Crater rows, burners and gas appliances

Abstract

The present invention discloses a nozzle row, a combustor, and a gas appliance, in which the nozzle row is provided with an intake port, a combustion nozzle, and an injection guide channel communicating between the intake port and the combustion nozzle, the injection guide channel including a contraction section, a mixing section, and a diffuser section that communicate with each other along the intake direction, and the mixing section rapidly expands along the intake direction.

Description

[Technical Field]

[0001] This application claims priority from a Chinese patent application bearing application number 202322018587.6, filed with the China Patent Office on July 28, 2023, the entire contents of which are incorporated herein by reference.

[0002] The present invention relates to the technical field of gas appliances, and more particularly to a burner array, a combustor, and a gas appliance. [Background technology]

[0003] Gas appliances (e.g., gas water heaters, wall-mounted boilers, etc.) are appliances that release heat by burning gas to heat a medium (e.g., water). Among them, the combustor acts as a carrier for burning fuel, mixing gas (mixed gas and air), distributing the mixed gas evenly, and ensuring sufficient and stable combustion of the fuel. Combustors generally consist of multiple single burner rows. Summary of the Invention [Problem to be solved by the invention]

[0004] The main object of the embodiment of the present invention is to propose a nozzle row that improves the uniformity of the mixture of gas and air, achieves complete combustion, and improves thermal efficiency. [Means for solving the problem]

[0005] In order to achieve the above object, the present invention provides: A crater row is proposed, and the crater row is provided with an air inlet, a combustion crater, and a jet guide channel communicating between the air inlet and the combustion crater.

[0006] In one embodiment, the jet guide channel comprises a contraction section, a mixing section, and a diffuser section that communicate with each other along the intake direction, and the mixing section expands suddenly along the intake direction.

[0007] In one embodiment, the mixing section includes a throttling section and a sudden change section, and the contraction section, the throttling section, the sudden change section, and the diffuser section communicate with each other along the intake direction.

[0008] In one embodiment, the constriction section is the narrowest portion of the jet guide channel and the abrupt change section expands from the constriction section towards the diffuser section.

[0009] In one embodiment, the abrupt change portion and the diffuser portion are both provided to gradually expand along the intake direction, and an expansion angle of the abrupt change portion is greater than an expansion angle of the diffuser portion.

[0010] In one embodiment, in a cross section perpendicular to the intake direction, the maximum radial dimension of the intake port is a, the maximum radial dimension of the constricted portion is b, and the value of b / a is 0.4 or more and 0.6 or less.

[0011] In one embodiment, the value of b / a is 0.5.

[0012] In one embodiment, the peripheral wall of the abrupt change section is inclined away from the centerline of the jet guide channel relative to the peripheral wall of the throttle section.

[0013] In one embodiment, an included angle α is formed between a peripheral wall of the abrupt change portion and a peripheral wall of the throttle portion, and α is equal to or greater than 120° and equal to or less than 170°.

[0014] In one embodiment, the distance between the intake port and the outlet of the mixer section is L1, the distance between the intake port and the outlet of the diffuser section is L2, and the value of L1 / L2 is greater than or equal to 0.2 and less than or equal to 0.5.

[0015] In one embodiment, the nozzle array includes a panel having a hollow region and a metal mesh laminated to the panel.

[0016] In one embodiment, the combustion nozzle is formed in a portion of the metal mesh that covers the hollow region.

[0017] In one embodiment, stopper portions are provided on opposite sides of the nozzle row, and the stopper portions located on both sides abut against the edge portions on both sides of the surface of the metal mesh that is away from the panel.

[0018] The invention further proposes a combustor comprising a row of nozzles as described above.

[0019] The present invention further proposes a gas appliance including the above-described combustor.

[0020] The nozzle array of the present invention includes an intake port, a combustion nozzle, and an injection guide channel connecting the intake port and the combustion nozzle. The injection guide channel includes a contraction section, a mixing section, and a diffuser section that are connected to each other along the intake direction, and the mixing section expands rapidly along the intake direction. In this way, the gas-air mixture enters the contraction section from the intake port and rapidly contracts and converges within the contraction section, causing the mixture to have a higher flow velocity. The high-speed mixture flows through the mixing section and rapidly expands near the diffuser section before entering the diffuser section for further mixing. In this way, the injection guide channel can have multiple changes in the intake direction, allowing the mixture to rapidly contract and expand, thereby increasing the turbulence effect and improving the uniformity of the gas-air mixture, thereby achieving complete fuel combustion, improving fuel utilization, and improving thermal efficiency. [Brief explanation of the drawings]

[0021] In order to more clearly describe the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art are briefly introduced above. Obviously, the above drawings are only some embodiments of the present invention, and those skilled in the art can also obtain other related drawings based on these drawings without any creative efforts. [Figure 1] FIG. 1 is a structural schematic diagram of an embodiment of a nozzle row of the present invention. [Figure 2] FIG. 2 is a front view of the crater row in FIG. 1. [Figure 3] This is a schematic cross-sectional view of the crater row in Figure 1 cut at the sudden change part. [Figure 4] FIG. 2 is a schematic diagram of a partial cross section of the crater row in FIG. 1. [Figure 5] FIG. 5 is an enlarged schematic diagram of a partial cross section of the crater row in FIG. 4. [Figure 6] This is a schematic structural diagram of the crater row in Figure 1 from another perspective. DETAILED DESCRIPTION OF THE INVENTION

[0022] The realization of the objects, functional features and advantages of the present invention will be further explained with reference to the examples and drawings.

[0023] The following clearly and completely describes the technical solutions of the embodiments of the present invention with reference to the drawings of the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are included in the protection scope of the present invention.

[0024] In addition, when directional indications (up, down, left, right, forward, backward, etc.) are included in an embodiment of the present invention, the directional indications are used only to explain the relative positional relationships and movement states between parts in a specific posture, and if the specific posture changes, the directional indications also change accordingly.

[0025] Furthermore, terms such as "first" and "second" in the embodiments of the present invention are used for descriptive purposes only and should not be understood as indicating or implying their relative importance or the number of technical features described. Therefore, features defined as "first" and "second" may explicitly or implicitly include at least one of the features. Furthermore, "and / or" in this specification means three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution that simultaneously satisfies both A and B. Furthermore, technical solutions in each embodiment may be combined with each other, but this must be based on the feasibility of a person skilled in the art. If a combination of technical solutions is inconsistent or cannot be realized, such a combination of technical solutions does not exist and is not considered to be within the scope of protection claimed by the present invention.

[0026] In the related art, the nozzle row of the combustor is provided with an injection guide channel for introducing the mixed gas, and the injection guide channel generally contracts from the intake port toward the inside of the channel and then gradually expands. Because the entire channel does not change smoothly, the mixing uniformity of the gas and air is low, which is unfavorable for complete combustion of the gas, and the thermal efficiency is low.

[0027] The present invention proposes a crater array 100 .

[0028] 1 to 3, in one embodiment of the present invention, the nozzle row 100 is provided with an intake port 101, a combustion nozzle 102, and an injection guide channel 10 that communicates between the intake port 101 and the combustion nozzle 102, and the injection guide channel 10 has a contraction section 11, a mixing section 12, and a diffuser section 13 that communicate with each other along the intake direction, and the mixing section 12 expands suddenly along the intake direction.

[0029] Specifically, the nozzle array 100 includes an intake port 101, a combustion nozzle 102, and an injection guide channel 10. A gas-air mixture enters the intake port 10 from the intake port 101, is thoroughly mixed in the injection guide channel 10, and is then sent to the combustion nozzle 102, where the mixture is ignited to achieve combustion. The injection guide channel 10 includes a contraction section 11, a mixing section 12, and a diffuser section 13, which are connected to each other along the intake direction. The contraction section 11 gradually contracts along the intake direction, the diffuser section 13 gradually expands along the intake direction, and the mixing section 12 connects the narrow end of the contraction section 11 to the narrow end of the diffuser section 13. The mixing section 12 expands rapidly along the intake direction, i.e., the cross-sectional dimension of the mixing section 12 at its end closest to the contraction section is small, while the cross-sectional dimension of the mixing section 12 at its end closest to the diffuser section 13 is large. The change in the cross-sectional dimension of the mixing section 12 in the intake direction is not a continuous linear change but has a clear gradient. In this way, the gas-air mixture enters the contraction section 11 from the intake port 101 and rapidly contracts and converges within the contraction section 11, resulting in a higher flow velocity of the mixture entering the mixing section 12. The high-speed mixture flows through the mixing section 12 and rapidly expands as it reaches the portion close to the diffuser section 13 before entering the diffuser section 13 for further mixing. In this way, the injection guide channel 10 can have multiple changes in the intake direction, allowing the mixture to rapidly contract and expand, thereby increasing the turbulence effect and improving mixing uniformity.

[0030] Specifically, in this embodiment, as shown in Figures 1 and 2, the nozzle array 100 includes a nozzle array main body and a combustion head provided on the upper part of the nozzle array main body. The nozzle array main body is provided with an air inlet 101 and an injection guide channel 10. The combustion head is provided with a plurality of combustion nozzles 102. The air inlet 101 communicates with the combustion nozzles 102 via the injection guide channel 10. The air inlet 101 is provided on a first side of the nozzle array main body, and the injection guide channel 10 extends from the first side to the second side of the nozzle array main body. For example, as shown in Figure 2, the air inlet 101 is provided on the left side of the nozzle array main body, and the injection guide channel extends from left to right. At this time, the mixed gas enters the injection guide channel 10 horizontally from the first side of the nozzle array main body and is sent toward the second side. 1 , the nozzle array body further includes a curved channel 20 and a diversion channel 30, one end of which is connected to the outlet end of the jet guide channel 10, and the other end of which is located above the jet guide channel 10 and connected to the inlet end of the diversion channel 30, the diversion channel 30 extending from the second side of the nozzle array body toward the first side of the nozzle array body, and the diversion channel 30 communicating with a plurality of combustion nozzles 102. In one embodiment, the nozzle array body includes two half cases joined together, which surround the intake port 101, the jet guide channel 10, the curved channel 20, and the diversion channel 30. Here, the half cases can be formed by stamping sheet metal parts to form corresponding hollow channels, and then the two half cases can be fixed together by welding.

[0031] The nozzle array 100 according to the technical solution of the embodiment of the present invention includes an intake port 101, a combustion nozzle 102, and an injection guide channel 10 connecting the intake port 101 and the combustion nozzle 102. The injection guide channel 10 includes a contraction section 11, a mixing section 12, and a diffuser section 13, which are connected to each other along the intake direction, and the mixing section 12 expands rapidly along the intake direction. In this way, the gas and air mixture enters the contraction section 11 from the intake port 101 and rapidly contracts and gathers in the contraction section 11, causing the mixture to have a higher flow velocity in the mixing section 12. The high-speed mixture flows through the mixing section 12 and rapidly expands when it reaches a position close to the diffuser section 13, before entering the diffuser section 13 for further mixing. In this way, the injection guide channel can be changed at multiple points in the intake direction, and the mixed gas can be rapidly contracted and expanded, thereby increasing the turbulence effect and improving the mixing uniformity of gas and air, thereby achieving complete fuel, improving fuel utilization rate, and improving thermal efficiency.

[0032] As shown in Figures 4 and 5, in one embodiment, the mixing section 12 includes a constriction section 121 and a sudden change section 122, and the contraction section 11, the constriction section 121, the sudden change section 122, and the diffuser section 13 are connected to each other along the intake direction, the constriction section 121 is the narrowest part of the injection guide channel 10, and the sudden change section 122 expands from the constriction section 121 toward the diffuser section 13.

[0033] In one embodiment, the mixing section 12 includes a constriction section 121 and a sudden change section 122. The constriction section 121 has a cylindrical shape extending straight generally along the intake direction, and the sudden change section 122 has a truncated cone shape gradually expanding generally along the intake direction, with the cross-sectional dimension of the constriction section 121 being small and the cross-sectional dimension of the sudden change section 122 being large. That is, a clear sudden change step (i.e., the sudden change section 122) is formed in a portion of the mixing section 12 close to the diffuser section 13, thereby creating the effect of the mixing section 12 suddenly expanding toward the gradual expansion section. The constriction section 121 is the narrowest part of the injection guide channel 10, and the mixed gas rapidly contracts through the contraction section 11 before entering the constriction section 121, where the flow velocity of the mixed gas becomes maximum. The high-speed mixed gas in the constriction section 121 enters the sudden change section 122, where it rapidly expands before entering the diffuser section 13, thereby increasing the turbulence effect.

[0034] In order to further improve the uniformity of the gas and air mixing, in one embodiment, as shown in FIG. 5, the sudden change section 122 and the diffuser section 13 are both configured to gradually expand along the intake direction, and the expansion angle of the sudden change section 122 is greater than the expansion angle of the diffuser section 13.

[0035] In one embodiment, both the sudden change section 122 and the diffuser section 13 gradually expand along the intake direction, and the expansion angle of the sudden change section 122 is greater than that of the diffuser section 13. That is, in the axial cross section of the injection guide channel 10, the included angle between the two edges of the sudden change section 122 must be greater than the included angle between the two edges of the diffuser section 13. In this way, the mixed gas rapidly contracts in the contraction section 11 and enters the throttling section 121, and then rapidly expands in the sudden change section 122 to enter the diffuser section 13. During this process, the mixed gas located on the outer periphery of the throttling section 121 enters the sudden change section 122, generating a large expansion angle. On the other hand, when the gas enters the diffuser section 13, the expansion angle of the diffuser section 13 is relatively small, so the gas mixture on the outer periphery expands and collides with the wall of the flow path of the diffuser section 13, then bounces back to the center of the flow path and collides again with the gas mixture on the inner periphery, which greatly increases the turbulence effect, makes the gas mixture more uniform, is more favorable for complete combustion, fully releases fuel heat, and improves thermal efficiency.

[0036] In the prior art, the ratio between the narrowest part of the jet guide channel 10 of the nozzle row 100 and the intake port 101 is large. When the wind speed of the fan of the gas appliance fluctuates, the air volume fluctuates and the amount of air entering the flow path also fluctuates greatly, resulting in a mismatch between the gas and air volumes, further destabilizing combustion.

[0037] In order to further improve the stability of combustion, in one embodiment, as shown in FIG. 4, in a cross section perpendicular to the intake direction, the maximum radial dimension of the intake port 101 is a, the maximum radial dimension of the constricted portion 121 is b, and the value of b / a is 0.4 or more and 0.6 or less.

[0038] In one embodiment, the intake port 101 is configured to have an oval shape extending generally vertically, and the cross section of the constricted portion 121 is configured to have an elliptical shape extending generally vertically. The vertical dimension of the intake port 101 is the maximum radial dimension a of the intake port 101, and the vertical dimension of the cross section of the constricted portion 121 is the maximum radial dimension b of the constricted portion 121. Of course, the cross sections of the intake port 101 and the constricted portion 121 may be designed to have other shapes, and are not specifically limited herein. Here, the value of b / a is 0.6 or less. By keeping the dimensional ratio of the narrowest portion of the injection guide channel 10 (i.e., the constricted portion 121) to the intake port 101 relatively small, the flow resistance can be appropriately increased. Therefore, even if the amount of air entering the flow path decreases when the wind speed of the fan of the gas appliance fluctuates, the gas-to-air ratio is not affected, and combustion becomes more stable. By limiting the value of b / a to 0.4 or more, it is possible to avoid an excessive increase in resistance and ensure that the mixed gas flows smoothly along the injection guide channel 10. Specifically, 0.4≦b / a≦0.6. For example, the value of b / a may be 0.4, 0.45, 0.5, 0.55, 0.6, etc.

[0039] In one embodiment, the value of b / a is 0.5, which provides a moderate resistance to the flow path and makes the gas-to-air ratio less susceptible to fluctuations in wind speed, further improving combustion stability.

[0040] As shown in FIG. 2, in one embodiment, the peripheral wall of the abrupt change portion 122 is inclined away from the center line of the jet guide channel 10 relative to the peripheral wall of the constriction portion 21, and an included angle α is formed between the peripheral wall of the abrupt change portion 122 and the peripheral wall of the constriction portion 121, and α is greater than or equal to 120° and less than or equal to 170°.

[0041] In one embodiment, the included angle α is between 120° and 170°, and the inclination angle of the peripheral wall of the sudden change portion 122 relative to the peripheral wall of the constriction portion 121 is moderate, which is advantageous for causing the airflow around the outer periphery of the constriction portion 121 to rapidly expand outward, collide with the side wall of the flow path, bounce back, and collide again with the mixed gas around the inner periphery, thereby enhancing the turbulence effect. Specifically, 120°≦α≦170°. For example, the included angle α may be 120°, 130°, 140°, 150°, 160°, 170°, etc.

[0042] 2, in one embodiment, the distance between the intake port 101 and the outlet of the mixer section 12 is L1, the distance between the intake port 101 and the outlet of the diffuser section 13 is L2, and the value of L1 / L2 is 0.2 or more and 0.5 or less. In this way, a sufficient distance of the diffuser section 13 can be ensured to sufficiently mix the gas and air. Specifically, 0.2≦L1 / L2≦0.5. For example, the value of L1 / L2 may be 0.2, 0.3, 0.4, 0.5, etc.

[0043] In one embodiment, the inner peripheral surface of the contraction section 11 is a smoothly curved surface, which reduces the resistance of the contraction section 11 and is advantageous for the gas mixture to flow rapidly and contract within the contraction section 11.

[0044] Based on the above embodiment, as shown in Figure 6, in one embodiment, the nozzle row 100 comprises a panel 40 having a hollow region and a metal mesh 50 arranged so as to be laminated to the panel 40, the combustion nozzle 102 is formed in the portion of the metal mesh 50 covering the hollow region, and stopper portions are provided on both opposing sides of the nozzle row 100, and the stopper portions located on both sides abut against the edge portions on both sides of the surface of the metal mesh 50 facing away from the panel 40.

[0045] In one embodiment, the metal mesh 50 may be laminated on the rear or front side of the panel 40. In one embodiment, the metal mesh 50 is laminated on the rear side of the panel 40. The stoppers on both sides of the nozzle array 100 stop the edges of the metal mesh 50 on both sides, so that the side edges of the edge of the metal mesh 50 are sandwiched between the panel 40 and the stoppers, making the edges of the metal mesh 50 less likely to warp and ensuring the flatness of the metal mesh 50. Compared to the conventional method of welding the metal mesh to the panel, this solution does not have the problem of the metal mesh 50 having high resistance at the welding points and low resistance at the warping points, making the resistance of the combustion surface of the nozzle array 100 uniform, which is advantageous for improving the uniformity and stability of combustion, making flashbacks and flame separation less likely to occur, and avoiding combustion noise and resonance caused by flame oscillation. Combined with the structural design of the injection guide channel 10 in the above embodiment, the air-gas mixture enters the injection guide channel 10 from the air inlet 101, is thoroughly mixed and homogenized, and then flows to the combustion nozzle 102 for combustion. This, combined with the mesh structure of the metal mesh 50 itself and the flatness of the installation of the metal mesh 50, makes the combustion in the metal mesh 50 more uniform and stable, which is advantageous in achieving a better low-nitrogen combustion effect.

[0046] The present invention further proposes a combustor including a nozzle array 100. The specific structure of the nozzle array 100 can be referred to the above embodiments, and since this combustor adopts all the technical solutions of all the above embodiments, it has at least all the effects brought by the technical solutions of the above embodiments, and therefore, they will not be described again here.

[0047] The present invention further proposes a gas appliance equipped with a combustor, the specific structure of which can be referred to the above embodiments, and since this gas appliance adopts all the technical solutions of all the above embodiments, it has at least all the effects brought by the technical solutions of the above embodiments, and therefore will not be repeated here.

[0048] The above description is merely a possible embodiment of the present invention and is not intended to limit the patent scope of the present invention. Under the technical concept of the present invention, any equivalent structural transformation made by utilizing the contents of the specification and drawings of the present invention, or any direct or indirect application to other related technical fields, shall all be included in the patent protection scope of the present invention. [Explanation of symbols]

[0049] 100 Crater Chain 101 Air intake 102 Combustion crater 10. Jet induction channel 11 Contraction section 12 Mixing section 121 Constriction section 122 Sudden changes 13 Diffuser section 20 curved channels 30 Diversion Channels 40 panels 50 metal mesh

Claims

1. A crater chain, an intake port, a combustion nozzle, and a jet guide channel communicating between the intake port and the combustion nozzle; the injection guide channel includes a contraction section, a mixing section, and a diffuser section that communicate with each other along an intake direction; The mixing section expands suddenly along the intake direction. Crater row.

2. the mixing section includes a throttling section and a sudden change section, the constriction section, the sudden change section, and the diffuser section are in communication with one another along the intake direction, the throttling section is the narrowest portion of the injection guide channel, and the sudden change section expands from the throttling section toward the diffuser section.

2. The nozzle array of claim 1.

3. the sudden change portion and the diffuser portion are both provided to gradually expand along the intake direction, and an expansion angle of the sudden change portion is larger than an expansion angle of the diffuser portion.

3. The crater row according to claim 2.

4. In a cross section perpendicular to the intake direction, a maximum radial dimension of the intake port is a, a maximum radial dimension of the throttle portion is b, and a value of b / a is 0.4 or more and 0.6 or less. The crater row according to claim 2 or 3.

5. The value of b / a is 0.

5.

5. The crater row according to claim 4.

6. The peripheral wall of the abrupt change portion is inclined away from the center line of the jet guide channel with respect to the peripheral wall of the constriction portion, and an included angle α is formed between the peripheral wall of the abrupt change portion and the peripheral wall of the constriction portion, and the angle α is 120° or more and 170° or less. The nozzle row according to any one of claims 2 to 5.

7. a distance between the intake port and an outlet of the mixing section is L1, a distance between the intake port and an outlet of the diffuser section is L2, and a value of L1 / L2 is equal to or greater than 0.2 and equal to or less than 0.5; The nozzle row according to any one of claims 1 to 6.

8. The crater row includes a panel having a hollow region and a metal mesh laminated to the panel, the combustion craters are formed in a portion of the metal mesh covering the hollow region, and stopper portions are provided on both opposing sides of the crater row, and the stopper portions located on both sides abut against both edge portions of the surface of the metal mesh that is away from the panel. The nozzle row according to any one of claims 1 to 7.

9. 1. A combustor comprising: A nozzle row according to any one of claims 1 to 8, Combustor.

10. A gas appliance, 10. A combustor comprising: Gas appliances.

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