A three-ring burner suitable for aircraft stoves

Abstract

A three-ring burner suitable for aircraft furnace end, comprising: gas distribution lower disc, gas distribution upper disc, center fire cover, inner ring fire cover and outer ring fire cover; the lower side cover of the gas distribution upper disc is arranged on the upper side of the gas distribution lower disc and surrounds to form an outer ring gas mixing chamber; the outer ring gas mixing chamber is communicated with the outer ring gas inlet hole; the upper side of the gas distribution upper disc is provided with an outer ring gas supply seat and an inner ring gas supply seat; the outer ring gas supply seat is communicated with the outer ring gas mixing chamber; the inner ring gas supply seat is communicated with the inner ring gas inlet hole; the outer ring fire cover and the inner ring fire cover are respectively arranged on the outer ring gas supply seat and the inner ring gas supply seat; the middle part of the inner ring gas supply seat is provided with a center gas supply channel penetrating through the upper and lower parts; the center gas supply channel is connected to the upper part of the center gas inlet cylinder and is used for connecting the center fire cover. The utility model, through the innovative combination structure of the gas distribution lower disc and the gas distribution upper disc, successfully realizes the independent and stable combustion of the three-ring flame on the basis of the traditional aircraft furnace end double-injection pipe.

Description

Technical Field

[0001] This utility model relates to the field of burner technology, and in particular to a three-ring burner suitable for aircraft stove heads. Background Technology

[0002] The "aircraft burner head," also known as the "square burner head," is a type of burner head with dual ejector tubes. It adopts a coaxial nested mixing chamber structure, which has higher combustion efficiency and greater versatility compared to the independent dual ejector tube burner head structure without a mixing chamber. Therefore, this type of burner head is widely used.

[0003] Aircraft burners are typically paired with simple, low-cost dual-ring gas distribution plates and burner caps. Therefore, their flame combustion zones are usually limited to a dual-ring burner structure, restricting the display effect of the combustion flame. Furthermore, the simple two-ring flame zone combustion effect is not conducive to improving the uniformity of gas mixing and distribution. Therefore, further improvements are needed. Utility Model Content

[0004] This invention aims to solve at least one of the technical problems existing in the prior art. To this end, this invention proposes a three-ring burner suitable for aircraft stove heads.

[0005] The technical solution adopted by one embodiment of this utility model to solve its technical problem is: a three-ring burner suitable for aircraft stove heads, including: a lower gas distribution plate, an upper gas distribution plate, a central burner cover, an inner ring burner cover and an outer ring burner cover; The lower gas distribution plate is provided with an outer ring air inlet cylinder and a central air inlet cylinder arranged coaxially and nested, which are connected to the outer ring air supply cylinder and the central air supply cylinder arranged coaxially and nested in the aircraft stove head; the outer ring air inlet cylinder is provided with an inner gas distribution plate; the gas distribution plate is provided with an inner ring air inlet hole and an outer ring air inlet hole. The lower side of the upper gas distributor plate is covered on the upper side of the lower gas distributor plate, forming an outer ring mixing chamber; the outer ring mixing chamber is connected to the outer ring air inlet; an outer ring air supply seat and an inner ring air supply seat are provided on the upper side of the upper gas distributor plate; the outer ring air supply seat is connected to the outer ring mixing chamber; the inner ring air supply seat is connected to the inner ring air inlet; the outer ring burner cap and the inner ring burner cap are respectively covered on the outer ring air supply seat and the inner ring air supply seat; a central air supply channel that runs vertically through the middle of the inner ring air supply seat is provided; the central air supply channel is connected to the top of the central air inlet cylinder and is used to connect to the central burner cap.

[0006] Optionally, the outer periphery of the upper gas distribution plate is provided with a plurality of outer ring connecting air passages at circumferential intervals, which are used to connect the outer ring mixing chamber and the outer ring air supply seat.

[0007] Optionally, the gap space between two adjacent outer ring connecting airways forms a secondary air supply channel.

[0008] Optionally, the upper air distribution plate is provided with an inner ring connecting air passage; the upper part of the inner ring connecting air passage is connected to the inner ring air supply seat, and the lower part abuts against the air distribution plate and is connected to the inner ring air inlet.

[0009] Optionally, the base plate of the gas distribution plate has a conical plate structure with a central upward convexity; the cross-section of the outer ring mixing chamber gradually narrows from the middle to the outer edge.

[0010] Optionally, the upper and lower gas distribution plates are provided with ignition mounting holes for installing ignition components; an ignition protrusion is provided on one side of the inner ring burner cap, extending from the inner ring burner cap toward the ignition mounting hole; the ignition protrusion is provided with an ignition hole or an ignition groove.

[0011] Optionally, an ignition clearance groove is provided on one side of the inner ring gas supply seat, and the ignition protrusion is embedded in the ignition clearance groove.

[0012] The beneficial effects of this invention are as follows: Through an innovative combination structure of the lower and upper gas distribution plates, independent and stable combustion of a three-ring flame is successfully achieved based on the traditional dual-ejector tube design of aircraft stoves. This design not only significantly enhances the layering and visual appeal of the flame, enriching the combustion display effect, but also effectively optimizes the uniformity of gas mixing and distribution through the added outer ring mixing chamber and the precisely arranged inner and outer ring air inlets on the gas distribution plate, thereby improving combustion efficiency and reducing pollutant emissions. Furthermore, this structure fully utilizes the coaxial nested interface of the original aircraft stove, enabling functional upgrades without modifying the main body of the stove, combining good versatility and economy.

[0013] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0014] The above and / or additional aspects and advantages of this utility model will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which: Figure 1 This is a schematic diagram of the burner structure of this utility model; Figure 2 for Figure 1 Exploded view of the burner; Figure 3 for Figure 1 Another exploded view of the burner; Figure 4 for Figure 1 Cross-sectional view of the burner.

[0015] Explanation of key component symbols: 10. Lower gas distributor plate; 11. Outer ring air inlet cylinder; 12. Central air inlet cylinder; 13. Gas distributor plate; 14. Inner ring air inlet; 15. Outer ring air inlet; 20. Upper gas distributor plate; 21. Outer ring air supply seat; 22. Inner ring air supply seat; 221. Ignition clearance groove; 23. Central air supply channel; 24. Outer ring connecting air channel; 25. Secondary air supply channel; 26. Inner ring connecting air channel; 30. Inner ring burner cap; 31. Ignition protrusion; 40. Outer ring burner cap; 50. Outer ring mixing chamber; 60. Ignition mounting hole. Detailed Implementation

[0016] This section will describe in detail the specific embodiments of the present utility model. The preferred embodiments of the present utility model are shown in the accompanying drawings. The purpose of the drawings is to supplement the textual description with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the present utility model, but they should not be construed as limiting the scope of protection of the present utility model.

[0017] In the description of this utility model, "multiple" means two or more; "greater than," "less than," and "exceeding" are understood to exclude the stated number; "above," "below," and "within" are understood to include the stated number. The use of "first" and "second" in the description is merely for distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly specifying the number of indicated technical features or their sequential relationship.

[0018] In the description of this utility model, it should be understood that the directional descriptions, such as up, down, front, back, left, right, etc., indicate the directional or positional relationship based on the directional or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0019] In this utility model, unless otherwise explicitly defined, the terms "setting," "installing," and "connecting" should be interpreted broadly. For example, they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to a fixed connection, a detachable connection, or an integral molding; they can refer to a mechanical connection; they can refer to the internal connection of two components or the interaction between two components. Those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model in conjunction with the specific content of the technical solution.

[0020] Example Reference Figures 1 to 4 The present invention proposes a three-ring burner suitable for aircraft stove heads, comprising: a lower gas distribution plate 10, an upper gas distribution plate 20, a central burner cap, an inner ring burner cap 30, and an outer ring burner cap 40. The lower gas distribution plate 10 is provided with an outer ring air inlet cylinder 11 and a central air inlet cylinder 12 arranged coaxially and nested, which are connected to the outer ring air supply cylinder and the central air supply cylinder arranged coaxially and nested in the aircraft stove head; the outer ring air inlet cylinder 11 is provided with an inner air distribution plate 13; the air distribution plate 13 is provided with an inner ring air inlet hole 14 and an outer ring air inlet hole 15. The upper gas distribution plate 20 is covered on the upper side of the lower gas distribution plate 10, forming an outer ring mixing chamber 50. The outer ring mixing chamber 50 is connected to the outer ring air inlet 15. An outer ring air supply seat 21 and an inner ring air supply seat 22 are provided on the upper side of the upper gas distribution plate 20. The outer ring air supply seat 21 is connected to the outer ring mixing chamber 50. The inner ring air supply seat 22 is connected to the inner ring air inlet 14. The outer ring burner cap 40 and the inner ring burner cap 30 are respectively covered on the outer ring air supply seat 21 and the inner ring air supply seat 22. A central air supply channel 23 is provided in the middle of the inner ring air supply seat 22. The central air supply channel 23 is connected to the top of the central air inlet cylinder 12 and is used to connect the central burner cap.

[0021] In this invention, through an innovative combination of the lower gas distribution plate 10 and the upper gas distribution plate 20, independent and stable combustion of a three-ring flame is successfully achieved based on the traditional dual-ejector tube of an aircraft stove. This design not only significantly enhances the layering and visual appeal of the flame, enriching the combustion display effect, but also effectively optimizes the uniformity of gas mixing and distribution through the added outer ring mixing chamber 50 and the precisely arranged inner and outer ring air inlets 15 on the gas distribution plate 13, thereby improving combustion efficiency and reducing pollutant emissions. Furthermore, this structure fully utilizes the coaxial nested interface of the original aircraft stove, enabling functional upgrades without modifying the main body of the stove, combining good versatility and economy.

[0022] In this embodiment, a plurality of outer ring connecting air channels 24 are arranged circumferentially around the outer periphery of the upper gas distribution plate 20 to connect the outer ring mixing chamber 50 and the outer ring air supply seat 21. This achieves efficient and uniform connection between the outer ring mixing chamber 50 and the outer ring air supply seat 21, effectively preventing uneven flame length or partial flameout caused by uneven air supply in the outer ring flame, resulting in a more complete and stable outer ring flame and better combustion effect.

[0023] Furthermore, the gap between two adjacent outer ring connecting air passages 24 forms a secondary air supply passage 25. These passages can introduce additional air (secondary air) from the bottom during flame combustion, directly supplying the root of the outer ring flame, greatly improving the oxygen demand conditions for gas combustion.

[0024] In this embodiment, the upper gas distribution plate 20 is provided with an inner ring connecting gas channel 26; the upper part of the inner ring connecting gas channel 26 is connected to the inner ring gas supply seat 22, and the lower part abuts against the gas distribution plate 13 and connects to the inner ring air inlet 14. By setting up a dedicated inner ring connecting gas channel 26 and directly abutting its lower end against the inner ring air inlet 14 of the gas distribution plate 13, an independent and smooth flow path is established for the inner ring gas from the lower gas distribution plate 10 directly to the inner ring gas supply seat 22. This point-to-point direct connection method minimizes the gas flow resistance and flow path cross interference, ensuring the response speed and stability of the inner ring gas supply, thereby ensuring that the inner ring flame can be quickly and independently ignited and adjusted.

[0025] In this embodiment, the base plate of the upper gas distribution plate 20 has a conical plate structure with a central upward convex shape; the outer ring mixing chamber 50 gradually narrows in cross-section from the middle to the outer edge. This tapering flow channel structure conforms to fluid mechanics principles, accelerating and pressurizing the flowing gas mixture, helping the gas to fill the entire mixing chamber more quickly and smoothly and flow towards the burner cap. This not only improves the dynamic uniformity of gas distribution but also helps maintain stable pressure within the chamber, thus providing structural protection for flame stability.

[0026] In this embodiment, the upper gas distribution plate 20 and the lower gas distribution plate 10 are provided with ignition mounting holes 60 for installing ignition components; an ignition protrusion 31 is provided on one side of the inner ring burner cap 30, extending from the inner ring burner cap 30 toward the ignition mounting hole 60; the ignition protrusion 31 has an ignition hole or an ignition groove. The electric spark or small flame generated during ignition can directly ignite the gas in the inner ring burner cap 30 through the ignition hole / groove, and then the inner ring flame can quickly and reliably ignite the adjacent central and outer ring flames. This central ignition method has a high success rate, solves the technical problem that it is difficult to ignite the flames of each ring in a multi-ring burner simultaneously and reliably, and improves the safety of the product and the user experience. Furthermore, an ignition clearance groove 221 is provided on one side of the inner ring gas supply seat 22, and an ignition protrusion 31 is embedded in the ignition clearance groove 221. The ignition clearance groove 221 is provided on one side of the inner ring gas supply seat 22 so that the ignition protrusion 31 of the inner ring flame cap 30 can be accurately embedded.

[0027] Of course, this utility model is not limited to the above-described embodiments. Those skilled in the art can make equivalent modifications or substitutions without departing from the spirit of this utility model. All such equivalent modifications and substitutions are included within the scope defined by the claims of this application.

Claims

1. A three-ring burner suitable for aircraft stove heads, characterized in that, include: The lower plate of the Qi distribution (10), the upper plate of the Qi distribution (20), the central fire cover, the inner ring fire cover (30), and the outer ring fire cover (40); The gas distribution plate (10) is provided with an outer ring air inlet cylinder (11) and a central air inlet cylinder (12) arranged coaxially and nested, which are connected to the outer ring air supply cylinder and the central air supply cylinder arranged coaxially and nested in the aircraft stove head; the outer ring air inlet cylinder (11) is provided with an inner air distribution plate (13); the air distribution plate (13) is provided with an inner ring air inlet hole (14) and an outer ring air inlet hole (15); The upper gas distribution plate (20) is covered on the upper side of the lower gas distribution plate (10) and forms an outer ring mixing chamber (50); the outer ring mixing chamber (50) is connected to the outer ring air inlet (15); an outer ring air supply seat (21) and an inner ring air supply seat (22) are provided on the upper side of the upper gas distribution plate (20); the outer ring air supply seat (21) is connected to the outer ring mixing chamber (50); the inner ring air supply seat (22) is connected to the inner ring air inlet (14); the outer ring flame cap (40) and the inner ring flame cap (30) are respectively covered on the outer ring air supply seat (21) and the inner ring air supply seat (22); a central air supply channel (23) is provided in the middle of the inner ring air supply seat (22); the central air supply channel (23) is connected to the top of the central air inlet cylinder (12) and is used to connect the central flame cap.

2. The three-ring burner for aircraft stove heads according to claim 1, characterized in that: The outer periphery of the upper gas distribution plate (20) is provided with a number of outer ring connecting air channels (24) at intervals along the circumference, which are used to connect the outer ring mixing chamber (50) and the outer ring air supply seat (21).

3. The three-ring burner for aircraft stove heads according to claim 2, characterized in that: The gap space between two adjacent outer ring connecting airways (24) forms a secondary air supply channel (25).

4. The three-ring burner for aircraft stove heads according to claim 1, characterized in that: The upper gas distribution plate (20) is provided with an inner ring connecting air passage (26); the upper part of the inner ring connecting air passage (26) is connected to the inner ring air supply seat (22), and the lower part is abutted against the gas distribution plate (13) and connected to the inner ring air inlet (14).

5. The three-ring burner for aircraft stove heads according to claim 1, characterized in that: The base plate of the gas distribution plate (20) has a conical plate structure with a central upward convexity; the outer ring mixing chamber (50) gradually narrows from the middle to the outer edge.

6. The three-ring burner for aircraft stove heads according to claim 1, characterized in that: The upper gas distribution plate (20) and the lower gas distribution plate (10) are provided with ignition mounting holes (60) for installing ignition components; an ignition protrusion (31) is provided on one side of the inner ring flame cap (30), extending from the inner ring flame cap (30) toward the ignition mounting hole (60); the ignition protrusion (31) is provided with an ignition hole or an ignition groove.

7. The three-ring burner for aircraft stove heads according to claim 6, characterized in that: The inner ring gas supply seat (22) has an ignition avoidance groove (221) on one side, and the ignition protrusion (31) is embedded in the ignition avoidance groove (221).

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