A dual fuel combustion nozzle for liquid hydrocarbon fuel and hydrogen fuel

Abstract

The application provides a dual-fuel combustion nozzle, comprising: a nozzle shell connected with a cooling plate; a coaxial hydrogen fuel gas collecting cavity and a liquid hydrocarbon fuel pipe are arranged in the nozzle shell; a first air passage is formed between the inner wall of the hydrogen fuel gas collecting cavity and the liquid hydrocarbon fuel pipe, and a swirler is arranged in the first air passage; a second air passage is formed between the outer wall of the hydrogen fuel gas collecting cavity and the inner shell of the nozzle shell; a liquid hydrocarbon fuel injection hole is arranged at the outlet end of the liquid hydrocarbon fuel pipe, and the liquid hydrocarbon fuel injection hole is located in the space formed by the expansion section of the venturi structure; and a hydrogen gas injection hole is arranged at the side wall of the hydrogen fuel gas collecting cavity close to the top end of the hydrogen fuel gas collecting cavity. The application also provides an engine combustion chamber comprising the above combustion nozzle. According to the application, the hydrogen fuel and the hydrocarbon fuel can be mixed efficiently, the backfire self-ignition phenomenon can be avoided, the flameout boundary can be widened, and the stable switching of multiple working modes can be realized.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aero-engines, and particularly relates to a dual-fuel combustion nozzle of liquid hydrocarbon fuel and hydrogen fuel. BACKGROUND

[0002] The combustion chamber is one of the three major components of the core engine of an aero-engine and is a core component of the aero-engine. Important performance indicators of the combustion chamber mainly include the ignition boundary, the extinction boundary, the outlet temperature distribution, and the total pressure loss. The combustion chamber is of great significance to the overall performance of the engine by converting the chemical energy of the fuel into the total enthalpy of the combustion gas through the rational organization of combustion and flow.

[0003] A spray device composed of a fuel nozzle and a multi-stage swirler is commonly referred to as a swirler cup. The swirler is an essential combustion chamber component for promoting aero-engine gas mixing and stabilizing the flame. In aero-engine design, it is necessary to reduce the smoke of the combustion chamber and increase its stable operating range. The number of swirler stages has developed from single-stage to double-stage and even to triple-stage. The swirler cup is an important component of the aero-engine combustion chamber and has excellent performance, which to some extent determines the combustion performance of the combustion chamber. Currently, the swirler cup structure using liquid hydrocarbon fuel such as aviation kerosene is widely used in the combustion chamber of the aero-engine. The liquid mist combustion of the swirler cup combustion chamber using traditional hydrocarbon fuel limits the high temperature rise and wide flammable boundary required by the current combustion chamber, thereby limiting the combustion performance.

[0004] Hydrogen has attracted attention due to its unique physical and chemical properties compared to traditional hydrocarbon fuels. Compared with natural gas, the lean equivalence ratio limit of hydrogen is 0.1, which is lower than the lean equivalence ratio limit of natural gas 0.4, and wide-range stable combustion can be achieved, thereby widening the operating boundary of lean oil combustion. However, hydrogen premixed combustion is prone to backfire, and the higher laminar flame speed of hydrogen also makes it more prone to backfire. Backfire can cause combustion instability, equipment damage, and even explosion.

[0005] Therefore, there is an urgent need for a new combustion nozzle structure to solve the above-mentioned defects. SUMMARY

[0006] The present application provides a dual-fuel combustion nozzle, in which the air, hydrocarbon fuel, and hydrogen fuel inlets are independent of each other, and the air, hydrocarbon fuel, and hydrogen fuel are mixed in separate zones, thereby solving the defects of the liquid mist combustion of the swirler cup combustion chamber using traditional hydrocarbon fuel, which limits the high temperature rise and wide flammable boundary required by the combustion chamber, and the use of hydrogen fuel, which is prone to backfire.

[0007] The application also provides a combustion chamber comprising the dual-fuel combustion nozzle, wherein air, hydrocarbon fuel and hydrogen fuel inlets are independent of each other, the dual-fuel combustion chamber can improve the combustion performance of the aero-engine, broaden the working boundary and adjustment range under various working environments and working states, and ensure sufficient safety margin through selection of two different combustion characteristic fuels and matching combustion organization modes. The dual-fuel combustion chamber can relieve the deficiency of single fuel in safety boundary and performance limit through switching or joint working of two fuels, and can realize stronger environmental adaptability.

[0008] According to one aspect of the application, a dual-fuel combustion nozzle is provided, comprising:

[0009] A nozzle shell connected with a cooling plate;

[0010] A hydrogen fuel gas collecting cavity and a liquid hydrocarbon fuel pipe coaxial with the nozzle shell are arranged inside the nozzle shell;

[0011] A first air passage is formed between the inner wall of the hydrogen fuel gas collecting cavity and the liquid hydrocarbon fuel pipe, and a swirler is arranged in the first air passage;

[0012] A second air passage is formed between the outer wall of the hydrogen fuel gas collecting cavity and the inner shell of the nozzle shell;

[0013] The side of the first air passage close to the outlet thereof has a venturi structure composed of the inner wall of the hydrogen fuel gas collecting cavity, and the venturi structure comprises an expansion section and a contraction section;

[0014] The outlet end of the liquid hydrocarbon fuel pipe is provided with a liquid hydrocarbon fuel injection hole, and the liquid hydrocarbon fuel injection hole is located in the space formed by the expansion section of the venturi structure;

[0015] The side wall of the hydrogen fuel gas collecting cavity close to the top end thereof is provided with a hydrogen gas injection hole, and the hydrogen gas injection hole is located close to the outlet end face.

[0016] The hydrogen gas injection hole is configured to horizontally straight inject or upwardly obliquely inject hydrogen gas.

[0017] The hydrogen gas injection holes are circumferentially and spacedly distributed on the contraction section.

[0018] The hydrogen gas injection holes are circumferentially and spacedly distributed on the outlet section of the outer wall of the hydrogen fuel gas collecting cavity, and the hydrogen gas injection holes are configured to upwardly obliquely inject hydrogen gas.

[0019] The diameter of the hydrogen gas injection hole is 0.5-1.5 times the diameter of the liquid hydrocarbon fuel injection hole.

[0020] The number of the hydrogen gas injection holes is 10-16.

[0021] The cooling plate is annular, and a plate surface of the cooling plate is flush with a top end of the hydrogen fuel gas collecting cavity.

[0022] The cooling through holes are inclined holes arranged in a circumferential direction.

[0023] The cooling through holes extend along a circumferential direction of the cooling plate, and a center line of the cooling through holes is at an angle of 30-60° with respect to a central axis of the cooling plate.

[0024] The diameter of the cooling through holes is 0.2-1.0 times the diameter of the liquid hydrocarbon fuel injection hole.

[0025] A cyclone is arranged in the second air passage, for example, at an air inlet end of the second air passage.

[0026] When the flow number is 0.3-0.5, the diameter of the liquid hydrocarbon fuel injection hole is 2-4 mm.

[0027] According to one aspect of the present application, an engine combustion chamber is provided, which comprises the aforementioned dual-fuel combustion nozzle.

[0028] According to the present application, air, liquid hydrocarbon fuel, and hydrogen fuel are mixed in a partitioned manner, and the traditional kerosene cyclone cup structure and the hydrogen micro-pipe structure are efficiently matched, so that efficient mixing of oil and gas can be achieved in multiple modes of independent work and common work of the two fuels, and the flameout boundary is widened, thereby creating favorable conditions for combustion in the flame tube.

[0029] According to the present application, by reasonably organizing micro-mixed combustion, the backfire self-ignition phenomenon of hydrogen combustion is avoided, and stable switching of multiple working modes is achieved.

[0030] According to the present application, a liquid hydrocarbon fuel and hydrogen fuel dual-fuel combustion form is adopted, and the advantages of wide-range stable dual-fuel combustion are used, so that the combustion chamber can stably combust under wide working conditions and complex air intake conditions.

[0031] According to the present application, by coupling the multi-inclined-hole cooling plate and the cyclone, high combustion efficiency is achieved in a wide range, and nitrogen oxide (NOx) emissions of the combustion chamber are reduced, and the flammable boundary of the combustion chamber is widened. BRIEF DESCRIPTION OF DRAWINGS

[0032] In order to more clearly illustrate the technical solutions in the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without any creative effort based on these drawings.

[0033] Figure 1 is a sectional view of one embodiment of the combustion nozzle provided by the present application.

[0034] Figure 2 is a schematic diagram of the injection of dual fuel in the combustion nozzle provided by the present application.

[0035] Figure 3 is a schematic diagram of one injection mode of hydrogen fuel in the combustion nozzle provided by the present application.

[0036] Figure 4 is a schematic diagram of another injection mode of hydrogen fuel in the combustion nozzle provided by the present application.

[0037] Figure 5 is Figure 4 is a diagram of the arrangement of hydrogen injection holes corresponding to the injection mode in

[0038] Figure 6 is a top view of one embodiment of the combustion nozzle provided by the present application.

[0039] Figure 7 is an oblique view of one embodiment of the combustion nozzle provided by the present application.

[0040] Figure 8 is a front view of one embodiment of the combustion chamber provided by the present application.

[0041] Figure 9 is Figure 8 is a sectional view at AA of

[0042] Reference Signs:

[0043] 100: air inlet pipe; 200: air cavity; 300: combustion area; 400: dual fuel nozzle;

[0044] 1: nozzle shell; 111: inner shell; 112: outer shell; 2: first air passage; 3: second air passage; 4: hydrogen inlet pipe; 5: liquid hydrocarbon inlet pipe; 6: cooling plate; 7: hydrogen fuel collection cavity; 711: outlet section; 712: tapered section; 713: top end; 8: venturi structure; 811: expansion section; 812: contraction section; 9: swirler; 10: liquid hydrocarbon injection hole; 11: hydrogen injection hole; 12: cooling through hole. DETAILED DESCRIPTION

[0045] In order to make the objectives, technical solutions and advantages of the present application clearer, the technical solutions in the present application will be described clearly and completely below in conjunction with the drawings in the present application. Obviously, the described embodiments are some, but not all, of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the scope of protection of the present application.

[0046] The application will be described below Figures 1-9 with reference to the drawings.

[0047] As Figure 1 shown in the drawings, a dual-fuel combustion nozzle 400 comprises a nozzle shell 1, the nozzle shell 1 is connected with a cooling plate 6; the nozzle shell 1 is internally provided with a hydrogen fuel gas collecting cavity 7 and a liquid hydrocarbon fuel pipe 5 coaxially with the nozzle shell 1; a first air passage 2 is formed between the inner wall of the hydrogen fuel gas collecting cavity 7 and the liquid hydrocarbon fuel pipe 5, and a swirler 9 is arranged in the first air passage 2; a second air passage 3 is formed between the outer wall of the hydrogen fuel gas collecting cavity 7 and the inner shell 111 of the nozzle shell 1; the side of the first air passage 2 close to the outlet thereof has a Venturi structure 8 formed by the inner wall of the hydrogen fuel gas collecting cavity 7, the Venturi structure 8 comprises an expansion section 811 and a contraction section 812; the outlet end of the liquid hydrocarbon fuel pipe 5 is provided with a liquid hydrocarbon fuel injection hole 10, and the liquid hydrocarbon fuel injection hole 10 is located in the expansion section 811 of the Venturi structure 8; the hydrogen fuel gas collecting cavity 7 is provided with a hydrogen fuel gas injection hole 11 on the side wall close to the top end 713 thereof.

[0048] According to the application, the nozzle shell 1 is coaxially arranged with the hydrogen fuel gas collecting cavity 7 and the liquid hydrocarbon fuel pipe 5; the air entering the first air passage 2 is sprayed out after passing through the swirler 9; the liquid hydrocarbon fuel is sprayed through the liquid hydrocarbon fuel injection hole 10 of the liquid hydrocarbon fuel pipe 5 and broken into small droplets; the liquid hydrocarbon fuel is mixed with the air sprayed out through the swirler 9 to form a hydrocarbon fuel mixture; the hydrocarbon fuel mixture passes through the Venturi structure 8 to improve the mixing effect. The position of the hydrogen fuel gas injection hole 11 is much higher than that of the liquid hydrocarbon fuel injection hole 10; the hydrocarbon fuel mixture is mixed with the hydrogen fuel sprayed out from the hydrogen fuel gas injection hole 11. In this way, the fuel can be mixed in different zones. The cooling plate helps to reduce the temperature of the combustion nozzle, prevent overheating, and ensure the combustion efficiency and service life.

[0049] The combustion nozzle according to the application adopts a dual-fuel combustion mode of liquid hydrocarbon fuel and hydrogen fuel, can work in two working combustion modes of independent work and common work of the two fuels, and the dual fuel and air are independently divided in different zones, so that the fuel can be fully combusted and backfire can be avoided in a wide working condition range.

[0050] The hydrogen fuel gas collecting cavity 7 is supplied with hydrogen fuel through a hydrogen fuel inlet pipe 4. The swirler 9 in the first air passage 2 is connected with the liquid hydrocarbon fuel inlet pipe 5 and the inner wall of the hydrogen fuel gas collecting cavity 7, respectively, and the position of the outlet port of the swirler 9 on the inner wall of the hydrogen fuel gas collecting cavity 7 is the starting point of the expansion section 811, the inner diameter is 11-13 mm, the outer diameter is 18-22 mm, and the length and the number of revolutions can be selected by those skilled in the art according to the needs.

[0051] The Venturi structure 8 includes a throat with a diameter of 3.5-4.5 mm, the ratio of the length of the expansion section 811 to the diameter of the throat is 0.7-1.1, such as 0.8-0.9, the ratio of the length of the contraction section 812 to the diameter of the throat is 0.5-0.9, such as 0.65-0.75, and the diameter of the end of the inner wall of the contraction section 812, i.e. the hydrogen fuel gas collection cavity 7, is 10-15 mm, such as 11-13 mm or 12.5-13.5 mm. The Venturi structure 8 is conducive to the sufficient mixing of fuel and air, the increase of gas pressure, the improvement of combustion efficiency, etc.

[0052] The hydrogen injection hole 11 is configured to inject hydrogen horizontally or upwardly. Those skilled in the art can understand that "up" or "top" in this context refers to the discharge end of the combustion nozzle, not the feed end. By further adjusting the opening direction of the hydrogen injection hole 11, the injection direction of the hydrogen fuel can be adjusted, the mixing form of the hydrogen fuel with air or with the hydrocarbon fuel mixture can be adjusted, and the combustion effect of the combustion area can be improved.

[0053] The flow number (FN) is used to represent the effective flow area of the liquid hydrocarbon injection hole, which is the ratio of the flow rate of the liquid hydrocarbon fuel to the square root of the pressure difference. When the flow number is 0.3-0.5, the diameter of the liquid hydrocarbon injection hole is 2-4 mm.

[0054] The number and diameter of the hydrogen injection hole 11 are determined according to the flow rate and pressure drop of hydrogen. According to the velocity obtained from the pressure drop, the total area of the hole can be obtained according to the required flow rate, and under the condition that the diameter of the hole is limited, the number of hydrogen injection holes 11 can be obtained. The calculation method is known to those skilled in the art, and will not be described here. In a specific embodiment, the diameter of the hydrogen injection hole 11 is 0.5-1.5 times the diameter of the liquid hydrocarbon injection hole 10. In a specific embodiment, the number of hydrogen injection holes 11 is 10-16.

[0055] The setting of the hydrogen injection hole allows hydrogen to be injected through a large number of small-diameter injection holes, realizing subsequent micro-mixed combustion of hydrogen. Hydrogen has a small quenching distance, and the smaller spatial scale of the hydrogen injection hole and the larger mass diffusion coefficient of hydrogen make the premixing effect better. Furthermore, by reducing the hydrogen outlet area and increasing the jet velocity, the backfire problem can be alleviated.

[0056] The second air passage 3 is also provided with a swirler 9, which is connected with the inner wall 111 of the nozzle shell 1 and the outer wall of the hydrogen fuel collecting cavity 7 and located at the air inlet end of the second air passage 3, so that the combustion nozzle is designed as a double-swirl cup, and the gas flowing out of the second air passage 3 is outer swirl air. The outer diameter of the swirler 9 in the second air passage 3 is 34-38 mm, and the inner diameter is 30-35 mm. The length and swirl number of the swirler 9 can be selected by those skilled in the art according to the needs. The gas outlet port of the swirler 9 in the second air passage 3 is flush with the gas outlet port of the first air passage 2.

[0057] The second air passage 3 is an annular chamber, the inner ring is the outer wall of the hydrogen fuel collecting cavity 7, and the outer ring is the inner shell of the nozzle shell 1. Near the discharge end of the dual-fuel combustion nozzle, the outer wall of the hydrogen fuel collecting cavity 7 first gradually shrinks in diameter to form a tapered section 712, then remains unchanged to form an outlet section 711, and the end of the outer wall is fused with the end of the inner wall to form an annular top end 713. The width of the top end 713 of the hydrogen fuel collecting cavity 7 in the radial direction of the combustion nozzle is 1.5-3 mm, such as 2-2.5 mm.

[0058] The starting point of the tapered section 712 is flush with the starting point of the expanding section 811 of the inner wall. Near the discharge end of the dual-fuel combustion nozzle, the diameter of the inner shell 111 of the nozzle shell 1 also gradually decreases. The distance between the inner ring and the outer ring at the outlet of the second air passage 3 is 1-2 mm, such as 1.5-2 mm or 1.3-1.8 mm.

[0059] As shown in Figure 2 and 3 , the hydrogen gas injection hole 11 is located on the converging section 812 of the venturi structure 8, i.e., on the upper part of the inner wall of the hydrogen fuel collecting cavity 7, and is distributed in a circumferential interval, so that the hydrogen fuel is injected inward. Figure 2 In the hydrogen gas injection hole 11, the opening of the hydrogen gas injection hole 11 is inclined upward, and the hydrogen fuel is inclined upward. Figure 3 In the hydrogen gas injection hole 11, the opening of the hydrogen gas injection hole 11 is horizontal, and the axis is in the radial direction of the combustion nozzle 400, and the hydrogen fuel is straightly injected horizontally. The inwardly injected hydrogen fuel is first mixed with the carbon-hydrogen fuel mixture for preliminary premixing, and then mixed with the outer swirl air, so as to further ensure uniform mixing, thereby optimizing the combustion performance and improving the combustion stability.

[0060] The opening position of the hydrogen gas injection hole 11 on the converging section 812 is not specifically limited, such as Figure 2 In the hydrogen gas injection hole 11, the hole edge distance from the hydrogen gas injection hole 11 to the top end 713 of the hydrogen fuel collecting cavity 7 is 0.25-0.35 mm, such as 0.3-0.35 mm. In the hydrogen gas injection hole 11, Figure 3As shown in FIG. 1, the hydrogen injection hole 11 is 1-2 mm, such as 1.5-2 mm, from the edge of the top end 713 of the hydrogen fuel collecting cavity 7.

[0061] As shown in FIG. 1, the hydrogen injection hole 11 is 1-2 mm, such as 1.5-2 mm, from the edge of the top end 713 of the hydrogen fuel collecting cavity 7. Figure 5 As shown in FIG. 1, the hydrogen injection hole 11 is 1-2 mm, such as 1.5-2 mm, from the edge of the top end 713 of the hydrogen fuel collecting cavity 7. Figure 4 5 As shown in FIG. 1, the hydrogen injection hole 11 is 1-2 mm, such as 1.5-2 mm, from the edge of the top end 713 of the hydrogen fuel collecting cavity 7.

[0062] In a specific embodiment, the hydrogen injection hole (11) is configured to inject hydrogen upwardly obliquely; the hydrogen fuel is injected obliquely outwardly from the top of the outer wall of the hydrogen fuel collecting cavity 7. At this time, the injected hydrogen fuel is mixed with the outer air first, and then mixed with the outflowing hydrocarbon fuel mixture; the partitioned mixing of the dual fuels is achieved, and the mixing is uniform. When the swirler 9 is arranged in the second air passage 3, the outer layer of swirling air is formed, and at this time, the injected hydrogen fuel is mixed with the outer layer of swirling air first, and then mixed with the outflowing hydrocarbon fuel mixture, so that a better mixing effect is achieved, the combustion performance is optimized, and the combustion stability is improved.

[0063] As shown in FIG. 1, the hydrogen injection hole 11 is 1-2 mm, such as 1.5-2 mm, from the edge of the top end 713 of the hydrogen fuel collecting cavity 7. Figure 6 Figure 7 As shown in FIG. 1, the hydrogen injection hole 11 is 1-2 mm, such as 1.5-2 mm, from the edge of the top end 713 of the hydrogen fuel collecting cavity 7.

[0064] As shown in FIG. 1, the hydrogen injection hole 11 is 1-2 mm, such as 1.5-2 mm, from the edge of the top end 713 of the hydrogen fuel collecting cavity 7. Figure 6 As shown in FIG. 1, the hydrogen injection hole 11 is 1-2 mm, such as 1.5-2 mm, from the edge of the top end 713 of the hydrogen fuel collecting cavity 7. Figure 7 ​​As shown, the cooling through hole 12 is an inclined hole, and the cooling through hole 12 is a plurality of circumferentially arranged inclined holes. The number of turns can be 1-5 turns. Among them, the cooling through hole 12 extends along the circumference of the cooling plate 6 and penetrates the cooling plate 6; the center line of the cooling through hole 12 and the center axis of the cooling plate 6, that is, the center axis of the dual-fuel combustion nozzle, form an angle of 30-60°. Such design can also generate corresponding swirling air, which can be further coupled and mixed with mixed dual-fuel and swirling air, thereby further improving the subsequent combustion efficiency, further reducing the NOx emission of the combustion chamber, and further widening the flammable boundary.

[0065] According to another aspect of the present application, an engine combustion chamber is also provided, comprising the aforementioned dual-fuel combustion nozzle. As Figure 8 and 9 As shown, the combustion chamber comprises an air inlet pipe 100; an air cavity 200; a combustion area 300, and a dual-fuel nozzle 400 installed on the bottom plate of the combustion area 300.

[0066] The air cavity 200 communicates with the first air passage 2 and the second air passage 3 of the dual-fuel combustion nozzle and the through hole of the cooling plate 6, and provides air for the first air passage 2 and the second air passage 3 and the cooling plate 6. The dual-fuel nozzle discharges mixed hydrocarbon fuel, hydrogen fuel and air into the combustion area (300) for combustion.

[0067] Hydrogen fuel is fed through the hydrogen inlet pipe 4, liquid hydrocarbon fuel is fed through the liquid hydrocarbon inlet pipe 5, and air is fed through the air inlet pipe 100, so that the air, hydrocarbon fuel and hydrogen fuel are independently fed; facilitating the switching or co-working of the two fuels.

[0068] The device embodiments described above are only schematic. Part or all of the components can be selected according to actual needs to achieve the purpose of the embodiment scheme. Those skilled in the art can understand and implement without creative labor.

[0069] Finally, it should be noted that: the above examples are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A dual fuel combustion nozzle characterized by, The dual-fuel combustion nozzle comprises: a nozzle shell (1) connected with a cooling plate (6); a hydrogen fuel gas collecting cavity (7) and a liquid hydrocarbon fuel pipe (5) coaxially arranged inside the nozzle shell (1); a first air passage (2) formed between the inner wall of the hydrogen fuel gas collecting cavity (7) and the liquid hydrocarbon fuel pipe (5), wherein a swirler is arranged in the first air passage (2); a second air passage (3) formed between the outer wall of the hydrogen fuel gas collecting cavity (7) and the inner shell (111) of the nozzle shell (1); a Venturi structure (8) formed by the inner wall of the hydrogen fuel gas collecting cavity (7) on the side close to the outlet of the first air passage (2), wherein the Venturi structure (8) comprises an expansion section (811) and a contraction section (812); a liquid hydrocarbon fuel injection hole (10) arranged at the outlet end of the liquid hydrocarbon fuel pipe (5), wherein the liquid hydrocarbon fuel injection hole (10) is located in the space formed by the expansion section (811) of the Venturi structure (8); a hydrogen gas injection hole (11) arranged on the side wall close to the top end (713) of the hydrogen fuel gas collecting cavity (7); the top end (713) of the hydrogen fuel gas collecting cavity (7) is flush with the plate surface of the cooling plate (6), wherein a cooling through hole (12) is arranged on the cooling plate (6), the cooling through hole (12) is an inclined hole arranged in multiple circles on the cooling plate (6), the number of circles is 1-5, the center line of the cooling through hole (12) extends along the circumference of the cooling plate (6) and forms an angle of 30-60° with the central axis of the cooling plate (6).

2. The dual fuel combustion nozzle of claim 1, wherein, The hydrogen gas injection hole (11) is configured to horizontally straightly inject or upwardly obliquely inject hydrogen gas.

3. The dual fuel combustion nozzle of claim 2, wherein, The hydrogen gas injection hole (11) is arranged in a circumferential interval on the contraction section (812).

4. The dual fuel combustion nozzle of claim 2, wherein, The hydrogen gas injection hole (11) is arranged in a circumferential interval on the outlet section (711) of the outer wall of the hydrogen fuel gas collecting cavity (7), and the hydrogen gas injection hole (11) is configured to upwardly obliquely inject hydrogen gas.

5. The dual fuel combustion nozzle of claim 2, wherein, The diameter of the hydrogen gas injection hole (11) is 0.5-1.5 times the diameter of the liquid hydrocarbon fuel injection hole (10); and / or, the number of the hydrogen gas injection holes is 10-16.

6. The dual fuel combustion nozzle of claim 1, wherein, The cooling plate (6) is in the shape of a ring.

7. The dual fuel combustion nozzle of claim 6, wherein, The diameter of the cooling through hole (12) is 0.2-1.0 times the diameter of the liquid hydrocarbon fuel injection hole.

8. The dual fuel combustion nozzle of claim 1, wherein, A swirler is arranged in the second air passage (3).

9. The dual fuel combustion nozzle of any of claims 1-8, wherein, When the flow number is 0.3-0.5, the diameter of the liquid hydrocarbon fuel injection hole is 2-4 mm.

10. An engine combustion chamber comprising the dual-fuel combustion nozzle according to claims 1-9.

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