in a direction parallel to the first long side, The second gas fuel nozzle has a third long side extending along a direction parallel to the first long side, and a third long side extending along a direction parallel to the third long side. a fourth long side disposed on the opposite side of the second long side with respect to the third long side; The first outer flame stabilizing member includes a first outer flame stabilizing member provided over the entire length of the outer periphery of the long side portion, and a second outer flame stabilizing member provided over the entire length of the outer periphery of the second long side portion. The member was configured to be wider than the second outer flame stabilizing member when viewed from the direction in which the axis of the first injection port of the first gas fuel nozzle extends.

According to configuration (8) above, the gas fuel nozzle includes a first gas fuel nozzle and a second gas fuel nozzle housed inside the same combustion air nozzle. The gas is supplied to the combustion space from the gap space formed between the second long side of the first injection port of the first gas fuel nozzle and the third long side of the second injection port of the second gas fuel nozzle. Since the combustion air used for combustion is used for both the combustion of the gas fuel injected from the first gas fuel nozzle and the combustion of the gas fuel injected from the second gas fuel nozzle, there is a risk of supply shortage. be. According to the above configuration, the width of the first outer flame stabilizing member is made larger than the width of the second outer flame stabilizing member to increase the supply amount of combustion air flowing around the first outer flame stabilizing member. Since a shortage of combustion air can be prevented, gaseous fuel can be stably combusted.

(9) In some embodiments, in the gas burner device according to (8) above, the outer flame stabilizing member is a third outer flame stabilizing member provided over the entire length of the outer peripheral edge of the third long side portion. and a fourth outer flame stabilizing member provided over the entire length of the outer periphery of the fourth long side, the fourth outer flame stabilizing member being aligned with the axis of the first injection port of the first gas fuel nozzle. When viewed from the extending direction, the third outer flame stabilizing member was configured to have a wider width than the third outer flame stabilizing member.

According to the configuration (9) above, the width of the fourth outer flame stabilizing member is made larger than the width of the third outer flame stabilizing member, and the supply amount of combustion air flowing around the fourth outer flame stabilizing member is controlled. By increasing the amount, it is possible to prevent a shortage of combustion air, and therefore it is possible to stably burn the gas fuel.

According to at least one embodiment of the present invention, a gas burner device that can stably burn gas fuel even under low load is provided.

1 is a schematic sectional view schematically showing the overall configuration of a boiler equipped with a gas burner device according to an embodiment of the present invention. 1 is a schematic cross-sectional view along the axial direction of a gas burner device according to an embodiment of the present invention. 1 is a schematic diagram of a gas burner device according to an embodiment of the present invention, viewed from the combustion space side. FIG. 3 is a schematic diagram of a gas burner device according to another embodiment of the present invention, viewed from the combustion space side. It is an explanatory view for explaining a flame stabilizer in one embodiment of the present invention. It is a schematic sectional view along the axial direction of the gas burner device concerning other one embodiment of the present invention. FIG. 7 is a schematic diagram of the gas burner device shown in FIG. 6 viewed from the combustion space side.

Hereinafter, some embodiments of the present invention will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of the components described as the embodiments or shown in the drawings are not intended to limit the scope of the present invention thereto, and are merely illustrative examples. do not have.
For example, expressions expressing relative or absolute positioning such as "in a certain direction,""along a certain direction,""parallel,""orthogonal,""centered,""concentric," or "coaxial" are strictly In addition to representing such an arrangement, it also represents a state in which they are relatively displaced with a tolerance or an angle or distance that allows the same function to be obtained.
For example, expressions such as "same,""equal," and "homogeneous" that indicate that things are in an equal state do not only mean that things are exactly equal, but also have tolerances or differences in the degree to which the same function can be obtained. It also represents the existing state.
For example, expressions expressing shapes such as squares and cylinders do not only refer to shapes such as squares and cylinders in a strict geometric sense, but also include uneven parts and chamfers to the extent that the same effect can be obtained. Shapes including parts, etc. shall also be expressed.
On the other hand, the expressions "comprising,""including," or "having" one component are not exclusive expressions that exclude the presence of other components.
Note that similar configurations may be given the same reference numerals and explanations may be omitted.

FIG. 1 is a schematic sectional view schematically showing the overall configuration of a boiler equipped with a gas burner device according to an embodiment of the present invention.
As shown in FIG. 1, a gas burner device 2 according to some embodiments of the present invention is a device that supplies gas fuel G and combustion air A to a combustion space 10 and burns the gas fuel G in the combustion space 10. It is.

In the illustrated embodiment, the gas burner device 2 is mounted on the boiler 1, as shown in FIG. The boiler 1 is a hollow boiler furnace 11 having an outer peripheral wall extending in the vertical direction, and includes a boiler furnace 11 in which a combustion chamber 12 is defined. The combustion space 10 mentioned above includes the combustion chamber 12 of the boiler 1.
The gas burner device 2 has a tip facing the combustion chamber 12, supplies gas fuel G and combustion air A to the combustion chamber 12 from outside the boiler 1, and burns the gas fuel G within the combustion chamber 12.

The combustion space 10 described above may be any space for burning the gas fuel G, and is not limited to the combustion chamber 12 described above. In some embodiments, the gas burner device 2 may be installed in equipment other than the boiler 1 including the combustion space 10 described above.

FIG. 2 is a schematic cross-sectional view along the axial direction of a gas burner device according to an embodiment of the present invention. FIG. 3 is a schematic diagram of a gas burner device according to an embodiment of the present invention viewed from the combustion space side. FIG. 4 is a schematic diagram of a gas burner device according to another embodiment of the present invention, viewed from the combustion space side. FIG. 5 is an explanatory diagram for explaining a flame stabilizer in an embodiment of the present invention.

A gas burner device 2 according to some embodiments includes a gas fuel nozzle 3 for supplying gas fuel G to a combustion space 10, and a combustion air A for supplying combustion air A to the combustion space 10, as shown in FIG. 2, for example. The combustion air nozzle 4 is a combustion air nozzle 4 disposed around the gas fuel nozzle 3, and the gas fuel G supplied from the gas fuel nozzle 3 to the combustion space 10 is combusted. and a flame stabilizer 5 configured to flame stabilize the combustion flame.

In the illustrated embodiment, as shown in FIG. 2, the gas fuel nozzle 3 is formed in a cylindrical shape defining a first flow path 30 therein, and has open ends at both ends. As shown in FIG. 2, the gas fuel nozzle 3 has an injection port 32 at a tip 31, which is one open end, for injecting the gas fuel G flowing through the first flow path 30 into the combustion space 10. . Further, the gas fuel nozzle 3 has an inlet 33 for introducing the gas fuel G into the first flow path 30 at the other open end different from the tip 31.
In the embodiment shown in FIG. 3, the gas fuel nozzle 3 is formed in a rectangular cylindrical shape, and the injection port 32 is formed in a rectangular annular shape. In the embodiment shown in FIG. 4, the gas fuel nozzle 3 is formed in a cylindrical shape, and the injection port 32 is formed in an annular shape.

In the illustrated embodiment, the gaseous fuel G described above is a residual mixture containing gaseous fuel G1 and primary air A1.
As shown in FIG. 2, one end of a gaseous fuel supply pipe 8 formed in a cylindrical shape and into which gaseous fuel G1 flows is inserted into the first flow path 30 from the center of the introduction port 33. The other end of the gaseous fuel supply pipe 8 is connected to a gaseous fuel supply device 9 such as a pipe or a tank configured to be able to supply gaseous fuel to the gaseous fuel supply pipe 8 . The gaseous fuel G1 is sent from the gaseous fuel supply device 9 to the first flow path 30 via the gaseous fuel supply pipe 8. Primary air A1 is introduced into the first flow path 30 from the outside in the radial direction of the gaseous fuel supply pipe 8 at the introduction port 33. Here, the "radial direction" is based on the axis LA of the injection port 32 described above. The "radial direction" in the following is based on the axis LA unless otherwise mentioned.

In some other embodiments, the gaseous fuel G described above includes only gaseous fuel G1. That is, from the introduction port 33 of the gas fuel nozzle 3, only the gaseous fuel G1 is introduced into the first flow path 30.

In the illustrated embodiment, as shown in FIG. 2, the combustion air nozzle 4 is formed in a cylindrical shape defining a second flow path 40 radially outwardly of the gas fuel nozzle 3, with open ends at both ends. An end is provided. As shown in FIG. 2, the combustion air nozzle 4 has a tip 41, which is one open end, for supplying combustion air A (secondary air) flowing through the second flow path to the combustion space 10. It has a supply port 42 of. The combustion air nozzle 4 also has an inlet 43 at the other open end different from the tip 41 for introducing the combustion air A into the second flow path 40 .

In the illustrated embodiment, as shown in FIGS. 3 and 4, the combustion air nozzle 4 is formed into a rectangular tube shape. The combustion air nozzle 4 includes an upper side member 44 that extends horizontally above the gas fuel nozzle 3 and an upper side member 44 that extends below the gas fuel nozzle 3 along the horizontal direction in which the upper side member 44 extends. and a pair of side members 46 and 47 extending along the vertical direction orthogonal to the extending direction of the upper side member 44 on the sides of the gas fuel nozzle 3. The combustion air nozzle 4 is formed into a rectangular tube shape by welding the ends of an upper side member 44, a lower side member 45, and a pair of side members 46 and 47 to each other.
In some other embodiments, the combustion air nozzle 4 may have a shape other than a rectangular tube, for example, a round tube. Furthermore, the combustion air nozzle 4 may be an integrally molded product such as a cast metal, instead of combining a plurality of members.

In some embodiments, the gas burner device 2 includes the above-mentioned gas fuel nozzle 3, the above-mentioned combustion air nozzle 4, and the above-mentioned flame stabilizer 5, as shown in FIGS. 2 to 4. The flame stabilizer 5 is an outer flame stabilizer 6 that protrudes outward from the tip 31 of the gas fuel nozzle 3, as shown in FIGS. It includes an outer flame stabilizing member 6 that extends continuously along the outer peripheral edge 34.

"Extending continuously along the outer periphery 34 of the injection port 32" means, as shown in FIGS. 3 and 4, when the entire length of the outer periphery 34 of the injection port 32 is P1, This means that the flame stabilizing member 6 has a total length of a predetermined ratio with respect to the total length P1. In one embodiment, the outer flame stabilizing member 6 has a total length of 0.3 P1 or more and P1 or less. Preferably, the outer flame stabilizing member 6 has a total length of 0.4 P1 or more and P1 or less. More preferably, the outer flame stabilizing member 6 has a total length of 0.5 P1 or more and P1 or less.

According to the above configuration, as shown in FIG. 5, gas fuel G is supplied to the combustion space 10 from the gas fuel nozzle 3 (first flow path 30). Further, the combustion air A is supplied to the combustion space 10 from the combustion air nozzle 4 (second flow path 40) arranged around the gas fuel nozzle 3, and the area in the combustion space 10 to which the gas fuel G is supplied. is supplied to the radially outer region of the The gas burner device 2 includes a flame stabilizer 5 including an outer flame stabilizer 6 protruding outward from the tip 31 of the gas fuel nozzle 3, so that the combustion air A flowing around the outer flame stabilizer 6 is After flowing so as to wrap around the outer flame stabilizing member 6, it flows radially inward. The combustion air A flowing radially inward and the gas fuel G injected from the injection port 32 of the gas fuel nozzle 3 form a vortex V downstream of the injection port 32 even during low load. be done. By mixing the combustion air A drawn radially inward by the vortex V with the gas fuel G, the gas fuel G can be stably combusted. Further, according to the above configuration, the outer flame stabilizing member 6 extends continuously along the outer peripheral edge 34 of the injection port 32 of the gas fuel nozzle 3, so that it is possible to prevent the vortex V from being generated over a wide range. can. Therefore, according to the above configuration, the gas fuel G can be stably combusted even under low load.

In some embodiments, the above-mentioned flame stabilizer 5 is an inner flame stabilizer 7 that projects inward from the tip 31 of the gas fuel nozzle 3, as shown in FIGS. The fuel nozzle 3 further includes an inner flame stabilizing member 7 extending continuously along the inner peripheral edge 35 of the injection port 32 of the fuel nozzle 3 .

"Extending continuously along the inner peripheral edge 35 of the injection port 32" means, as shown in FIGS. 3 and 4, when the entire length of the inner peripheral edge 35 of the injection port 32 is P2, This means that the member 7 has a total length of a predetermined ratio with respect to the total length P2. In one embodiment, the inner flame stabilizing member 7 has a total length of 0.3 P2 or more and P2 or less. Preferably, the inner flame stabilizing member 7 has a total length of 0.4P2 or more and P2 or less. More preferably, the inner flame stabilizing member 7 has a total length of 0.5P2 or more and P2 or less.

According to the above configuration, as shown in FIG. 5, the flame stabilizer 5 includes the inner flame stabilizer 7 that protrudes inward from the tip 31 of the gas fuel nozzle 3. Even if the gaseous fuel G flows around the inner flame stabilizing member 7, the flow of the gas fuel G is disturbed. When the flow of the gas fuel G flowing around the inner flame stabilizing member 7 is disturbed, the gas fuel G stays near the injection port 32 of the gas fuel nozzle 3, so the ignition area E is moved to the injection port 32 of the gas fuel nozzle 3. The gas fuel G can be stably combusted. If the ignition area E is located downstream from the injection port 32 of the gas fuel nozzle 3 (on the combustion space 10 side in the direction in which the axis LA extends), the gas fuel G cannot be stably supplied to the ignition area E. Therefore, there is a risk that the combustion flame will blow out. Further, according to the above configuration, the inner flame stabilizing member 7 extends continuously along the inner peripheral edge 35 of the injection port 32 of the gas fuel nozzle 3. Since a large amount of gas fuel G can be retained in the vicinity, the ignition region E can be more reliably brought closer to the injection port 32 of the gas fuel nozzle 3, and the gas fuel G can be burned more stably. Therefore, according to the above configuration, the gas fuel G can be stably combusted even under low load.

In some embodiments, the inner flame stabilizing member 7 described above has a circular cross-sectional shape, as shown in FIG. In this case, since the inner flame stabilizing member 7 has a circular cross-sectional shape, it is possible to disturb the flow of the gaseous fuel G flowing around the inner flame stabilizing member 7, and also to disturb the flow of the gaseous fuel G flowing around the inner flame stabilizing member 7. It is possible to suppress the pressure loss of the gas flowing through the pipe. By suppressing the pressure drop of the gas, the gas fuel G can be burned more stably.
In addition, when the inner flame stabilizing member 7 is separate from the gas fuel nozzle 3, the inner flame stabilizing member 7 having a circular cross-sectional shape is easily available and can be attached to the gas fuel nozzle 3 by welding, etc. This makes the installation work easier.

In some other embodiments, the inner flame stabilizing member 7 described above has a rectangular cross-sectional shape. In this case, the flow of gas fuel G flowing around the inner flame stabilizing member 7 can be disturbed. Further, when the inner flame stabilizing member 7 is separate from the gas fuel nozzle 3, the inner flame stabilizing member 7 having a rectangular cross-sectional shape is easily available and can be attached to the gas fuel nozzle 3 by welding, etc. This makes the installation work easier.

In some embodiments, as shown in FIGS. 2 and 5, the outer flame stabilizing member 6 described above extends from the end surface 36 of the tip portion 31 toward the combustion space 10 side, and has a diameter with respect to the axis LA of the injection port 32. Extends to increase the directional distance.

In the illustrated embodiment, the gas burner device 2 further includes a rib 51 fixed to the outer surface of the outer flame stabilizing member 6 and the outer peripheral edge of the gas fuel nozzle 3, as shown in FIG.
In the illustrated embodiment, as shown in FIG. 5, the outer flame stabilizing member 6 has a rectangular cross-sectional shape, and is fixed to the end surface 36 of the tip 31 of the gas fuel nozzle 3 by welding W. has been done.

According to the above configuration, the outer flame stabilizing member 6 extends from the end surface 36 of the tip portion 31 toward the combustion space 10 side so that the radial distance from the axis LA of the injection port 32 increases. , most of the combustion air A flowing around the outer flame stabilizing member 6 can flow radially inward on the downstream side of the outer flame stabilizing member 6, and the vortex V can be generated more effectively. can. Therefore, according to the above configuration, the gas fuel G can be burned more stably.

In some other embodiments, the outer flame stabilizing member 6 extends from the outer peripheral edge 34 of the tip portion 31 toward the combustion space 10 so that the radial distance from the axis LA of the injection port 32 increases. You may do so. In some other embodiments, the outer flame stabilizing member 6 may extend radially outward from the end surface 36 or outer peripheral edge 34 of the tip portion 31.

In some embodiments, as shown in FIG. 3, the injection port 32 of the gas fuel nozzle 3 described above has a pair of long sides 371, 372 extending in parallel directions, and a pair of long sides 371, 372 extending in parallel directions. It has a rectangular annular shape including a pair of short sides 381 and 382 provided so as to connect the sides 371 and 372.

In the embodiment shown in FIG. 3, the injection port 32 has a longitudinal direction along the horizontal direction. The long side portion 371 extends along the horizontal direction and defines the upper side of the injection port 32 . The long side portion 372 is located below the long side portion 371 and extends along the horizontal direction, which is the direction in which the long side portion 371 extends, and defines the lower side of the injection port 32 . Each of the pair of short sides 381 and 382 extends along the vertical direction, which is a direction perpendicular to the extending direction of the long side 371, so as to connect the ends of the long side 371 and the long side 372. and defines the sides of the injection port 32.

In the embodiment shown in FIG. 3, the outer flame stabilizing member 6 extends continuously over the entire length of the rectangular outer peripheral edge 34. In the embodiment shown in FIG. As shown in FIG. 3, the outer flame stabilizing member 6 includes an outer flame stabilizing member 6A that extends linearly along the horizontal direction over the entire length of the outer peripheral edge 341 of the long side portion 371, and an outer flame stabilizing member 6A that extends linearly along the horizontal direction over the entire length of the outer peripheral edge 341 of the long side portion 371. An outer flame stabilizing member 6B that extends linearly along the horizontal direction over the entire length of the peripheral edge 342, and an outer flame stabilizing member 6C that extends linearly along the vertical direction over the entire length of the outer peripheral edge 343 of the short side portion 381. and an outer flame stabilizing member 6D extending linearly along the vertical direction over the entire length of the outer peripheral edge 344 of the short side portion 382.

In the embodiment shown in FIG. 3, the inner flame stabilizing member 7 includes an inner flame stabilizing member 7A that extends linearly along the horizontal direction over the entire length of the inner peripheral edge 351 of the long side portion 371, and It includes an inner flame stabilizing member 7B that extends linearly along the horizontal direction over the entire length of the inner peripheral edge 352.
In some other embodiments, the inner flame stabilizing member 7 may extend continuously over the entire length of the rectangular inner peripheral edge 35. In other words, the inner flame stabilizing member 7 extends linearly along the vertical direction over the entire length of the inner peripheral edge 353 of the short side portion 381, and the inner flame stabilizing member 7 extends vertically over the entire length of the inner peripheral edge 354 of the short side portion 382. It may also include an inner flame stabilizing member 7 that extends linearly along the direction.

According to the above configuration, the injection port 32 of the gas fuel nozzle 3 has a rectangular annular shape including a pair of long sides 371 and 372 and a pair of short sides 381 and 382. Here, the gas fuel G and combustion air A flowing around the corner 39 (see FIG. 3) of the injection port 32 are different from the gas fuel G and combustion air A flowing around the center of the long side and the center of the short side. Since the flow velocity is lower than that in A, it is difficult to generate a vortex V. According to the above configuration, since the outer flame stabilizing member 6 extends continuously along the outer peripheral edge 34 of the injection port 32 of the gas fuel nozzle 3, the vortex V can be generated over a wide range. Therefore, according to the above configuration, the gas fuel G can be stably combusted even downstream of the corner portion 39.

In some embodiments, as shown in FIG. 3, the above-mentioned outer flame stabilizing member 6 (6A, 6B) is continuously provided over the entire length of the outer peripheral edge 34 of at least one of the pair of long sides 371, 372. extend. In this case, the outer flame stabilizing member 6 (6A, 6B) continuously extends over the entire length of the outer peripheral edge 34 of at least one of the pair of long sides 371, 372, and therefore generates the vortex V over a wide range. In addition, the vortex V can be generated more stably downstream of the corner portion 39. Therefore, according to the above configuration, the gas fuel G can be stably combusted even downstream of the corner portion 39.

In some embodiments, as shown in FIG. 3, the above-described inner flame stabilizing member 7 (7A, 7B) is continuously provided over the entire length of the inner peripheral edge 35 of at least one of the pair of long sides 371, 372. extend. In this case, the inner flame stabilizing member 7 (7A, 7B) extends continuously over the entire length of the inner peripheral edge 35 of at least one of the pair of long sides 371, 372, so that A large amount of gas fuel G can be retained near the gas fuel nozzle 32, and the ignition region E can be brought closer to the injection port 32 of the gas fuel nozzle 3 more reliably. Further, according to the above configuration, the flow of the gas fuel G flowing around the corner portion 39 can be disturbed, so the gas fuel G can be burned more stably. Therefore, according to the above configuration, the gas fuel G can be stably combusted even under low load.

In some embodiments, as shown in FIG. 4, the injection port 32 of the gas fuel nozzle 3 described above is annular.
In the embodiment shown in FIG. 4, the flame stabilizer 5 includes an annular outer flame stabilizer 6E (outer flame stabilizer 6) that continuously extends over the entire length of the circular outer peripheral edge 34 of the injection port 32. , arc-shaped inner flame stabilizing members 7C and 7D (inner flame stabilizing members 7) that continuously extend along the circular inner peripheral edge 35 of the injection port 32.
In some other embodiments, the flame stabilizer 5 includes an arc-shaped outer flame stabilizer 6 that continuously extends along the circular outer periphery 34 of the injection port 32 or It may also include an annular inner flame stabilizing member 7 that extends continuously over the entire length of the circular inner peripheral edge 35 .

FIG. 6 is a schematic cross-sectional view along the axial direction of a gas burner device according to another embodiment of the present invention. FIG. 7 is a schematic diagram of the gas burner device shown in FIG. 6 viewed from the combustion space side.

In some embodiments, as shown in FIGS. 6 and 7, the gas fuel nozzle 3 described above includes a first gas fuel nozzle 3A housed inside the combustion air nozzle 4; A second gas fuel nozzle 3B is housed inside the combustion air nozzle 4 in which the combustion air nozzle 4 is housed, and a second gas fuel nozzle 3B is arranged in parallel to the first gas fuel nozzle 3A.
In the illustrated embodiment, the second gas fuel nozzle 3B is arranged below the first gas fuel nozzle 3A.

In the following description, when the configuration of the gas fuel nozzle 3 described above is that of the first gas fuel nozzle 3A, "first" may be added to the beginning and "A" is added to the code, and the second gas fuel nozzle If it is a 3B item, "second" may be added to the beginning and B may be added to the code. For example, the injection port 32 of the first gas fuel nozzle 3A is referred to as a first injection port 32A.

In the illustrated embodiment, as shown in FIG. 7, the first gas fuel nozzle 3A extends along a long side 371A (first long side) and a direction parallel to the long side 371A. A long side portion 372A (second long side portion).
In the illustrated embodiment, as shown in FIG. 7, the second gas fuel nozzle 3B has a long side portion 371B (third long side portion) extending along a direction parallel to the long side portion 371A. and a long side portion 372B (fourth long side portion) extending along a direction parallel to the long side portion 371B and disposed on the opposite side of the long side portion 372A with respect to the long side portion 371B; A rectangular annular second injection port 32B is provided.

In some embodiments, as shown in FIG. 7, the outer flame stabilizing member 6 of the first gas fuel nozzle 3A is provided over the entire length of the outer peripheral edge 341A of the long side 371A (first long side). an outer flame stabilizing member 6A (first outer flame stabilizing member), and an outer flame stabilizing member 6B (second outer flame stabilizing member) provided over the entire length of the outer peripheral edge 342A of the long side 372A (second long side). ,including. As shown in FIG. 7, the outer flame stabilizing member 6A of the first gas fuel nozzle 3A is viewed from the direction in which the axis LA of the first injection port 32A of the first gas fuel nozzle 3A extends (combustion space 10 side). The width of the first gas fuel nozzle 3A was larger than that of the outer flame stabilizing member 6B. That is, as shown in FIG. 7, the width D1 of the outer flame stabilizing member 6A of the first gas fuel nozzle 3A is larger than the width D2 of the outer flame stabilizing member 6B of the first gas fuel nozzle 3A.

According to the above configuration, the gas fuel nozzle 3 includes a first gas fuel nozzle 3A and a second gas fuel nozzle 3B housed inside the same combustion air nozzle 4. A long side 372A (second long side) of the first injection port 32A of the first gas fuel nozzle 3A and a long side 371B (third long side) of the second injection port 32B of the second gas fuel nozzle 3B. The combustion air A supplied to the combustion space 10 from the gap space 40A formed between the combustion air A and the combustion air A is used for combustion of the gas fuel G injected from the first gas fuel nozzle 3A and for combustion of the gas fuel G injected from the second gas fuel nozzle 3B. Since it is used for both the combustion of gas fuel G and the combustion of gas fuel G, there is a risk of a supply shortage. According to the above configuration, the width D1 of the outer flame stabilizing member 6A (first outer flame stabilizing member) of the first gas fuel nozzle 3A is set to To prevent insufficient supply of combustion air A by increasing the supply amount of combustion air A flowing around the outer flame stabilizing member 6A of the first gas fuel nozzle 3A by increasing the width D2 of the outer flame stabilizing member 6A of the first gas fuel nozzle 3A. Therefore, the gas fuel G can be stably combusted.

In some embodiments, as shown in FIG. 7, the outer flame stabilizing member 6 of the second gas fuel nozzle 3B is provided over the entire length of the outer peripheral edge 341B of the long side 371B (third long side). and an outer flame stabilizing member 6B (fourth outer flame stabilizing member) provided over the entire length of the outer peripheral edge 342B of the long side 372B (fourth long side). ,including. As shown in FIG. 7, the outer flame stabilizing member 6B (fourth outer flame stabilizing member) of the second gas fuel nozzle 3B extends in the direction in which the axis LA of the first injection port 32A of the first gas fuel nozzle 3A extends. When viewed from the combustion space 10 side, the width was configured to be larger than that of the outer flame stabilizing member 6A (third outer flame stabilizing member) of the second gas fuel nozzle 3B. That is, as shown in FIG. 7, the width D4 of the outer flame stabilizing member 6B of the second gas fuel nozzle 3B is larger than the width D3 of the outer flame stabilizing member 6A of the second gas fuel nozzle 3B.

According to the above configuration, the width D4 of the outer flame stabilizing member 6B (fourth outer flame stabilizing member) of the second gas fuel nozzle 3B is set to ) by increasing the supply amount of combustion air A flowing around the outer flame stabilizing member 6B of the second gas fuel nozzle 3B, it is possible to prevent insufficient supply of combustion air A. Therefore, the gas fuel G can be stably combusted.

The present invention is not limited to the embodiments described above, and also includes forms in which modifications are added to the embodiments described above, and forms in which these forms are appropriately combined.

1 Boiler 10 Combustion space 11 Boiler furnace 12 Combustion chamber 2 Gas burner device 3 Gas fuel nozzle 30 First flow path 31 Tip 32 Injection port 33 Inlet 34, 341-344 Outer periphery 35, 351-354 Inner periphery 36 End surface 371, 372 Long sides 381, 382 Short sides 39 Corner 4 Combustion air nozzle 40 Second flow path 41 Tip 42 Supply port 43 Inlet 44 Upper side member 45 Lower side members 46, 47 Side member 5 Flame stabilizer 51 Ribs 6, 6A to 6E Outer flame stabilizing member 7, 7A to 7D Inner flame stabilizing member 8 Gaseous fuel supply pipe 9 Gaseous fuel supply device A Combustion air A1 Primary air D1 to D4 Width E Ignition area G Gas fuel G1 Gaseous fuel LA Axis of the injection port P1 Total length of the outer periphery of the injection port P2 Total length of the inner periphery of the injection port V Eddy flow W Welding

Claims (7)

a gas fuel nozzle for supplying gas fuel to the combustion space;
a combustion air nozzle for supplying combustion air to the combustion space, the combustion air nozzle being disposed around the gas fuel nozzle;
A flame stabilizer including an outer flame stabilizer that protrudes outward from the tip of the gas fuel nozzle and that extends continuously along the outer periphery of the injection port of the gas fuel nozzle. and,
The flame stabilizer is an inner flame stabilizer that protrudes inward from the tip of the gas fuel nozzle, and is an inner flame stabilizer that extends continuously along the inner peripheral edge of the injection port of the gas fuel nozzle. further comprising a flame-holding member ;
The inner flame stabilizing member has a circular cross-sectional shape.
Gas burner equipment. The gas burner device according to claim 1 , wherein the outer flame stabilizing member extends from an end surface of the tip portion toward the combustion space so that a radial distance from the axis of the injection port increases. The injection port of the gas fuel nozzle has a rectangular shape including a pair of long sides extending in parallel directions and a pair of short sides connecting the pair of long sides. The gas burner device according to claim 1 or 2, which is annular. The gas burner device according to claim 3 , wherein the outer flame stabilizing member extends continuously over the entire length of an outer peripheral edge of at least one of the pair of long sides. The flame stabilizer is an inner flame stabilizer that protrudes inward from the tip of the gas fuel nozzle, and is an inner flame stabilizer that extends continuously along the inner peripheral edge of the injection port of the gas fuel nozzle. further comprising a flame-holding member;
The gas burner device according to claim 3 or 4 , wherein the inner flame stabilizing member extends continuously over the entire length of an inner peripheral edge of at least one of the pair of long sides. a gas fuel nozzle for supplying gas fuel to the combustion space;
a combustion air nozzle for supplying combustion air to the combustion space, the combustion air nozzle being disposed around the gas fuel nozzle;
A flame stabilizer including an outer flame stabilizer that protrudes outward from the tip of the gas fuel nozzle and that extends continuously along the outer periphery of the injection port of the gas fuel nozzle. and,
The gas fuel nozzle includes:
a first gas fuel nozzle housed within the combustion air nozzle;
a second gas fuel nozzle housed within the combustion air nozzle in which the first gas fuel nozzle is housed and arranged in parallel to the first gas fuel nozzle;
The first gas fuel nozzle includes a rectangular annular first injection port including a first long side and a second long side extending in a direction parallel to the first long side,
The second gas fuel nozzle has a third long side extending along a direction parallel to the first long side, and a third long side extending along a direction parallel to the third long side; a fourth long side portion disposed on the opposite side of the second long side portion with respect to the third long side portion;
The outer flame stabilizing member includes a first outer flame stabilizing member provided over the entire length of the outer periphery of the first long side portion, and a second outer flame stabilizing member provided over the entire length of the outer periphery of the second long side portion. , including;
The first outer flame stabilizing member is configured to be wider than the second outer flame stabilizing member when viewed from the direction in which the axis of the first injection port of the first gas fuel nozzle extends. gas burner equipment. The outer flame stabilizing member includes a third outer flame stabilizing member provided over the entire length of the outer periphery of the third long side portion, and a fourth outer flame stabilizing member provided over the entire length of the outer periphery of the fourth long side portion. , including;
The fourth outer flame stabilizing member is configured to be wider than the third outer flame stabilizing member when viewed from the direction in which the axis of the first injection port of the first gas fuel nozzle extends. The gas burner device according to claim 6 .

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