Turbulent burner

Abstract

The invention relates to the technical field of fuel injection, and provides a turbulent burner. The turbulent burner comprises an outer wall ring, a central bluff body, a plurality of rotational flow blades, a turbulent flow bluff body and an anti-vibration pile; a central channel is formed in the middle of the outer wall ring; the central bluff body is located in the central channel, a first fuel channel and a second fuel channel are formed in the central bluff body, and a first fuel spray hole communicated with the first fuel channel and a second fuel spray hole communicated with the second fuel channel are formed in the downstream of the central bluff body; the rotational flow blades are connected with the central bluff body and the outer wall ring; the turbulent flow bluff bodies are circumferentially distributed along the downstream of the central bluff body and are positioned on the upstream of the first fuel spray holes; a rotational flow channel is formed among the outer wall ring, the central bluff body, the turbulent flow bluff body and the rotational flow blades, air flows through the rotational flow channel to form air rotational flow, and the first fuel spraying holes and the second fuel spraying holes are used for spraying fuel and mixed with the air rotational flow for combustion in a transverse jet flow mode. The anti-vibration pile is connected with the outer wall ring, located at an outlet of the turbulent burner and arranged in the circumferential direction of the outer wall ring.

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 the world's 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 to the environment. 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 using green hydrogen as fuel 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 and avoiding the waste of waste heat from the reaction of fuel and fuel cells. 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] Since the current dynamic response performance of SOFC does not meet the requirements of stable operation under all operating conditions, the current SOFC-GT combined cycle architecture adopts two operating modes. Under operating conditions such as takeoff, climb, approach, and slow speed, SOFC is subject to a large rate of change in operating conditions, so SOFC is not turned on. At this time, the entire machine operates in GT mode, and the combustion chamber uses hydrogen as fuel. Under cruising conditions, the rate of change in operating conditions is very small, and SOFC is turned on to generate electricity. At this time, the combustion chamber uses anode exhaust gas as fuel. Therefore, the combustion chamber head nozzle suitable for the SOFC-GT combined cycle system needs to have the ability to take into account efficient and stable combustion of dual modes and dual fuels.

[0005] However, in the context of the dual-mode, dual-fuel system, the injection and mixing of the fuel still faces several challenges. In the existing traditional combustion chamber head nozzle, the maximum fuel supply pressure is often significantly higher than the combustion chamber inlet air pressure. However, in the scenario of using the fuel cell anode 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. Therefore, the injection pressure difference of the anode tail gas is extremely limited, resulting in insufficient fuel jet momentum and jet penetration depth, affecting the rapid and uniform mixing of the fuel and the oxidant, and ultimately causing local hot spots in the flame and pushing up nitrogen oxide emissions.

[0006] When burning pure hydrogen, the lower density of hydrogen will lead to low fuel jet momentum, which makes the hydrogen jet easily swept away by the air, and it is difficult to form ideal fuel jet penetration and dispersion, thus affecting the air-fuel mixing effect. The SOFC-GT combined cycle combustor needs to meet the requirements of efficient, stable, and low-emission combustion when using hydrogen or low calorific value anode tail gas as fuel. This poses a great challenge to the design of the combustion chamber head mixing unit. It is urgent to develop a combustion chamber head nozzle suitable for the SOFC-GT combined cycle system. It needs to have a combustion chamber head nozzle that takes into account efficient and stable combustion of dual modes and dual fuels. Summary of the invention

[0007] The present application aims to solve at least one of the technical problems existing in the related art. To this end, the present application proposes a swirl burner that can simultaneously take into account the efficient air-fuel mixing of gaseous dual fuels with two fuel supply pressure differences that are very different.

[0008] The swirl burner proposed in the embodiment of the present application includes: An outer wall ring, wherein a central channel is formed in the middle of the outer wall ring; a central bluff body, located in the central channel, a first fuel channel and a second fuel channel are arranged inside the central bluff body, the first fuel channel is arranged around the second fuel channel, a first fuel injection hole and a second fuel injection hole are opened downstream of the central bluff body, the first fuel injection hole and the second fuel injection hole are distributed along the downstream circumference of the central bluff body, the first fuel injection hole is located upstream of the second fuel injection hole, the first fuel injection hole is connected to the first fuel channel, and the second fuel injection hole is connected to the second fuel channel; A plurality of swirl blades connecting the central bluff body and the outer wall ring; A turbulent bluff body is distributed along the downstream circumference of the central bluff body, and the turbulent bluff body is located upstream of the first fuel injection hole; A swirl channel is formed between the outer wall ring, the central bluff body, the turbulent bluff body and the swirl blades, and air flows through the swirl channel to form an air swirl. The first fuel injection hole and the second fuel injection hole are used to inject fuel to mix and burn with the air swirl in a lateral jet manner. An anti-vibration stack is connected to the outer wall ring, the anti-vibration stack is located at the outlet of the swirl burner, and the anti-vibration stack is arranged circumferentially along the outer wall ring.

[0009] According to the swirl burner of the embodiment of the present application, two sets of fuel injection systems and fuel flow paths are integrated through the first fuel channel and the second fuel channel and the first fuel nozzle hole and the second fuel nozzle hole to simultaneously meet the different requirements of the two fuels for injection performance (pressure difference). At the same time, three different flow modes of air swirl, multiple fuel lateral jets, and turbulence generated by the turbulent blunt body are coupled downstream of the central blunt body to enhance air-fuel mixing and make up for the disadvantage of poor mixing effect of a single lateral jet, thereby controlling local hot spots and inhibiting the generation of nitrogen oxides while ensuring efficient and stable combustion.

[0010] According to one embodiment of the present application, the first fuel channel is an annular channel, and the annular channel is arranged in an annular manner around the second fuel channel.

[0011] According to an embodiment of the present application, the first fuel injection holes and the second fuel injection holes are staggeredly distributed in the circumferential direction of the central bluff body.

[0012] 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.

[0013] 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 L 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.

[0014] 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.

[0015] According to one embodiment of the present application, the outer diameter D of the central bluff body ranges from 5 mm to 55 mm.

[0016] According to an embodiment of the present application, the first 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 first fuel spray holes n h The range is 2 to 30, and the diameter of the first fuel injection hole d h The range is 0.1mm~2.5mm, and the distance h1 between the plane where the first fuel injection hole is located and the end surface of the outer wall ring is 0mm~6mm; and / or, The second 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 second fuel spray holes ranges from n l The number of the second fuel injection holes is 2 to 30, and the diameter d of the second fuel injection holes is l The range is 0.5mm~4mm, and the distance h2 between the plane where the second fuel injection hole is located and the end face of the outer wall ring is in the range of 0mm~6mm.

[0017] According to one embodiment of the present application, the outer contour of the spoiler is one of a pyramid type, a cylindrical type, a conical type, a rectangular type, and a blade type. When the outer contour of the spoiler is a triangular pyramid type, the width w of the spoiler is in the range of 0.5 mm to 10 mm, the inclination angle β of the spoiler is in the range of 5° to 80°, the height h of the spoiler is in the range of 0.8 mm to 20 mm, and the distance l between the installation position of the spoiler and the end face of the outer wall ring is in the range of 0 to 5 mm.

[0018] 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

[0019] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. 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 paying creative work.

[0020] 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.

[0021] Figure 2 It is a schematic diagram of the structure of the swirl burner provided in the embodiment of the present application.

[0022] Figure 3 It is a schematic diagram of the dimensions of the swirl burner provided in the embodiment of the present application.

[0023] Figure 4 yes Figure 3 A schematic diagram of the cross-sectional structure of a swirl burner provided in an embodiment, as viewed in the direction of A.

[0024] Figure 5 yes Figure 4 A schematic diagram of a partially enlarged structure of a swirl burner provided in an embodiment.

[0025] Figure 6 It is a schematic diagram of the structure of the hollow swirl blade provided in the embodiment of the present application.

[0026] Figure 7 It is a schematic diagram of the structure of the spoiler bluff body provided in an embodiment of the present application.

[0027] Figure 8 It is a schematic diagram of the dimensions of the spoiler bluff body provided in the embodiment of the present application.

[0028] Fig. 9 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.

[0029] 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 pentagon.

[0030] 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 a square.

[0031] Fig.12 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.

[0032] Fig.13 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.

[0033] Fig.14 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.

[0034] Fig.15 This is one of the structural schematic diagrams provided in the embodiment of the present application in which the shape of the first fuel injection hole and / or the second fuel injection hole is a rounded rectangle.

[0035] Fig.16 It is a structural schematic diagram of the first fuel injection hole and / or the second fuel injection hole provided in the embodiment of the present application having an elliptical shape.

[0036] Fig.17 It is a structural schematic diagram of a first fuel injection hole and / or a second fuel injection hole provided in an embodiment of the present application having a circular shape.

[0037] Fig.18It is a structural schematic diagram of a first fuel injection hole and / or a second fuel injection hole provided in an embodiment of the present application having a triangular shape.

[0038] Fig.19 It is a schematic structural diagram of a first fuel injection hole and / or a second fuel injection hole provided in an embodiment of the present application in a quadrilateral shape.

[0039] Fig. 20 This is the second structural schematic diagram of the first fuel injection hole and / or the second fuel injection hole provided in the embodiment of the present application in a shape of a rounded rectangle.

[0040] Fig.21 It is a schematic structural diagram of a spoiler provided in an embodiment of the present application in the shape of a triangular pyramid.

[0041] Fig. 22 It is a schematic structural diagram of a spoiler provided in an embodiment of the present application in the shape of a cylinder.

[0042] Fig.23 It is a schematic diagram of the structure in which the spoiler provided in an embodiment of the present application is in the shape of a cone.

[0043] Fig.24 It is a schematic structural diagram of a spoiler provided in an embodiment of the present application in the shape of a rectangular parallelepiped.

[0044] Fig.25 It is a schematic structural diagram of a spoiler provided in an embodiment of the present application in the shape of a blade.

[0045] Reference numerals: 1. Inlet annular channel; 2. First fuel channel; 3. Second fuel channel; 4. Outer wall ring; 5. Outlet annular channel; 6. First fuel nozzle hole; 7. Second fuel nozzle hole; 8. Swirl blade; 9. Turbine blunt body; 10. Anti-vibration pile; 11. Central blunt body. DETAILED DESCRIPTION

[0046] 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.

[0047] 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" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, which are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the embodiments of the present application. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0048] 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.

[0049] 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.

[0050] 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.

[0051] Combine the following Figure 1-Figure 25 The swirl burner of the present invention is described.

[0052] According to the swirl burner proposed in the embodiment of the present application, please refer to Figure 1 and Figure 2 The swirl burner includes an outer wall ring 4, a central bluff body 11, a plurality of swirl blades 8 and a turbulent bluff body 9. A central channel is formed in the middle of the outer wall ring 4. The central bluff body 11 is located in the central channel. A first fuel channel 2 and a second fuel channel 3 are arranged inside the central bluff body 11. The first fuel channel 2 is arranged around the second fuel channel 3. A first fuel injection hole 6 and a second fuel injection hole 7 are opened downstream of the central bluff body 11. The first fuel injection hole 6 and the second fuel injection hole 7 are distributed along the circumferential direction of the downstream of the central bluff body 11. The first fuel injection hole 6 is located above the second fuel injection hole 7. The first fuel injection hole 6 is connected to the first fuel channel 2, and the second fuel injection hole 7 is connected to the second fuel channel 3; the swirl blade 8 connects the central blunt body 11 and the outer wall ring 4; the turbulent blunt body 9 is distributed circumferentially along the downstream of the central blunt body 11, and the turbulent blunt body 9 is located upstream of the first fuel injection hole 6; a swirl channel is formed between the outer wall ring 4, the central blunt body 11, the turbulent blunt body 9 and the swirl blade 8, and the air flows through the swirl channel to form an air swirl. The first fuel injection hole 6 and the second fuel injection hole 7 are used to inject fuel, which is mixed with the air swirl in the form of a lateral jet and burned.

[0053] According to the swirl burner of the embodiment of the present application, two sets of fuel injection systems and fuel flow paths are integrated through the first fuel channel 2 and the second fuel channel 3 and the first fuel nozzle 6 and the second fuel nozzle 7 to simultaneously meet the different requirements of the two fuels for injection performance (pressure difference). At the same time, three different flow modes of air swirl, multiple fuel lateral jets, and turbulence generated by the turbulent blunt body 9 are coupled downstream of the central blunt body 11 to enhance air-fuel mixing and make up for the disadvantage of poor mixing effect of a single lateral jet, thereby controlling local hot spots and inhibiting the generation of nitrogen oxides while ensuring efficient and stable combustion.

[0054] A central channel is formed in the middle of the outer wall ring 4 for fixing blades and for restricting airflow to guide air flow.

[0055] The central bluff body 11 is located in the central channel, and is used to strengthen the downstream backflow intensity to ensure wide-domain flame stability. The first fuel channel 2 and the second fuel channel 3 are arranged inside the central bluff body 11. The first fuel channel 2 can ensure that the fuel is uniformly ejected from the first fuel nozzle 6; the second fuel channel 3 can ensure that the fuel is uniformly ejected from the second fuel nozzle 7. The first fuel channel 2 is arranged around the second fuel channel 3, and the two are respectively used to supply fuels with different injection pressure differences. The first fuel nozzle 6 and the second fuel nozzle 7 are uniformly distributed along the circumference of the central bluff body 11, and are used to inject fuel, inject air swirl in the form of multi-point lateral jets and mix and burn, wherein the first fuel nozzle 6 is located upstream of the second fuel nozzle 7.

[0056] The swirl blades 8 connect the central bluff body 11 and the outer wall ring 4, and are used to impart a tangential velocity component to the air, thereby generating an air swirl, thereby enhancing mixing and forming a recirculation zone to stabilize the fire.

[0057] The turbulent bluff bodies 9 are distributed along the downstream circumference of the central bluff body 11 and are located upstream of the first fuel injection hole 6 to generate additional small-scale vortices. By generating small-scale vortices, the turbulence is increased to enhance the downstream mixing.

[0058] Specifically, the first fuel channel 2 may be a high fuel injection pressure difference path (low-density gaseous fuel), and the first fuel injection hole 6 may be a small-sized fuel injection hole to increase the fuel penetration depth and thus enhance air-fuel mixing.

[0059] The second fuel channel 3 can be a low fuel injection pressure difference path, and the second fuel injection hole 7 is arranged downstream of the sudden expansion of the swirl outlet, and the sudden expansion pressure drop is used to provide part of the fuel injection pressure difference. At the same time, the second fuel injection hole 7 can use a large-sized fuel injection hole array to further reduce the fuel injection pressure requirement. At this time, the efficient air-fuel mixing is achieved by the aerodynamic action of the swirl stirring effect and the blunt body turbulence.

[0060] The present design firstly uses the swirl blade 8 to generate the air swirl. The fuel enters from the inlet of the first fuel channel 2 and / or the second fuel channel 3, and is injected into the air swirl in the form of a lateral jet from the first fuel nozzle 6 and / or the second fuel nozzle 7. The first fuel nozzle 6 and the second fuel nozzle 7 can adopt a multi-point injection diffusion flame layout, and the two fuels are sprayed from the first fuel nozzle 6 and / or the second fuel nozzle 7 array.

[0061] In one embodiment, the first fuel injection hole 6 is located in the central passage, and the second fuel injection hole 7 is located downstream of an outlet of the central passage.

[0062] A plurality of small turbulent bluff bodies 9 are arranged on the central bluff body 11 upstream of the first fuel nozzle 6 to generate additional small-scale vortices to enhance downstream mixing. Under the combined effect of air swirl, fuel lateral jet and bluff body turbulence, the fuel is quickly and evenly mixed with the air along the entire cross section, thereby suppressing the generation of nitrogen oxides in the downstream flame area. Under the dual effect of swirl and central fuel cavity, a recirculation zone can be formed downstream to ensure flame stability under a wide range of working conditions.

[0063] This design can burn two different fuel gases with high and low fuel injection pressure differences at the same time, and can reduce the dependence on the injection velocity of the lateral jet of the fuel with low fuel injection pressure difference, thereby reducing the demand for fuel supply pressure. At the same time, the flame can be controlled near the shear layer in the 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 when using the premixed mode is avoided by adopting a diffusion combustion layout, thereby improving the safety of the system. The swirl burner can form an air-fuel mixing structure at the head of combustion chambers of different magnitudes in an array form, realizing efficient, stable, and low-emission combustion of a gaseous dual-fuel system with different fuel supply pressure differences.

[0064] When burning high injection pressure difference fuel, air enters from the upstream of the swirler, and the first fuel nozzle 6 enters the central blunt body 11 first fuel nozzle 6 through the first fuel channel 2 first fuel nozzle 6 and is ejected from the first fuel nozzle 6 first fuel nozzle 6; the air flow first enters the first fuel nozzle 6 of the intake annular channel 1, flows through the first fuel nozzle 6 of multiple swirl blades 8, and then enters the first fuel nozzle 6 of the outlet annular channel 5, and then passes through the first fuel nozzle 6 of the turbulent blunt body 9, and finally flows out from the first fuel nozzle 6 of the outlet annular channel 5 and mixes with the first fuel nozzle 6.

[0065] When burning low injection pressure difference fuel, low oxygen air (SOFC cathode tail gas) enters from the upstream of the swirler, and the low injection pressure difference fuel enters the first fuel nozzle 6 of the central blunt body 11 through the first fuel nozzle 6 of the second fuel channel 3, and is ejected from the first fuel nozzle 6 of the second fuel nozzle 7; the low oxygen air flow first enters the first fuel nozzle 6 of the intake annular channel 1, flows through the first fuel nozzle 6 of multiple swirl blades 8, and then enters the first fuel nozzle 6 of the outlet annular channel 5, and then passes through the first fuel nozzle 6 of the turbulent blunt body 9, and finally flows out from the first fuel nozzle 6 of the outlet annular channel 5 to mix with the low injection pressure difference fuel.

[0066] It should be noted that different swirl burner structures can be provided according to the outer wall ring 4, the number and twist of the swirler blades, the size of the central bluff body 11, the position and size of the fuel nozzles, the form of the fuel channel, the bluff body geometry, the anti-vibration stack 10 geometry, and the head unit arrangement form and spacing.

[0067] According to one embodiment of the present application, the first fuel channel 2 is an annular channel, and the annular channel is arranged around the second fuel channel 3. The annular channel can be used as an independent fuel supply channel, which can more effectively utilize the space inside the burner and make the structure of the entire burner more compact.

[0068] According to an embodiment of the present application, the first fuel injection holes 6 and the second fuel injection holes 7 are staggeredly distributed circumferentially on the central bluff body 11. The first fuel injection holes 6 and the second fuel injection holes 7 are staggeredly distributed to form a more complex flame structure of multi-point injection, which helps to improve the mixing effect of fuel and air.

[0069] According to one embodiment of the present application, the swirl channel includes an inlet annular channel 1 and an outlet annular channel 5. The inlet annular channel 1 is connected to the outlet annular channel 5. The inlet annular channel 1 is located on the first side of the hollow swirl blade 8, and the outlet annular channel 5 is located on the second side of the hollow swirl blade 8. The opening of the outlet annular channel 5 gradually decreases along the flow direction of the air to form a tapered channel.

[0070] It can be understood that the air inlet annular channel 1 is located on the first side (such as the upstream side) of the hollow swirl blade 8, and the air outlet annular channel 5 is located on the second side (such as the downstream side) of the hollow swirl blade 8. The air inlet annular channel 1 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 5 serves as the air outlet, and a tapered channel is formed by the central bluff body 11 and the outer wall ring 4. The tapered channel helps to guide the air swirl and enhance the swirl effect, thereby further promoting the mixing of fuel and air.

[0071] According to one embodiment of the present application, the swirl burner includes a plurality of vibration-proof stacks 10, which are connected to the outer wall ring 4, are located at the outlet of the swirl burner, and are arranged circumferentially along the outer wall ring 4. It can be understood that the vibration-proof stacks 10 play a role in reducing the volume of the corner vortex area and adjusting the velocity distribution at the swirler outlet, thereby achieving the purpose of preventing combustion oscillation.

[0072] In one embodiment, the vibration isolation stacks 10 are arranged at four corners of the outer wall ring 4 along the circumferential direction.

[0073] In one embodiment, please refer to Figures 1 to 8 The vibration-proof stack 10 is a triangular pyramid structure, and the length w1 of the first edge length, the length w2 of the second edge length, and the length w3 of the third edge length of the vibration-proof stack 10 are all in the range of 4 mm to 16 mm.

[0074] According to an embodiment of the present application, please refer to Figures 9 to 14 The outer contour of the outer wall ring 4 is one of a hexagon, a pentagon, a rectangle, a square, a triangle, and a circle.

[0075] In one embodiment, the outer contour of the outer wall ring 4 is a square, the height H of the outer wall ring 4 ranges from 15 mm to 60 mm; the thickness L of the outer wall ring 4 ranges from 10 mm to 60 mm; the inlet inner diameter D of the outer wall ring 4 iiThe range is 10mm~55mm; the outlet inner diameter D of the outer wall ring 4 eo The range is 8mm~53mm.

[0076] According to an embodiment of the present application, the hollow swirl blade 8 is one of a twisted blade, a non-twisted blade, a curved blade, and a straight blade.

[0077] In one embodiment, the hollow swirl blade 8 is a non-twisted blade, the blade inclination angle α of the hollow swirl blade 8 ranges from 20° to 70°; the blade length L of the hollow swirl blade 8 ranges from 5 mm to 25 mm; the number of blades n of the hollow swirl blade 8 is A 4 to 16 pieces.

[0078] According to one embodiment of the present application, the outer diameter D of the central bluff body 11 ranges from 5 mm to 55 mm.

[0079] According to an embodiment of the present application, please refer to Figures 15 to 20 The first 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.

[0080] In one embodiment, the number n of the first fuel injection holes 6 is h The range is 2 to 30, the first fuel injection hole 6 has a diameter d h The range is 0.1mm~2.5mm, and the distance h1 between the plane where the first fuel injection hole 6 is located and the end surface of the outer wall ring 4 is in the range of 0mm~6mm; According to an embodiment of the present application, please refer to Figures 15 to 20 The second fuel injection hole 7 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.

[0081] In one embodiment, the number range n of the second fuel injection holes 7 is l The number of the second fuel injection holes 7 is 2 to 30. l The range is 0.5 mm to 4 mm, and the distance h2 between the plane where the second fuel injection hole 7 is located and the end surface of the outer wall ring 4 is 0 mm to 6 mm.

[0082] According to an embodiment of the present application, please refer to Figure 21 to Figure 25 The outer contour of the spoiler 9 is one of a pyramid type, a cylinder type, a cone type, a rectangular parallelepiped type, and a blade type.

[0083] In one embodiment, the outer contour of the spoiler bluff body 9 is a triangular pyramid, the width w of the spoiler bluff body 9 is in the range of 0.5 mm to 10 mm, the inclination angle β of the spoiler bluff body 9 is in the range of 5° to 80°, the height h of the spoiler bluff body 9 is in the range of 0.8 mm to 20 mm, and the distance l between the installation position of the spoiler bluff body 9 and the end face of the outer wall ring 4 is in the range of 0 to 5 mm.

[0084] 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 (4), wherein a central channel is formed in the middle of the outer wall ring (4); A central bluff body (11) is located in the central channel, a first fuel channel (2) and a second fuel channel (3) are provided inside the central bluff body (11), the first fuel channel (2) is arranged around the second fuel channel (3), a first fuel injection hole (6) and a second fuel injection hole (7) are opened downstream of the central bluff body (11), the first fuel injection hole (6) and the second fuel injection hole (7) are distributed along the downstream circumference of the central bluff body (11), the first fuel injection hole (6) is located upstream of the second fuel injection hole (7), the first fuel injection hole (6) is connected to the first fuel channel (2), and the second fuel injection hole (7) is connected to the second fuel channel (3); A plurality of swirl blades (8) connecting the central bluff body (11) and the outer wall ring (4); A turbulent bluff body (9) is distributed circumferentially downstream of the central bluff body (11), and the turbulent bluff body (9) is located upstream of the first fuel injection hole (6); A swirl channel is formed between the outer wall ring (4), the central blunt body (11), the turbulent blunt body (9) and the swirl blade (8), and air flows through the swirl channel to form an air swirl. The first fuel injection hole (6) and the second fuel injection hole (7) are used to inject fuel to mix with the air swirl in a transverse jet manner for combustion; An anti-vibration stack (10), the anti-vibration stack (10) being connected to the outer wall ring (4), the anti-vibration stack (10) being located at the outlet of the swirl burner, and the anti-vibration stack (10) being arranged along the circumference of the outer wall ring (4).

2. The swirl burner according to claim 1, characterized in that: The first fuel channel (2) is an annular channel, and the annular channel is arranged in an annular manner around the second fuel channel (3).

3. The swirl burner according to claim 1, characterized in that: The first fuel injection holes (6) and the second fuel injection holes (7) are staggeredly distributed in the circumferential direction of the central bluff body (11).

4. The swirl burner according to claim 1, characterized in that: The swirl channel comprises an air inlet annular channel (1) and an air outlet annular channel (5), the air inlet annular channel (1) being connected to the air outlet annular channel (5), the air inlet annular channel (1) being located on a first side of the hollow swirl blade (8), the air outlet annular channel (5) being located on a second side of the hollow swirl blade (8), and the opening of the air outlet annular channel (5) gradually decreases along the flow direction of the air to form a tapered channel.

5. The swirl burner according to any one of claims 1 to 4, characterized in that: The outer contour of the outer wall ring (4) 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 (4) is a square, the height H of the outer wall ring (4) is in the range of 15 mm to 60 mm; the thickness L of the outer wall ring (4) is in the range of 10 mm to 60 mm; the inlet inner diameter D of the outer wall ring (4) is ii The range is 10 mm to 55 mm; the outlet inner diameter D of the outer wall ring (4) eo The range is 8mm~53mm.

6. The swirl burner according to any one of claims 1 to 4, characterized in that: The hollow swirl blade (8) is one of a twisted blade, a non-twisted blade, a curved blade, and a straight blade. When the hollow swirl blade (8) is a non-twisted blade, the blade inclination angle α of the hollow swirl blade (8) is in the range of 20° to 70°; the blade length L of the hollow swirl blade (8) is in the range of 5 mm to 25 mm; the number n of blades of the hollow swirl blade (8) is A 4 to 16 pieces.

7. The swirl burner according to any one of claims 1 to 4, characterized in that: The outer diameter D of the central bluff body (11) ranges from 5 mm to 55 mm.

8. The swirl burner according to any one of claims 1 to 4, characterized in that: The first 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 first fuel spray holes (6) is h The range is 2 to 30, and the diameter d of the first fuel injection hole (6) is h The range is 0.1 mm to 2.5 mm, and the distance h1 between the plane where the first fuel injection hole (6) is located and the end surface of the outer wall ring (4) is in the range of 0 mm to 6 mm.

9. The swirl burner according to any one of claims 1 to 4, characterized in that: The second fuel spray hole (7) 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 range of the second fuel spray holes (7) is n. l The number of the second fuel injection holes (7) is 2 to 30, and the diameter d of the second fuel injection holes (7) is l The range is 0.5 mm to 4 mm, and the distance h2 between the plane where the second fuel injection hole (7) is located and the end surface of the outer wall ring (4) is 0 mm to 6 mm.

10. The swirl burner according to any one of claims 1 to 4, characterized in that: The outer contour of the spoiler (9) is one of a pyramidal shape, a cylindrical shape, a conical shape, a rectangular shape, and a blade shape. When the outer contour of the spoiler (9) is a triangular pyramid shape, the width w of the spoiler (9) is in the range of 0.5 mm to 10 mm, the inclination angle β of the spoiler (9) is in the range of 5° to 80°, the height h of the spoiler (9) is in the range of 0.8 mm to 20 mm, and the distance l between the installation position of the spoiler (9) and the end face of the outer wall ring (4) is in the range of 0 to 5 mm.

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