Swirl burner

Abstract

The present application relates to the field of fuel injection, and provides a swirl burner, which comprises an outer wall ring, a central bluff body and a plurality of hollow swirl vanes, a central passage is formed in the middle of the outer wall ring, the outer wall ring is provided with a fuel supply ring cavity and a fuel connecting passage, the fuel connecting passage is communicated with the fuel supply ring cavity; the central bluff body is located in the central passage, the central bluff body is internally provided with a central bluff body fuel cavity, and a plurality of fuel injection holes are formed in the central bluff body; the hollow swirl vane is connected with the central bluff body and the outer wall ring, the hollow swirl vane is internally provided with a vane fuel passage, the vane fuel passage is communicated with the central bluff body fuel cavity and the fuel supply ring cavity; a swirl passage is formed between the outer wall ring, the central bluff body and the hollow swirl vane, air flows through the swirl passage to form an air swirl, and the fuel injection holes are used for injecting fuel to be mixed and combusted with the air swirl in the form of a transverse jet.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of fuel injection technology, in particular to a swirl burner. BACKGROUND

[0002] With the increasing awareness of environmental protection around the world, the use of hydrogen instead of traditional carbon-hydrogen fuel has become one of the important development directions and technical approaches for future zero-carbon aviation power. As a clean energy, hydrogen has only water as its combustion product, which is pollution-free to the environment, and is a key to achieving the carbon neutralization goal of the aviation industry. However, due to the low volumetric energy density of hydrogen, future hydrogen aviation power systems need to continuously pursue higher overall thermal efficiency to ensure sufficient endurance.

[0003] In order to improve the overall thermal efficiency of the hydrogen aviation power system, the solid oxide fuel cell (SOFC) and aviation gas turbine (GT) combined cycle technology has emerged. This technology couples electrochemical reactions and combustion chemical reactions to achieve energy cascade utilization. SOFCs fueled by green hydrogen can efficiently convert hydrogen energy into electricity, while unreacted hydrogen is continuously burned with air in the combustion chamber to further drive the turbine. This combined cycle process is expected to increase the overall thermal efficiency of the corresponding power plant to 60-70%, which is a highly potential future zero-carbon aviation power technology.

[0004] However, in the traditional swirl burner scheme suitable for pure hydrogen and other gaseous fuels, the maximum supply pressure of the fuel gas is often significantly higher than the inlet air pressure of the combustion chamber. The fuel flow path can use a high enough pressure difference to give the gas jet the required momentum, which in turn helps its rapid mixing with air and uniform combustion. However, in the scenario of using SOFC tail gas as the combustion working medium, the supply pressure of the fuel (anode tail gas) and the oxidant side (cathode tail gas) need to be almost the same, otherwise there is a risk of damaging the internal structure of the SOFC. This greatly limits the pressure difference that can be used for fuel injection, resulting in low injection velocity and low penetration depth of the transverse fuel jet, which in turn affects the mixing effect of the fuel jet and the oxidant. This can cause local high equivalence ratio in the flame, which in turn causes local hot spots and increases nitrogen oxide emissions. In addition, the combustion organization scheme in the premixed mode is not suitable for the combustion of SOFC tail gas, because the electrochemical reaction gives the SOFC tail gas a higher temperature, greatly shortening the ignition delay time and easily causing hydrogen to self-ignite in the premixed section, causing backfire risk. SUMMARY

[0005] The present application aims to solve one of the technical problems in the related art. In this regard, the present application proposes a swirl burner.

[0006] According to the swirl burner provided by the first aspect of the present application, the swirl burner comprises:

[0007] an outer wall ring, a central passage being formed in a middle portion of the outer wall ring, a fuel supply ring cavity being provided inside the outer wall ring, a fuel connection passage being formed in the outer wall ring, the fuel connection passage being in communication with the fuel supply ring cavity;

[0008] a central bluff body, located in the central passage, a central bluff body fuel cavity being provided inside the central bluff body, a plurality of fuel injection holes being formed in the central bluff body, the fuel injection holes being distributed along a circumferential direction of a top portion of the central bluff body, the fuel injection holes being in communication with the central bluff body fuel cavity;

[0009] a plurality of hollow swirl vanes, the hollow swirl vanes being connected to the central bluff body and the outer wall ring, a vane fuel passage being provided inside the hollow swirl vanes, the vane fuel passage being in communication with the central bluff body fuel cavity and the fuel supply ring cavity;

[0010] a swirl passage being formed between the outer wall ring, the central bluff body and the hollow swirl vanes, air flowing through the swirl passage to form an air swirl, the fuel injection holes being used for injecting fuel to mix with the air swirl in a lateral jet manner to combust.

[0011] According to the swirl burner provided by the embodiment of the present application, the air swirl is generated by the central bluff body and the hollow swirl vanes, and the multi-point injection diffusion flame layout is adopted, the gaseous fuel jet is injected by the fuel injection hole array located at the top portion of the central bluff body, and the gaseous fuel jet enters the air swirl in a lateral manner. The mixing is strengthened by the combination of the swirl stirring and the multi-point fuel injection, so that the fuel is rapidly and uniformly mixed with the air in the whole cross section. The swirl burner can reduce the dependence on the fuel lateral jet injection speed, and in turn reduce the demand for the fuel supply pressure. Meanwhile, the flame can be controlled in the shear layer in the air swirl, and the combustion oscillation and the high nitrogen oxide emission caused by the corner vortex area combustion can be prevented. In addition, the risk of the fuel spontaneous ignition backfire is avoided by adopting the diffusion combustion layout. The swirl burner can be arranged in an array form to form a combustion chamber head, and is used for organizing the efficient, stable and low emission combustion of the low calorific value anode tail gas.

[0012] According to one embodiment of the present application, the swirl passage includes an air inlet annular passage and an air outlet annular passage, the air inlet annular passage being in communication with the air outlet annular passage, the air inlet annular passage being located at a first side of the hollow swirl vane, the air outlet annular passage being located at a second side of the hollow swirl vane, and the opening of the air outlet annular passage gradually decreases to form a tapered passage along the flow direction of the air.

[0013] According to one embodiment of the present application, the outer wall ring and the central bluff body are provided with chamfers at the inlet of the air inlet annular passage.

[0014] According to one embodiment of the present application, the fuel injection holes are evenly distributed along the circumference of the top of the central bluff body.

[0015] According to one embodiment of the present application, the top of the central bluff body protrudes from the central passage, and the plane of the fuel injection holes is spaced apart from the end face of the outer wall ring.

[0016] According to one embodiment of the present application, the outer contour of the outer wall ring is one of a hexagon, a pentagon, a rectangle, a square, a triangle, and a circle. In the case where the outer contour of the outer wall ring is a square, the height H of the outer wall ring ranges from 15 mm to 60 mm, the thickness T of the outer wall ring ranges from 10 mm to 60 mm, the inner diameter D ii of the inlet of the outer wall ring ranges from 10 mm to 55 mm, and the inner diameter D eo of the outlet of the outer wall ring ranges from 8 mm to 53 mm.

[0017] According to one embodiment of the present application, the hollow swirl vane is one of a twisted vane, a non-twisted vane, a curved vane, and a straight vane. In the case where the hollow swirl vane is a non-twisted vane, the vane inclination angle a of the hollow swirl vane ranges from 20° to 70°, the vane length L of the hollow swirl vane ranges from 5 mm to 25 mm, and the number n A of vanes of the hollow swirl vane ranges from 4 to 16.

[0018] According to one embodiment of the present application, the outer diameter D io of the inlet of the central bluff body ranges from 5 mm to 55 mm, the outer diameter D ei of the outlet of the central bluff body ranges from 6 mm to 58 mm, and the diameter D oi of the bluff body trailing edge of the central bluff body ranges from 4 mm to 60 mm.

[0019] According to one embodiment of the present application, the fuel injection hole is one of a circular hole, an elliptical hole, an arcuate hole, a rounded rectangular hole, and a triangular hole. The number n B of fuel injection holes ranges from 2 to 30, the hole diameter d j ranges from 0.1 mm to 2.5 mm, and the distance h between the plane of the fuel injection holes and the end face of the outer wall ring ranges from 0 mm to 6 mm.

[0020] According to one embodiment of the present application, the number n C of fuel connection passages ranges from 2 to 8, and the cross-sectional area of a single fuel connection passage ranges from 1 mm 2 to 100 mm 2 .

[0021] Additional aspects and advantages of the application will be set forth in part in the description which follows, and in part will become apparent to those having ordinary skill in the art upon examination of the following or can be learned from practice of the application. BRIEF DESCRIPTION OF DRAWINGS

[0022] The accompanying drawings, which are incorporated herein and form a part of the specification, illustrate the present application and, together with the description, further serve to explain the principles of the application and to enable a person skilled in the relevant art(s) to make and use the application.

[0023] Figure 1 is a sectional axial structure schematic view of a cyclone burner provided by the embodiment of the present application.

[0024] Figure 2 is a structure schematic view of a cyclone burner provided by the embodiment of the present application.

[0025] Figure 3 is an A-direction sectional structure schematic view of a cyclone burner provided by the embodiment of the present application.

[0026] Figure 4 is a structure schematic view of a hollow cyclone blade provided by the embodiment of the present application. Figure 3 is a local enlarged structure schematic view of a cyclone burner provided by the embodiment.

[0027] Figure 5 is a structure schematic view of a hollow cyclone blade provided by the embodiment of the present application.

[0028] Figure 6 is a structure schematic view of an outer wall ring with a hexagonal outer contour shape provided by the embodiment of the present application.

[0029] Figure 7 is a structure schematic view of an outer wall ring with a pentagonal outer contour shape provided by the embodiment of the present application.

[0030] Figure 8 is a structure schematic view of an outer wall ring with a square outer contour shape provided by the embodiment of the present application.

[0031] Figure 9 is a structure schematic view of an outer wall ring with a rectangular outer contour shape provided by the embodiment of the present application.

[0032] Figure 10 is a structure schematic view of an outer wall ring with a triangular outer contour shape provided by the embodiment of the present application.

[0033] Figure 11 is a structure schematic view of an outer wall ring with a circular outer contour shape provided by the embodiment of the present application.

[0034] Figure 12is one of structural schematic diagrams of a structure of a fuel injection hole in a round rectangle shape provided by an embodiment of the present application.

[0035] Figure 13 is one of structural schematic diagrams of a structure of a fuel injection hole in an ellipse shape provided by an embodiment of the present application.

[0036] Figure 14 is one of structural schematic diagrams of a structure of a fuel injection hole in a round shape provided by an embodiment of the present application.

[0037] Figure 15 is one of structural schematic diagrams of a structure of a fuel injection hole in a triangle shape provided by an embodiment of the present application.

[0038] Figure 16 is one of structural schematic diagrams of a structure of a fuel injection hole in a quadrilateral shape provided by an embodiment of the present application.

[0039] Figure 17 is one of structural schematic diagrams of a structure of a fuel injection hole in a round rectangle shape provided by an embodiment of the present application.

[0040] Reference signs:

[0041] 1, fuel supply ring cavity; 2, air inlet annular channel; 3, hollow swirler blade; 4, fuel connecting channel; 5, blade fuel channel; 6, fuel injection hole; 7, air outlet annular channel; 8, central bluff body fuel cavity; 9, central bluff body; 10, outer wall ring. DETAILED DESCRIPTION

[0042] The embodiments of the present application will be further described below in conjunction with the drawings and examples. The following examples are used to illustrate the present application, but cannot be used to limit the scope of the present application.

[0043] In the description of the embodiments of the present application, it should be noted that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship range based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the embodiments of the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the scope of the embodiments of the present application. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0044] In the description of the embodiments of the present application, it should be noted that unless specifically defined and limited otherwise, the terms "connected", "connection" should be interpreted broadly, for example, can be fixedly connected, can also be detachably connected, wherein the fixedly connected can include the manner of integrally connected; can be mechanically connected, can also be electrically connected; can be directly connected, can also be indirectly connected through an intermediate medium. For those skilled in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0045] In the embodiments of the present application, unless specifically defined and limited otherwise, the first feature is "on" or "under" the second feature can be that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature can be "above", "over" and "on" the second feature, which can be that the first feature is directly above or obliquely above the second feature, or only means that the horizontal height of the first feature is higher than that of the second feature. The first feature can be "below", "under" and "under" the second feature, which can be that the first feature is directly below or obliquely below the second feature, or only means that the horizontal height of the first feature is less than that of the second feature.

[0046] In the description of the present application, the description of the terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, those skilled in the art can combine and combine the different embodiments or examples described in the present application and the features of the different embodiments or examples without contradiction.

[0047] The following will be described in combination with Figures 1-17 The present application describes a cyclone burner.

[0048] According to the cyclone burner provided by the embodiments of the present application, please refer to Figures 1 to 5, the cyclone burner comprises an outer wall ring 10, a central bluff body 9 and a plurality of hollow cyclone vanes 3, the central passage is formed in the middle of the outer wall ring 10, the fuel supply ring cavity 1 is arranged inside the outer wall ring 10, the fuel connecting channels 4 are formed in the outer wall ring 10, and the fuel connecting channels 4 are communicated with the fuel supply ring cavity 1; the central bluff body 9 is located in the central passage, the central bluff body fuel cavity 8 is arranged inside the central bluff body 9, a plurality of fuel injection holes 6 are formed in the central bluff body 9, the fuel injection holes 6 are distributed along the circumference of the top of the central bluff body 9, and the fuel injection holes 6 are communicated with the central bluff body fuel cavity 8; the hollow cyclone vane 3 is connected with the central bluff body 9 and the outer wall ring 10, the vane fuel channel 5 is arranged inside the hollow cyclone vane 3, and the vane fuel channel 5 is communicated with the central bluff body fuel cavity 8 and the fuel supply ring cavity 1; the cyclone passage is formed between the outer wall ring 10, the central bluff body 9 and the hollow cyclone vane 3, air flows through the cyclone passage to form an air cyclone, and the fuel injection holes 6 are used for injecting fuel to be mixed and combusted with the air cyclone in the form of a transverse jet.

[0049] According to the cyclone burner provided in the embodiment of the application, the air cyclone is generated through the central bluff body 9 and the hollow cyclone vane 3, and a multi-point injection diffusion flame layout is adopted, the gaseous fuel jet is injected out of the fuel injection hole 6 array located at the top of the central bluff body 9 and enters the air cyclone in the form of a transverse jet. The mixing is strengthened in the form of the combination of the cyclone stirring and the multi-point fuel injection, so that the fuel is rapidly and uniformly mixed with the air in the whole cross section. The cyclone burner can reduce the dependence on the transverse jet injection speed of the fuel, and in turn reduce the demand for the fuel supply pressure. Meanwhile, the flame can be controlled in the shear layer in the air cyclone, and the combustion oscillation and the excessively high nitrogen oxide emission that may be caused by the corner vortex zone combustion can be prevented. In addition, the risk of the self-ignition backfire of the fuel is avoided by adopting the diffusion combustion layout. The cyclone burner can be used to form a combustion chamber head in the form of an array, and is used to organize the efficient, stable and low-emission combustion of the low-calorific-value anode tail gas.

[0050] The outer wall ring 10 is the peripheral structure of the cyclone, is used for fixing the vanes, restraining the air flow and being connected with other head units. The central passage is formed in the middle of the outer wall ring 10, the central passage provides the installation space of the central bluff body 9 and the hollow cyclone vane 3, and also provides the flow space of the gas. The fuel supply ring cavity 1 is arranged inside the outer wall ring 10, is used for storing and distributing the fuel, and can ensure that the fuel uniformly enters each vane fuel channel 5. The fuel connecting channels 4 are formed in the outer wall ring 10, the channels are communicated with the fuel supply ring cavity 1, and ensure that the fuel can smoothly enter the inside of the cyclone. The fuel connecting channels 4 are used for connecting the fuel supply ring cavity 1 with other head micro-cyclone units and / or fuel pipelines, and in turn form a complete head array.

[0051] The central bluff body 9 is located in the central passage and serves to stabilize the airflow and enhance the effect of the rotational flow. The central bluff body 9 is provided with a central bluff body fuel cavity 8 inside, which is used to collect fuel from the vane fuel passage 5 and ensure that the fuel can be uniformly injected from the fuel injection hole 6. The central bluff body 9 is provided with a plurality of fuel injection holes 6 on the top in the circumferential direction, which injects fuel into the air rotational flow in a multi-point injection manner to form a diffusion flame layout.

[0052] The hollow rotational vane 3 connects the central bluff body 9 and the outer wall ring 10, and forms a rotational flow passage with the central bluff body 9 and the outer wall ring 10. The hollow rotational vane 3 is used to generate rotational flow, which serves to strengthen the mixing and form a backflow area to stabilize the flame. The vane is provided with a vane fuel passage 5 inside, which is connected to the central bluff body fuel cavity 8 and the fuel supply ring cavity 1, and is used to connect the fuel supply ring cavity 1 and the central bluff body fuel cavity 8.

[0053] The rotational flow combustor provided in the present application aims to realize rapid and uniform mixing of fuel and air by optimizing the air flow organization and fuel injection mode, thereby improving the combustion efficiency, reducing the emission, and ensuring the stability and controllability of the combustion.

[0054] When the air flows through the rotational flow passage between the outer wall ring 10 and the central bluff body 9 and the hollow rotational vane 3, the air is guided to form a rotational flow due to the shape and arrangement of the vane. The fuel enters the air rotational flow in a multi-point injection manner through the fuel injection hole 6 on the top of the central bluff body 9. Since the injection holes are distributed in the circumferential direction, the fuel can be uniformly distributed in the rotational flow and fully mixed with the air to form a diffusion flame layout. By combining rotational flow stirring and multi-point fuel injection, the rotational flow device of the present application can significantly strengthen the mixing effect of fuel and air. At the same time, the design of the central bluff body 9 and the hollow rotational vane 3 helps to form a stable backflow area, further stabilizing the flame and preventing the occurrence of combustion oscillation and backfire. Since multi-point injection and rotational flow stirring are used, the rotational flow device of the present application reduces the dependence on the transverse jet injection speed of the fuel, thereby reducing the demand for gas supply pressure.

[0055] It should be noted that the rotational flow device of the present application can be arranged in an array form to form the head of the combustion chamber, and through the synergistic effect of multiple rotational flow devices, the low-calorific-value anode tail gas can be burned efficiently, stably and with low emission. This array form not only improves the volumetric heat intensity of the combustion chamber, but also enhances the stability and controllability of the combustion process.

[0056] It should be noted that different micro-mixing rotational flow devices can be obtained according to the number and twist of the outer wall ring 10 and the hollow vane of the rotational flow device, the size of the central bluff body 9, the position and size of the fuel injection hole 6, the form of the fuel passage, and the arrangement form and spacing of the head unit.

[0057] According to an embodiment of the present application, the cyclone passage comprises an air inlet annular passage 2 and an air outlet annular passage 7, the air inlet annular passage 2 is connected to the air outlet annular passage 7, the air inlet annular passage 2 is located at the first side of the hollow cyclone vane 3, the air outlet annular passage 7 is located at the second side of the hollow cyclone vane 3, and the air outlet annular passage 7 is gradually reduced in opening along the flow direction of the air to form a converging passage.

[0058] It can be understood that the air inlet annular passage 2 is located at the first side (such as the upstream side) of the hollow cyclone vane 3, and the air outlet annular passage 7 is located at the second side (such as the downstream side) of the hollow cyclone vane 3. The air inlet annular passage 2 serves as the air inlet, which is responsible for introducing external air into the interior of the cyclone. The design should ensure that the air can enter the cyclone uniformly and smoothly, providing sufficient oxygen for subsequent cyclone generation and fuel mixing. The air outlet annular passage 7 serves as the air outlet, which forms a converging passage with the central body 9 and the outer wall ring 10. The converging passage helps to guide the air cyclone and enhances the cyclone effect, thereby further promoting the mixing of fuel and air.

[0059] According to an embodiment of the present application, the outer wall ring 10 and the central body 9 are provided with chamfers at the inlet of the air inlet annular passage 2. In this embodiment, the outer wall ring 10 and the central body 9 are provided with chamfers at the inlet of the air inlet annular passage 2. This design is beneficial to reduce the inlet pressure loss and improve the smoothness and efficiency of air flow.

[0060] In one embodiment, low-oxygen air (SOFC cathode tail gas) enters from the upstream of the cyclone, fuel (SOFC anode tail gas) first enters the fuel supply ring cavity 1 through the fuel connection channels 4 distributed around, then enters the central body fuel cavity 8 through the vane fuel channels 5, and finally is sprayed out from the array fuel injection holes 6; the air flow first enters the air inlet passage and flows through the flow passage composed of multiple hollow cyclone vanes 3, then passes through the converging passage formed by the outer wall of the cyclone and the central body 9, and finally flows out from the air outlet passage to mix with the anode tail gas.

[0061] According to an embodiment of the present application, the fuel injection holes 6 are uniformly distributed along the circumference of the top of the central body 9. It can be understood that the fuel injection holes 6 are arranged in an equidistant manner along the edge of the top of the central body 9, which can ensure that the fuel can uniformly cover the target area when sprayed, thereby improving the combustion efficiency or the uniformity of the chemical reaction.

[0062] According to an embodiment of the present application, the central body 9 protrudes from the central passage, and the plane where the fuel injection holes 6 are located and the end surface of the outer wall ring 10 are spaced apart.

[0063] The plane where the fuel injection holes 6 are located refers to a two-dimensional plane where the fuel injection holes 6 distributed along the circumference of the top of the central bluff body 9 are located. There is a certain distance or gap between the plane where the fuel injection holes 6 are located and the end face of the outer wall ring 10, which can ensure that the fuel can be correctly and stably injected into the vortex generated by the swirler.

[0064] According to one embodiment of the present application, please refer to Figures 6 to 11 , the outer contour of the outer wall ring 10 is one of a hexagon, a pentagon, a rectangle, a square, a triangle, and a circle.

[0065] In one embodiment, the outer contour of the outer wall ring 10 is a square, the height H of the outer wall ring 10 ranges from 15 mm to 60 mm, the thickness T of the outer wall ring 10 ranges from 10 mm to 60 mm, the inlet inner diameter D ii of the outer wall ring 10 ranges from 10 mm to 55 mm, and the outlet inner diameter D eo of the outer wall ring 10 ranges from 8 mm to 53 mm.

[0066] According to one embodiment of the present application, the hollow swirler blade 3 is one of a twisted blade, a non-twisted blade, a curved blade, and a straight blade.

[0067] In one embodiment, the hollow swirler blade 3 is a non-twisted blade, the blade inclination angle a of the hollow swirler blade 3 ranges from 20° to 70°, the blade length L of the hollow swirler blade 3 ranges from 5 mm to 25 mm, and the number n A of the hollow swirler blade 3 ranges from 4 to 16.

[0068] According to one embodiment of the present application, the inlet outer diameter D io of the central bluff body 9 ranges from 5 mm to 55 mm, the outlet outer diameter D ei of the central bluff body 9 ranges from 6 mm to 58 mm, and the bluff body trailing edge diameter D oi of the central bluff body 9 ranges from 4 mm to 60 mm.

[0069] According to one embodiment of the present application, please refer to Figures 12 to 17 , the fuel injection hole 6 is one of a circular hole, an elliptical hole, an arched hole, a round rectangular hole, and a triangular hole. Among them, the round rectangular hole radius can be half of the rectangular hole, forming a shape similar to a playground track.

[0070] In one embodiment, the number n B of the fuel injection hole 6 ranges from 2 to 30, the hole diameter d j ranges from 0.1 mm to 2.5 mm, and the distance h between the plane where the fuel injection hole 6 is located and the end face of the outer wall ring 10 ranges from 0 mm to 6 mm.

[0071] According to one embodiment of the present application, the number n of the fuel connection passages C is 2 to 8, and the cross-sectional area of the individual fuel connection passages ranges from 1 mm 2 to 100 mm 2 .

[0072] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, and are not intended to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that the technical solutions recorded in the foregoing embodiments can still be modified, or some technical features therein can be replaced by equivalents; and such modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A swirl burner, characterized by The application relates to a fuel injection device, which comprises the following parts: an outer wall ring (10) with a central passage in the middle, a fuel supply ring cavity (1) in the inner part of the outer wall ring (10), and a fuel connection passage (4) in the outer wall ring (10) and connected with the fuel supply ring cavity (1); a central blunt body (9) in the central passage, a central blunt body fuel cavity (8) in the inner part of the central blunt body (9), and a plurality of fuel injection holes (6) in the central blunt body (9) and distributed along the circumferential direction of the top of the central blunt body (9), wherein the fuel injection holes (6) are connected with the central blunt body fuel cavity (8); a plurality of hollow swirl vanes (3) connected with the central blunt body (9) and the outer wall ring (10), wherein the hollow swirl vanes (3) are provided with vane fuel passages (5) in the inner parts of the hollow swirl vanes (3), and the vane fuel passages (5) are connected with the central blunt body fuel cavity (8) and the fuel supply ring cavity (1); a swirl passage is formed between the outer wall ring (10), the central blunt body (9) and the hollow swirl vanes (3), air flows through the swirl passage to form air swirl, and the fuel injection holes (6) are used for injecting fuel to mix with the air swirl in the form of transverse jet flow and combust.

2. The swirl burner of claim 1, wherein The swirl passage comprises an air inlet annular passage (2) and an air outlet annular passage (7), the air inlet annular passage (2) is connected with the air outlet annular passage (7), the air inlet annular passage (2) is located on the first side of the hollow swirl vane (3), the air outlet annular passage (7) is located on the second side of the hollow swirl vane (3), and the opening of the air outlet annular passage (7) gradually decreases to form a tapered passage along the flowing direction of the air.

3. The swirl burner of claim 2, wherein The outer wall ring (10) and the central blunt body (9) are provided with chamfers at the inlet of the air inlet annular passage (2).

4. The swirl burner of claim 1, wherein The fuel injection holes (6) are uniformly distributed along the circumferential direction of the top of the central blunt body (9).

5. The swirl burner of claim 1, wherein The top of the central blunt body (9) protrudes from the central passage, and the plane where the fuel injection holes (6) are located and the end surface of the outer wall ring (10) are spaced apart.

6. The swirl burner according to any one of claims 1 to 5, characterized in that The outer contour of the outer wall ring (10) is one of hexagon, pentagon, rectangle, square, triangle and circle. In the case that the outer contour of the outer wall ring (10) is square, the height H of the outer wall ring (10) ranges from 15 mm to 60 mm; the thickness T of the outer wall ring (10) ranges from 10 mm to 60 mm; the inlet inner diameter D ii of the outer wall ring (10) ranges from 10 mm to 55 mm; and the outlet inner diameter D eo of the outer wall ring (10) ranges from 8 mm to 53 mm.

7. The swirl burner according to any one of claims 1 to 5, characterized in that The hollow cyclone vane (3) is one of twisted vane, non-twisted vane, curved vane and straight vane, in the case of non-twisted vane, the vane angle α of the hollow cyclone vane (3) ranges from 20° to 70°; the vane length L of the hollow cyclone vane (3) ranges from 5mm to 25mm; the number n of the hollow cyclone vane (3) ranges from 4 to 16. A The hollow cyclone vane (3) is one of twisted vane, non-twisted vane, curved vane and straight vane, in the case of non-twisted vane, the vane angle α of the hollow cyclone vane (3) ranges from 20° to 70°; the vane length L of the hollow cyclone vane (3) ranges from 5mm to 25mm; the number n of the hollow cyclone vane (3) ranges from 4 to 16.

8. The swirl burner according to any one of claims 1 to 5, characterized in that The outer diameter D of the inlet of the central bluff body (9) io ranging from 5 mm to 55 mm; the outer diameter D of the outlet of the central bluff body (9) ei ranging from 6 mm to 58 mm; the diameter D of the trailing edge of the central bluff body (9) oi ranging from 4 mm to 60 mm.

9. The swirl burner according to any one of claims 1 to 5, characterized in that The fuel injection hole (6) is one of a circular hole, an elliptical hole, an arcuate hole, a rounded rectangular hole, and a triangular hole, the number n of the fuel injection holes (6) is 2 to 30, the hole diameter d is 0.1 mm to 2.5 mm, and the distance h between the plane in which the fuel injection holes (6) are located and the end surface of the outer wall ring (10) is 0 mm to 6 mm. B j j j j j j j j j j j j j j j j j j j j j j j j j j j j j j <000000 10. The swirl burner according to any one of claims 1 to 5, characterized in that The number of passages n of the fuel connection passage (4) C is 2 to 8, and the passage cross-sectional area of the individual fuel connection passage (4) ranges from 1 mm 2 to 100 mm 2 .

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