Turbulent burner

Abstract

The invention relates to the field of fuel injection, and provides a turbulent burner which comprises an outer wall ring, a central bluff body and a plurality of hollow rotational flow blades, a central channel 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 channel, and the fuel connecting channel is communicated with the fuel supply ring cavity; the central bluff body is located in the central channel, a central bluff body fuel cavity is formed in the central bluff body, and a plurality of fuel spray holes are formed in the central bluff body; the hollow swirl vane is connected with the central bluff body and the outer wall ring, a vane fuel channel is arranged in the hollow swirl vane, and the vane fuel channel is communicated with the central bluff body fuel cavity and the fuel supply ring cavity; a rotational flow channel is formed among the outer wall ring, the central bluff body and the hollow rotational flow blades, air flows through the rotational flow channel to form air rotational flow, and the fuel spraying holes are used for spraying fuel and mixed with the air rotational flow for combustion in a transverse jet flow mode.

Description

Technical Field

[0001] The invention relates to the technical field of fuel injection, and in particular to a swirl burner. Background Art

[0002] As global awareness of environmental protection increases, the use of hydrogen to replace traditional hydrocarbon fuels has become one of the important development directions and technical approaches for future zero-carbon aviation power. As a clean energy source, hydrogen only produces water as a combustion product, which is pollution-free and is the key to achieving the goal of carbon neutrality in the aviation industry. However, due to the low volume energy density of hydrogen, future hydrogen-powered aviation power systems need to continuously pursue higher comprehensive thermal efficiency to ensure sufficient endurance.

[0003] In order to improve the comprehensive thermal efficiency of hydrogen-powered aviation power systems, the combined cycle technology of solid oxide fuel cells (SOFC) and aviation gas turbines (GT) came into being. This technology achieves the cascade utilization of energy by coupling electrochemical reactions and combustion chemical reactions. SOFC fueled by green hydrogen can efficiently convert hydrogen energy into electrical energy, while the incompletely reacted hydrogen continues to be passed into the combustion chamber with air to burn, further driving the turbine to do work. This combined cycle process is expected to increase the comprehensive thermal efficiency of the corresponding power unit to 60-70%, and is a highly promising 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 gas is often significantly higher than the air pressure at the combustion chamber inlet. The fuel flow path can use a sufficiently high pressure difference to give the gas jet the required momentum, thereby helping it to quickly mix with the air and burn evenly. However, in the scenario where SOFC tail gas is used as a combustion medium, the supply pressure of the fuel (anode tail gas) needs to be almost the same as that of the oxidant side (cathode tail gas), 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 lateral fuel jet, which in turn affects the mixing effect of the fuel jet and the oxidant. This will lead to a high local equivalence ratio in the flame, resulting in local hot spots and pushing up nitrogen oxide emissions. In addition, the combustion organization scheme in the premixed mode is also not suitable for the combustion of SOFC tail gas. The reason is that the electrochemical reaction gives the SOFC tail gas a higher temperature, which greatly shortens the ignition delay time, and is very likely to cause hydrogen to spontaneously ignite in the premixed section, causing a flashback risk. Summary of the invention

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

[0006] A swirl burner according to an embodiment of the first aspect of the present application includes: An outer wall ring, wherein a central channel is formed in the middle of the outer wall ring, a fuel supply ring cavity is arranged inside the outer wall ring, and a fuel connecting channel is opened in the outer wall ring, and the fuel connecting channel is connected to the fuel supply ring cavity; A central bluff body is located in the central channel, a central bluff body fuel cavity is provided inside the central bluff body, a plurality of fuel spray holes are opened in the central bluff body, the fuel spray holes are distributed along the circumference of the top of the central bluff body, and the fuel spray holes are connected to the central bluff body fuel cavity; A plurality of hollow swirl blades, wherein the hollow swirl blades are connected to the central bluff body and the outer wall ring, and a blade fuel channel is provided inside the hollow swirl blades, and the blade fuel channel is connected to the central bluff body fuel cavity and the fuel supply ring cavity; A swirl channel is formed between the outer wall ring, the central blunt body and the hollow swirl blades. Air flows through the swirl channel to form an air swirl. The fuel injection hole is used to inject fuel to mix with the air swirl in a transverse jet manner for combustion.

[0007] According to the swirl burner of the embodiment of the present application, an air swirl is generated by a central blunt body and hollow swirl blades, and a multi-point injection diffusion flame layout is adopted. The gaseous fuel jet is ejected from the fuel nozzle array located at the top of the central blunt body and enters the air swirl laterally. The mixing is enhanced by combining swirl stirring and multi-point fuel injection, so that the fuel is quickly and evenly mixed with the air along the entire cross-section. The swirl burner of the present application can reduce the dependence on the injection speed of the lateral jet of the fuel, thereby reducing the demand for the gas supply pressure. At the same time, the flame can also be controlled in the shear layer of the air swirl to prevent combustion oscillations and excessive nitrogen oxide emissions that may be caused by combustion in the corner vortex zone. In addition, the risk of spontaneous combustion and flashback of the fuel is avoided by adopting a diffusion combustion layout. The swirl burner of the present application can form a combustion chamber head in the form of an array, which is used to organize the efficient, stable and low-emission combustion of low calorific value anode tail gas.

[0008] According to one embodiment of the present application, the swirl channel includes an inlet annular channel and an outlet annular channel, the inlet annular channel is connected to the outlet annular channel, the inlet annular channel is located on the first side of the hollow swirl blade, and the outlet annular channel is located on the second side of the hollow swirl blade, and the opening of the outlet annular channel gradually decreases along the flow direction of the air to form a tapered channel.

[0009] According to an embodiment of the present application, the outer wall ring and the central bluff body are provided with chamfers at the inlet of the air intake annular channel.

[0010] According to an embodiment of the present application, the fuel injection holes are evenly distributed along the circumference of the top of the central bluff body.

[0011] According to an embodiment of the present application, the top of the central bluff body extends out of the central channel, and the plane where the fuel injection holes are located and the end surface of the outer wall ring are spaced apart.

[0012] 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. When 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 inlet inner diameter D of the outer wall ring ii The range is 10mm~55mm; the outlet inner diameter D of the outer wall ring eo The range is 8mm~53mm.

[0013] According to one embodiment of the present application, the hollow swirl blade is one of a twisted blade, a non-twisted blade, a curved blade, and a straight blade. When the hollow swirl blade is a non-twisted blade, the blade inclination angle α of the hollow swirl blade ranges from 20° to 70°; the blade length L of the hollow swirl blade ranges from 5 mm to 25 mm; the number of blades n of the hollow swirl blade is A 4 to 16 pieces.

[0014] According to one embodiment of the present application, the inlet outer diameter D of the central bluff body is io The range is 5mm to 55mm; the outlet outer diameter D of the central blunt body ei The range is 6mm to 58mm; the diameter D of the trailing edge of the central bluff body oi The range is 4mm~60mm.

[0015] According to one embodiment of the present application, the fuel spray hole is one of a circular spray hole, an elliptical spray hole, an arched spray hole, a rounded rectangular spray hole, and a triangular spray hole. The number of the fuel spray holes n is B 2 to 30, aperture d j The range is 0.1mm~2.5mm, and the distance h between the plane where the fuel injection hole is located and the end face of the outer wall ring is in the range of 0mm~6mm.

[0016] According to one embodiment of the present application, the number of channels n of the fuel connection channel is C The number of fuel connection channels is 2 to 8, and the cross-sectional area of ​​a single fuel connection channel is 1 mm 2 ~100mm 2 .

[0017] Additional aspects and advantages of the present application will be given in part in the description below, and in part will become apparent from the description below, or will be learned through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Scope In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0019] Figure 1 It is a schematic diagram of the cross-sectional axial structure of the swirl burner provided in an embodiment of the present application.

[0020] Figure 2 It is a schematic diagram of the structure of the swirl burner provided in the embodiment of the present application.

[0021] Figure 3 It is a schematic diagram of the cross-sectional structure in the direction of A of the swirl burner provided in an embodiment of the present application.

[0022] Figure 4 yes Figure 3 A schematic diagram of a partially enlarged structure of a swirl burner provided in an embodiment.

[0023] Figure 5 It is a schematic diagram of the structure of the hollow swirl blade provided in the embodiment of the present application.

[0024] Figure 6 It is a structural schematic diagram of an embodiment of the present application in which the outer contour shape of the outer wall ring is a hexagon.

[0025] Figure 7 It is a structural schematic diagram of an embodiment of the present application in which the outer contour shape of the outer wall ring is a pentagon.

[0026] Figure 8 It is a structural schematic diagram of an embodiment of the present application in which the outer contour of the outer wall ring is a square.

[0027] Fig. 9 It is a structural schematic diagram of an embodiment of the present application in which the outer contour of the outer wall ring is a rectangular shape.

[0028] Fig.10 It is a structural schematic diagram of an embodiment of the present application in which the outer contour shape of the outer wall ring is a triangle.

[0029] Fig.11 It is a structural schematic diagram of an embodiment of the present application in which the outer contour of the outer wall ring is circular.

[0030] Fig.12 This is one of the structural schematic diagrams of the fuel injection hole provided in the embodiment of the present application, which is in the shape of a rounded rectangle.

[0031] Fig.13It is a structural schematic diagram of a fuel injection hole with an elliptical shape provided in an embodiment of the present application.

[0032] Fig.14 It is a structural schematic diagram of a circular fuel injection hole provided in an embodiment of the present application.

[0033] Fig.15 It is a structural schematic diagram of a fuel injection hole with a triangular shape provided in an embodiment of the present application.

[0034] Fig.16 It is a schematic structural diagram of a fuel injection hole in a quadrilateral shape provided in an embodiment of the present application.

[0035] Fig.17 This is the second structural schematic diagram of the fuel injection hole in the embodiment of the present application, which is in the shape of a rounded rectangle.

[0036] Reference numerals: 1. Fuel supply annular cavity; 2. Inlet annular channel; 3. Hollow swirl blades; 4. Fuel connection channel; 5. Blade fuel channel; 6. Fuel nozzle; 7. Exhaust annular channel; 8. Central blunt body fuel cavity; 9. Central blunt body; 10. Outer wall ring. DETAILED DESCRIPTION

[0037] The following is a further detailed description of the implementation of the present application in conjunction with the accompanying 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.

[0038] In the description of the embodiments of the present application, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc. indicate the range of orientation or position relationship based on the orientation or position relationship shown in the accompanying drawings. The range is only for the convenience of describing the embodiments of the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, the range cannot be understood as a limitation on the embodiments of the present application. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and the range cannot be understood as indicating or implying relative importance.

[0039] In the description of the embodiments of the present application, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection, wherein the fixed connection can include an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific circumstances.

[0040] In the embodiments of the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean 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, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0041] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the embodiments of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0042] Combine the following Figure 1-Figure 17 The swirl burner of the present invention is described.

[0043] According to a swirl burner proposed in the embodiment of the present application, please refer to Figures 1 to 5 The swirl burner includes an outer wall ring 10, a central blunt body 9 and a plurality of hollow swirl blades 3. A central channel is formed in the middle of the outer wall ring 10. A fuel supply ring cavity 1 is provided inside the outer wall ring 10. A fuel connecting channel 4 is opened in the outer wall ring 10. The fuel connecting channel 4 is connected to the fuel supply ring cavity 1. The central blunt body 9 is located in the central channel. A central blunt body fuel cavity 8 is provided inside the central blunt body 9. A plurality of fuel spray holes 6 are opened in the central blunt body 9. The fuel spray holes 6 are distributed circumferentially along the top of the central blunt body 9. The fuel spray holes 6 are connected to the central blunt body fuel cavity 8. The hollow swirl blades 3 connect the central blunt body 9 and the outer wall ring 10. A blade fuel channel 5 is provided inside the hollow swirl blades 3. The blade fuel channel 5 is connected to the central blunt body fuel cavity 8 and the fuel supply ring cavity 1. A swirl channel is formed between the outer wall ring 10, the central blunt body 9 and the hollow swirl blades 3. Air flows through the swirl channel to form an air swirl. The fuel spray holes 6 are used to inject fuel, which is mixed and burned with the air swirl in the form of a transverse jet.

[0044] According to the swirl burner of the embodiment of the present application, an air swirl is generated by the central bluff body 9 and the hollow swirl blades 3, and a multi-point injection diffusion flame layout is adopted. The gaseous fuel jet is ejected from the array of fuel nozzles 6 located at the top of the central bluff body 9 and enters the air swirl laterally. The mixing is enhanced by combining swirl stirring and multi-point fuel injection, so that the fuel is quickly and evenly mixed with the air along the entire cross-section. The swirl burner of the present application can reduce the dependence on the injection speed of the lateral jet of the fuel, thereby reducing the demand for the gas supply pressure. At the same time, the flame can also be controlled in the shear layer of the air swirl to prevent combustion oscillations and excessive nitrogen oxide emissions that may be caused by combustion in the corner vortex zone. In addition, the risk of spontaneous combustion and flashback of the fuel is avoided by adopting a diffusion combustion layout. The swirl burner of the present application can form a combustion chamber head in the form of an array, which is used to organize the efficient, stable and low-emission combustion of low calorific value anode tail gas.

[0045] The outer wall ring 10 is the peripheral structure of the cyclone, which is used to fix the blades, constrain the airflow and connect with other head units. A central channel is formed in the middle of the outer wall ring 10, which provides installation space for the central blunt body 9 and the hollow swirl blades 3, and also provides a flow space for the gas. A fuel supply ring cavity 1 is provided inside the outer wall ring 10 for storing and distributing fuel. The fuel supply ring cavity 1 can ensure that the fuel enters each blade fuel channel 5 evenly. The outer wall ring 10 is also provided with fuel connection channels 4, which are connected to the fuel supply ring cavity 1 to ensure that the fuel can smoothly enter the cyclone. The fuel connection channel 4 is used to connect the fuel supply ring cavity 1 with other head micro-swirl units and / or fuel pipelines, thereby forming a complete head array.

[0046] The central bluff body 9 is located in the central channel, which plays a role in stabilizing the airflow and enhancing the swirl effect. The central bluff body 9 is used to strengthen the downstream backflow strength to stabilize the flame. A central bluff body fuel cavity 8 is provided inside the central bluff body 9. The central bluff body fuel cavity 8 is used to collect the fuel from the blade fuel channel 5 and ensure that the fuel can be evenly sprayed from the fuel nozzle hole 6. A plurality of fuel nozzle holes 6 are distributed along the circumference on the top of the central bluff body 9. These nozzle holes inject the fuel into the air swirl laterally in a multi-point injection manner to mix and burn with the air swirl, forming a diffusion flame layout.

[0047] The hollow swirl blade 3 connects the central bluff body 9 and the outer wall ring 10, and the hollow swirl blade 3, the central bluff body 9 and the outer wall ring 10 form a swirl channel. The hollow swirl blade 3 is used to generate swirl, which plays a role in strengthening mixing and forming a reflux zone to stabilize fire. A blade fuel channel 5 is provided inside the blade, and the blade fuel channel 5 connects 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.

[0048] The swirl burner proposed in this application aims to achieve rapid and uniform mixing of fuel and air by optimizing airflow organization and fuel injection method, thereby improving combustion efficiency, reducing emissions, and ensuring combustion stability and controllability.

[0049] When the air flows through the swirl channel between the outer wall ring 10 and the central blunt body 9 and the hollow swirl blades 3, the air is guided to form a swirl due to the shape and arrangement of the blades. The fuel enters the air swirl in a multi-point injection manner through the fuel nozzle 6 at the top of the central blunt body 9. Since the nozzles are distributed circumferentially, the fuel can be evenly distributed in the swirl, fully mixed with the air and burned to form a diffusion flame layout. By combining swirl stirring and multi-point fuel injection, the swirler of the present application can significantly enhance the mixing effect of fuel and air. At the same time, the design of the central blunt body 9 and the hollow swirl blades 3 helps to form a stable recirculation zone, further stabilize the flame, and prevent the occurrence of combustion oscillation and flashback. Due to the use of multi-point injection and swirl stirring, the swirler of the present application reduces the dependence on the injection velocity of the fuel lateral jet, thereby reducing the demand for gas supply pressure.

[0050] It should be noted that the cyclones of the present application can be formed into an array at the head of the combustion chamber, and through the synergistic effect of multiple cyclones, efficient, stable and low-emission combustion of low calorific value anode tail gas can be achieved. This array form not only improves the volumetric thermal intensity of the combustion chamber, but also enhances the stability and controllability of the combustion process.

[0051] It should be noted that different micro-mixing swirlers can be provided according to the outer wall ring 10, the number and twist of the hollow blades of the swirler, the size of the central bluff body 9, the position and size of the fuel nozzle 6, the form of the fuel channel, and the arrangement form and spacing of the head units.

[0052] According to one embodiment of the present application, the swirl channel includes an inlet annular channel 2 and an outlet annular channel 7. The inlet annular channel 2 is connected to the outlet annular channel 7. The inlet annular channel 2 is located on the first side of the hollow swirl blade 3, and the outlet annular channel 7 is located on the second side of the hollow swirl blade 3. The opening of the outlet annular channel 7 gradually decreases along the flow direction of the air to form a tapered channel.

[0053] It can be understood that the air inlet annular channel 2 is located on the first side (such as the upstream side) of the hollow swirl blade 3, and the air outlet annular channel 7 is located on the second side (such as the downstream side) of the hollow swirl blade 3. The air inlet annular channel 2 serves as the air inlet and is responsible for introducing external air into the swirler. Its design should ensure that the air can enter the swirler evenly and smoothly, providing sufficient oxygen for subsequent swirl generation and fuel mixing. The air outlet annular channel 7 serves as the air outlet, and a tapered channel is formed by the central bluff body 9 and the outer wall ring 10. The tapered channel helps to guide the air swirl and enhance the swirl effect, thereby further promoting the mixing of fuel and air.

[0054] According to one embodiment of the present application, the outer wall ring 10 and the central bluff body 9 are provided with chamfers at the inlet of the air intake annular channel 2. In this embodiment, the outer wall ring 10 and the central bluff body 9 are provided with chamfers at the inlet of the air intake annular channel 2. This design is conducive to reducing the inlet pressure loss and improving the smoothness and efficiency of air flow.

[0055] In one embodiment, low-oxygen air (SOFC cathode exhaust gas) enters from the upstream of the cyclone, and the fuel (SOFC anode exhaust gas) first enters the fuel supply ring cavity 1 through the fuel connection channels 4 distributed on the surroundings, then enters the central blunt body fuel cavity 8 through the blade fuel channel 5, and finally is ejected from the array fuel nozzle 6; the air flow first enters the air inlet channel and flows through the flow channel formed by multiple hollow swirl blades 3, passes through the tapered channel formed by the outer wall of the cyclone and the central blunt body 9, and finally flows out from the air outlet channel to mix with the anode exhaust gas.

[0056] According to one embodiment of the present application, the fuel injection holes 6 are evenly distributed along the circumference of the top of the central bluff 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 bluff body 9, which can ensure that the fuel can evenly cover the target area when injected, thereby improving the combustion efficiency or the uniformity of the chemical reaction.

[0057] According to an embodiment of the present application, the top of the central bluff body 9 extends out of the central channel, and the plane where the fuel injection holes 6 are located and the end surface of the outer wall ring 10 are spaced apart.

[0058] The plane where the fuel injection holes 6 are located refers to the two-dimensional plane where the fuel injection holes 6 are distributed circumferentially along the top of the central bluff body 9. 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 swirl generated by the swirler.

[0059] According to an 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.

[0060] 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 of the outer wall ring 10 ii The range is 10mm~55mm; the outlet inner diameter D of the outer wall ring 10 eo The range is 8mm~53mm.

[0061] According to an embodiment of the present application, the hollow swirl blade 3 is one of a twisted blade, a non-twisted blade, a curved blade, and a straight blade.

[0062] In one embodiment, the hollow swirl blade 3 is a non-twisted blade, the blade inclination angle α of the hollow swirl blade 3 ranges from 20° to 70°; the blade length L of the hollow swirl blade 3 ranges from 5 mm to 25 mm; the number of blades n of the hollow swirl blade 3 is A 4 to 16 pieces.

[0063] According to one embodiment of the present application, the inlet outer diameter D of the central bluff body 9 is io The range is 5mm~55mm; the outlet outer diameter D of the central blunt body 9 ei The range is 6mm~58mm; the diameter D of the tail edge of the central bluff body 9 oi The range is 4mm~60mm.

[0064] According to an embodiment of the present application, please refer to Figures 12 to 17 The fuel injection hole 6 is one of a circular injection hole, an elliptical injection hole, an arched injection hole, a rounded rectangular injection hole, and a triangular injection hole. The rounded corner radius of the rounded rectangle can be half of the rectangle, forming a shape similar to a playground runway.

[0065] In one embodiment, the number n of the fuel injection holes 6 is B 2 to 30, aperture d j The range is 0.1mm~2.5mm, and the distance h between the plane where the fuel injection hole 6 is located and the end surface of the outer wall ring 10 is in the range of 0mm~6mm.

[0066] According to one embodiment of the present application, the number of channels n of the fuel connection channel is C The number of fuel connection channels is 2 to 8, and the cross-sectional area of ​​a single fuel connection channel ranges from 1 mm 2 ~100mm 2 .

[0067] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A swirl burner, characterized in that: include: An outer wall ring (10), wherein a central channel is formed in the middle of the outer wall ring (10), a fuel supply ring cavity (1) is provided inside the outer wall ring (10), and a fuel connection channel (4) is opened on the outer wall ring (10), wherein the fuel connection channel (4) is connected to the fuel supply ring cavity (1); A central bluff body (9) is located in the central passage, a central bluff body fuel cavity (8) is provided inside the central bluff body (9), a plurality of fuel injection holes (6) are opened 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 connected to the central bluff body fuel cavity (8); A plurality of hollow swirl blades (3), wherein the hollow swirl blades (3) are connected to the central bluff body (9) and the outer wall ring (10), and a blade fuel channel (5) is provided inside the hollow swirl blades (3), and the blade fuel channel (5) is connected to the central bluff body fuel cavity (8) and the fuel supply ring cavity (1); A swirl channel is formed between the outer wall ring (10), the central blunt body (9) and the hollow swirl blades (3), and air flows through the swirl channel to form an air swirl. The fuel injection hole (6) is used to inject fuel to mix with the air swirl in a transverse jet manner for combustion.

2. The swirl burner according to claim 1, characterized in that: The swirl channel comprises an air inlet annular channel (2) and an air outlet annular channel (7), the air inlet annular channel (2) is connected to the air outlet annular channel (7), the air inlet annular channel (2) is located on a first side of the hollow swirl blade (3), and the air outlet annular channel (7) is located on a second side of the hollow swirl blade (3), and the opening of the air outlet annular channel (7) gradually decreases along the flow direction of the air to form a tapered channel.

3. The swirl burner according to claim 2, characterized in that: The outer wall ring (10) and the central bluff body (9) are provided with chamfers at the inlet of the air intake annular channel (2).

4. The swirl burner according to claim 1, characterized in that: The fuel injection holes (6) are evenly distributed along the circumference of the top of the central bluff body (9).

5. The swirl burner according to claim 1, characterized in that: The top of the central bluff body (9) protrudes from the central channel, and the plane where the fuel injection hole (6) is located and the end surface of the outer wall ring (10) are arranged at intervals.

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 a hexagon, a pentagon, a rectangle, a square, a triangle, and a circle. When the outer contour of the outer wall ring (10) is a square, the height H of the outer wall ring (10) is in the range of 15 mm to 60 mm; the thickness T of the outer wall ring (10) is in the range of 10 mm to 60 mm; the inlet inner diameter D of the outer wall ring (10) is ii The range is 10 mm to 55 mm; the outlet inner diameter D of the outer wall ring (10) eo The range is 8mm~53mm.

7. The swirl burner according to any one of claims 1 to 5, characterized in that: The hollow swirl blade (3) is one of a twisted blade, a non-twisted blade, a curved blade, and a straight blade. When the hollow swirl blade (3) is a non-twisted blade, the blade inclination angle α of the hollow swirl blade (3) is in the range of 20° to 70°; the blade length L of the hollow swirl blade (3) is in the range of 5 mm to 25 mm; the number n of blades of the hollow swirl blade (3) is A 4 to 16 pieces.

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

9. The swirl burner according to any one of claims 1 to 5, characterized in that: The fuel spray hole (6) is one of a circular spray hole, an elliptical spray hole, an arched spray hole, a rounded rectangular spray hole, and a triangular spray hole. The number n of the fuel spray holes (6) is B 2 to 30, aperture d j The range is 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 surface of the outer wall ring (10) is in the range of 0 mm to 6 mm.

10. The swirl burner according to any one of claims 1 to 5, characterized in that: The number n of channels of the fuel connection channel (4) C The number of the fuel connection channels (4) is 2 to 8, and the cross-sectional area of ​​a single fuel connection channel (4) is in the range of 1 mm 2 ~100mm 2 .

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