Swirl burner

Abstract

The present application relates to the technical field of fuel injection, and provides a swirl burner. The swirl burner comprises an outer wall ring, a central bluff body, a plurality of swirl vanes, a spoiler bluff body and a vibration-proof stack. A central passage is formed in the middle of the outer wall ring. The central bluff body is located in the central passage. The central bluff body is internally provided with a first fuel passage and a second fuel passage. A first fuel injection hole communicating with the first fuel passage and a second fuel injection hole communicating with the second fuel passage are formed in the downstream of the central bluff body. The swirl vanes are connected to the central bluff body and the outer wall ring. The spoiler bluff body is distributed along the downstream circumference of the central bluff body and is located upstream of the first fuel injection hole. The swirl passage is formed among the outer wall ring, the central bluff body, the spoiler bluff body and the swirl vanes. Air flows through the swirl passage to form air swirl. The first fuel injection hole and the second fuel injection hole are used for injecting fuel to be mixed and combusted with the air swirl in the form of a transverse jet. The vibration-proof stack is connected to the outer wall ring and is located at the outlet of the swirl burner and is arranged along the circumference of the outer wall ring.

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 to work, avoiding waste of fuel and fuel cell reaction waste heat. This combined cycle process is expected to increase the overall thermal efficiency of the corresponding power plant to 60-70%, which is a very promising future zero-carbon aviation power technology.

[0004] Due to the fact that the dynamic response performance of the current SOFC does not meet the requirements of stable operation under all operating conditions, the current SOFC-GT combined cycle architecture adopts two operating modes. In take-off, climb, approach, slow vehicle and other operating conditions, the SOFC bears a large operating condition change rate, so the SOFC is not started, and the GT mode is used at this time. The combustion chamber uses hydrogen as fuel. In the cruising condition, the operating condition change rate is very small, the SOFC is started to generate electricity, and the combustion chamber uses anode tail gas as fuel. Therefore, the combustion chamber head nozzle suitable for the SOFC-GT combined cycle system needs to have the ability to consider the high-efficiency and stable combustion of dual-mode and dual-fuel.

[0005] However, under the above dual-mode and dual-fuel system background, the injection and mixing of the fuel still faces several challenges. In the existing traditional combustion chamber head nozzle, the maximum supply pressure of the fuel is often significantly higher than the inlet air pressure of the combustion chamber, but in the scenario of using anode tail gas of the fuel cell as 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 increasing nitrogen oxide emissions.

[0006] When pure hydrogen is used as fuel, the low density of hydrogen results in low momentum of hydrogen jet, which makes the hydrogen jet easy to be carried away by air, and difficult to form ideal fuel jet penetration and dispersion, thereby affecting air-fuel mixing effect. The SOFC-GT combined cycle combustor needs to meet the requirements of high efficiency, stability and low emission combustion when using hydrogen or low heat value anode tail gas as fuel, which brings great challenges to the design of the mixing unit at the head of the combustor. Therefore, it is urgent to develop a combustor head nozzle suitable for SOFC-GT combined cycle system, which needs to have high efficient and stable combustion for dual-mode and dual-fuel. SUMMARY

[0007] The present application aims to at least solve one of the technical problems in the related art. To this end, the present application provides a swirl burner which can simultaneously consider the high efficient air-fuel mixing of gaseous dual fuel with different pressure differences of two fuel supplies.

[0008] The swirl burner according to the embodiments of the present application comprises:

[0009] An outer wall ring, a central passage is formed in the middle of the outer wall ring;

[0010] A central bluff body is located in the central passage, the central bluff body is internally provided with a first fuel passage and a second fuel passage, the first fuel passage is arranged around the second fuel passage, 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 passage, and the second fuel injection hole is connected to the second fuel passage;

[0011] A plurality of swirl vanes are connected to the central bluff body and the outer wall ring;

[0012] A spoiler bluff body is distributed along the downstream circumference of the central bluff body, and the spoiler bluff body is located upstream of the first fuel injection hole;

[0013] A swirl passage is formed between the outer wall ring, the central bluff body, the spoiler bluff body and the swirl vanes, air flows through the swirl passage to form air swirl, and the first fuel injection hole and the second fuel injection hole are used for injecting fuel to mix and burn with air swirl in the form of transverse jet;

[0014] A vibration isolation stack is connected to the outer wall ring, and the vibration isolation stack is located at the outlet of the swirl burner and is arranged along the circumference of the outer wall ring.

[0015] According to the swirl burner, 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 injection hole and the second fuel injection hole to simultaneously meet different requirements of two fuel paths on injection performance (pressure difference), and three different flow modes of air swirl, multiple fuel transverse jets and turbulence generated by turbulence bodies downstream of the central body are coupled to strengthen air-fuel mixing and make up for the poor mixing effect of single transverse jet, so that local hot spots are controlled and generation of nitrogen oxides is inhibited under the premise of ensuring efficient and stable combustion.

[0016] According to one embodiment of the present application, the first fuel channel is an annular channel, and the annular channel is annularly arranged around the second fuel channel.

[0017] According to one embodiment of the present application, the first fuel injection hole and the second fuel injection hole are circumferentially staggered around the central body.

[0018] According to one embodiment of the present application, the swirl channel includes an air inlet annular channel and an air outlet annular channel, the air inlet annular channel is communicated with the air outlet annular channel, the air inlet annular channel is located on the first side of the hollow swirl vane, the air outlet annular channel is located on the second side of the hollow swirl vane, and the outlet of the air outlet annular channel gradually decreases to form a tapered channel along the flow direction of air.

[0019] 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 that 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 ii of the outer wall ring ranges from 10 mm to 55 mm, and the outlet inner diameter D eo of the outer wall ring ranges from 8 mm to 53 mm.

[0020] 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 that the hollow swirl vane is a non-twisted vane, the vane inclination angle α 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.

[0021] According to one embodiment of the present application, the outer diameter D of the central body ranges from 5 mm to 55 mm.

[0022] According to one embodiment of the present application, the first 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 of the first fuel injection holes n h ranges from 2 to 30, the diameter d h of the first fuel injection hole ranges from 0.1 mm to 2.5 mm, and the distance h1 between the plane where the first fuel injection hole is located and the end surface of the outer wall ring ranges from 0 mm to 6 mm.

[0023] and / or,

[0024] The second 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 of the second fuel injection holes n l ranges from 2 to 30, the diameter d l of the second fuel injection hole ranges from 0.5 mm to 4 mm, and the distance h2 between the plane where the second fuel injection hole is located and the end surface of the outer wall ring ranges from 0 mm to 6 mm.

[0025] According to one embodiment of the present application, the outer contour of the spoiler is one of a pyramid, a cylinder, a cone, a cuboid, and a blade, in the case where the outer contour of the spoiler is a triangular pyramid, the width w of the spoiler ranges from 0.5 mm to 10 mm, the inclination angle β of the spoiler ranges from 5° to 80°, the height h of the spoiler ranges from 0.8 mm to 20 mm, and the distance l between the mounting position of the spoiler and the end surface of the outer wall ring ranges from 0 to 5 mm.

[0026] Additional aspects and advantages of the present application will be given, partially in the following description, partially become obvious from the following description, or be learned by practice of the present application. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to more clearly illustrate the technical solutions of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without any creative effort on the basis of these drawings.

[0028] Figure 1 is a cross-sectional axial side structure schematic diagram of a cyclone combustor provided by an embodiment of the present application.

[0029] Figure 2 is a structure schematic diagram of a cyclone combustor provided by an embodiment of the present application.

[0030] Figure 3is a size schematic view of a cyclone combustor provided by an embodiment of the present application.

[0031] Figure 4 is Figure 3 is a schematic view of an A-direction cross-sectional structure of a cyclone combustor provided by an embodiment.

[0032] Figure 5 is Figure 4 is a schematic view of a partial enlarged structure of a cyclone combustor provided by an embodiment.

[0033] Figure 6 is a schematic view of a hollow cyclone vane provided by an embodiment of the present application.

[0034] Figure 7 is a schematic view of a spoiler bluff body provided by an embodiment of the present application.

[0035] Figure 8 is a size schematic view of a spoiler bluff body provided by an embodiment of the present application.

[0036] Figure 9 is a schematic view of an outer wall ring with a hexagonal outer contour shape provided by an embodiment of the present application.

[0037] Figure 10 is a schematic view of an outer wall ring with a pentagonal outer contour shape provided by an embodiment of the present application.

[0038] Figure 11 is a schematic view of an outer wall ring with a square outer contour shape provided by an embodiment of the present application.

[0039] Figure 12 is a schematic view of an outer wall ring with a rectangular outer contour shape provided by an embodiment of the present application.

[0040] Figure 13 is a schematic view of an outer wall ring with a triangular outer contour shape provided by an embodiment of the present application.

[0041] Figure 14 is a schematic view of an outer wall ring with a circular outer contour shape provided by an embodiment of the present application.

[0042] Figure 15 is one of schematic views of a first fuel injection hole and / or a second fuel injection hole with a rounded rectangular shape provided by an embodiment of the present application.

[0043] Figure 16 is a schematic view of a first fuel injection hole and / or a second fuel injection hole with an elliptical shape provided by an embodiment of the present application.

[0044] Figure 17 is a schematic view of a first fuel injection hole and / or a second fuel injection hole with a circular shape provided by an embodiment of the present application.

[0045] Figure 18 is a structure schematic diagram of the first fuel injection hole and / or the second fuel injection hole provided by the embodiment of the present application, which is a triangle.

[0046] Figure 19 is a structure schematic diagram of the first fuel injection hole and / or the second fuel injection hole provided by the embodiment of the present application, which is a quadrilateral.

[0047] Figure 20 is a structure schematic diagram of the first fuel injection hole and / or the second fuel injection hole provided by the embodiment of the present application, which is a round rectangle.

[0048] Figure 21 is a structure schematic diagram of the spoiler provided by the embodiment of the present application, which is a triangular pyramid.

[0049] Figure 22 is a structure schematic diagram of the spoiler provided by the embodiment of the present application, which is a cylinder.

[0050] Figure 23 is a structure schematic diagram of the spoiler provided by the embodiment of the present application, which is a cone.

[0051] Figure 24 is a structure schematic diagram of the spoiler provided by the embodiment of the present application, which is a cuboid.

[0052] Figures 1-25 is a structure schematic diagram of the spoiler provided by the embodiment of the present application, which is a blade type.

[0053] Reference signs:

[0054] 1, inlet annular channel; 2, first fuel channel; 3, second fuel channel; 4, outer wall ring; 5, outlet annular channel; 6, first fuel injection hole; 7, second fuel injection hole; 8, swirl vane; 9, spoiler; 10, anti-vibration stack; 11, central body. DETAILED DESCRIPTION

[0055] The embodiments of the present application will be further described in detail below with reference to the accompanying drawings and embodiments. The following embodiments are used to illustrate the present application, but cannot be used to limit the scope of the present application.

[0056] In the description of the embodiments of the present application, it should be noted that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and 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 devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on 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.

[0057] In the description of the embodiments of the present application, unless otherwise explicitly specified and limited, the terms "connected", "connected" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, wherein the fixedly connected can include the way of integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0058] In the embodiments of the present application, unless otherwise explicitly specified and limited, the first feature is "on" or "under" the second feature, which 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 "above", "above" and "above" the second feature can be that the first feature is directly above or obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature "below", "below" and "below" the second feature can be that the first feature is directly below or obliquely below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0059] 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 conjunction 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 one or more embodiments or examples in a suitable manner. 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.

[0060] The following will be described in conjunction with Figure 1 The present application describes a cyclone burner.

[0061] According to the swirling combustor provided by the embodiment of the present application, refer to Figure 2 and Figures 1 to 8 The swirling combustor comprises an outer wall ring 4, a central bluff body 11, a plurality of swirling vanes 8 and a spoiler bluff body 9. The central passage is formed in the middle of the outer wall ring 4. The central bluff body 11 is located in the central passage. The first fuel passage 2 and the second fuel passage 3 are arranged inside the central bluff body 11. The first fuel passage 2 is arranged around the second fuel passage 3. The first fuel injection hole 6 and the second fuel injection hole 7 are arranged downstream of the central bluff body 11. The first fuel injection hole 6 and the second fuel injection hole 7 are distributed along the circumference of the downstream 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 with the first fuel passage 2. The second fuel injection hole 7 is connected with the second fuel passage 3. The swirling vane 8 is connected with the central bluff body 11 and the outer wall ring 4. The spoiler bluff body 9 is distributed along the circumference of the downstream of the central bluff body 11. The spoiler bluff body 9 is located upstream of the first fuel injection hole 6. The swirling passage is formed between the outer wall ring 4, the central bluff body 11, the spoiler bluff body 9 and the swirling vane 8. The air flows through the swirling passage to form the air swirl. The first fuel injection hole 6 and the second fuel injection hole 7 are used for injecting fuel to mix and burn with the air swirl in the form of transverse jet.

[0062] According to the swirling combustor provided by the embodiment of the present application, two sets of fuel injection systems and fuel flow paths are integrated through the first fuel passage 2 and the second fuel passage 3 and the first fuel injection hole 6 and the second fuel injection hole 7 to simultaneously meet the different requirements of two fuel injection performances (pressure difference). Meanwhile, the air swirl, the multiple fuel transverse jets and the spoiler bluff body 9 are coupled downstream of the central bluff body 11 to generate the disturbance flow to strengthen the air-fuel mixing, make up for the disadvantage of the single transverse jet mixing effect and control the local hot spot and inhibit the generation of nitrogen oxide under the premise of ensuring the high-efficiency and stable combustion.

[0063] The central passage is formed in the middle of the outer wall ring 4 to fix the vane and to constrain the air flow to guide the air flow.

[0064] The central bluff body 11 is located in the central passage to strengthen the downstream backflow intensity to ensure the wide-range flame stability. The first fuel passage 2 and the second fuel passage 3 are arranged inside the central bluff body 11. The first fuel passage 2 can ensure that the fuel is uniformly injected from the first fuel injection hole 6. The second fuel passage 3 can ensure that the fuel is uniformly injected from the second fuel injection hole 7. The first fuel passage 2 is arranged around the second fuel passage 3. The two are respectively used for supplying the fuel with different injection pressure differences. The first fuel injection hole 6 and the second fuel injection hole 7 are uniformly distributed along the circumference of the central bluff body 11 to inject fuel in the form of multiple-point transverse jet to inject the air swirl and mix and burn. The first fuel injection hole 6 is located upstream of the second fuel injection hole 7.

[0065] The swirl vanes 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 flow, thereby generating an air swirl, and to strengthen the mixing and form a recirculation zone to stabilize the flame.

[0066] The spoiler bluff bodies 9 are distributed circumferentially downstream of the central bluff body 11 and upstream of the first fuel injection holes 6, and are used to generate additional small-scale vortices to enhance the downstream mixing by increasing the turbulence intensity.

[0067] Specifically, the first fuel passage 2 can be a high fuel injection pressure difference path (low density gaseous fuel), and the first fuel injection holes 6 can be small-sized fuel injection holes to increase the fuel penetration depth and enhance the air-fuel mixing.

[0068] The second fuel passage 3 can be a low fuel injection pressure difference path, and the second fuel injection holes 7 are arranged downstream of the swirl outlet expansion, and utilize the expansion pressure drop to provide part of the fuel injection pressure difference, while the second fuel injection holes 7 can be large-sized fuel injection hole arrays to further reduce the fuel injection pressure requirement. The high-efficiency air-fuel mixing at this time is achieved by the swirl stirring action and the aerodynamic action of the bluff body spoiler.

[0069] The design first utilizes the swirl vanes 8 to generate an air swirl. Fuel enters from the inlet of the first fuel passage 2 and / or the second fuel passage 3, and is injected into the air swirl in the form of a transverse jet from the first fuel injection holes 6 and / or the second fuel injection holes 7. The first fuel injection holes 6 and the second fuel injection holes 7 can adopt a multi-point injection diffusion flame layout, and the two fuels are injected by the first fuel injection hole 6 and / or the second fuel injection hole 7 array.

[0070] In one embodiment, the first fuel injection holes 6 are located in the central passage, and the second fuel injection holes 7 are located downstream of the central passage outlet.

[0071] A plurality of small spoiler bluff bodies 9 are arranged on the central bluff body 11 upstream of the first fuel injection holes 6 to generate additional small-scale vortices to enhance the downstream mixing. Under the combined action of the air swirl, the fuel transverse jet, and the bluff body spoiler, the fuel is rapidly and uniformly mixed with the air throughout the cross section, thereby suppressing the formation of nitrogen oxides in the downstream flame region. Under the dual action of the swirl and the central fuel cavity, a recirculation zone can be formed downstream to ensure the flame stability under wide-range operating conditions.

[0072] The design can simultaneously burn two different fuels with high and low fuel injection pressure differences, and can reduce the dependence on the low fuel injection pressure difference fuel transverse jet injection speed, thereby reducing the demand for fuel supply pressure. At the same time, it can also control the flame near the shear layer within the swirl, preventing combustion oscillation and excessive nitrogen oxide emission that may be caused by the corner vortex zone combustion. In addition, by adopting a diffusion combustion layout, the risk of spontaneous backfire of fuel in premixed mode is avoided, improving the safety of the system. The swirl burner can be arrayed to form a head air-fuel mixing structure of a combustion chamber of different magnitudes, realizing efficient, stable and low-emission combustion of gaseous dual-fuel systems with different fuel supply pressure differences.

[0073] When burning high injection pressure difference fuel, air enters from upstream of the swirler, the first fuel injection hole 6 enters the central bluff body 11 through the first fuel channel 2 and is injected from the first fuel injection hole 6; the air flow first enters the inlet annular channel 1, passes through the plurality of swirl vanes 8, enters the outlet annular channel 5, and finally flows out of the outlet annular channel 5 after passing through the spoiler bluff body 9, and is mixed with the first fuel injection hole 6.

[0074] When burning low injection pressure difference fuel, low-oxygen air (SOFC cathode tail gas) enters from upstream of the swirler, and low injection pressure difference fuel enters the central bluff body 11 through the second fuel channel 3 and is injected from the second fuel injection hole 7; the low-oxygen air flow first enters the inlet annular channel 1, passes through the plurality of swirl vanes 8, enters the outlet annular channel 5, and finally flows out of the outlet annular channel 5 after passing through the spoiler bluff body 9, and is mixed with the low injection pressure difference fuel.

[0075] It should be noted that according to the outer wall ring 4, the number and twist of the swirler vanes, the size of the central bluff body 11, the position and size of the fuel injection hole, the form of the fuel channel, the bluff body geometry, the anti-vibration pile 10 geometry, and the head unit arrangement form and spacing, there are different structures of the swirl burner.

[0076] According to one embodiment of the present application, the first fuel channel 2 is an annular channel, and the annular channel is annularly 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, making the structure of the entire burner more compact.

[0077] According to one embodiment of the present application, the first fuel injection hole 6 and the second fuel injection hole 7 are circumferentially staggered on the central bluff body 11. The staggered distribution of the first fuel injection hole 6 and the second fuel injection hole 7 forms a more complex multi-point injection flame structure, which helps to improve the mixing effect of fuel and air.

[0078] According to one embodiment of the present application, the cyclone passage comprises an air inlet annular passage 1 and an air outlet annular passage 5, the air inlet annular passage 1 is connected to the air outlet annular passage 5, the air inlet annular passage 1 is located at the first side of the hollow cyclone vane 8, and the air outlet annular passage 5 is located at the second side of the hollow cyclone vane, and the air outlet annular passage 5 is gradually reduced in opening along the flow direction of the air to form a converging passage.

[0079] It can be understood that the air inlet annular passage 1 is located at the first side (such as the upstream side) of the hollow cyclone vane, and the air outlet annular passage 5 is located at the second side (such as the downstream side) of the hollow cyclone vane, the air inlet annular passage 1 serves as the air inlet and is responsible for introducing the external air into the interior of the cyclone. The design should ensure that the air can enter the cyclone uniformly and smoothly, and provide sufficient oxygen for the subsequent cyclone generation and fuel mixing. The air outlet annular passage 5 serves as the air outlet and forms a converging passage with the central bluff body 11 and the outer wall ring 4. The converging passage helps to guide the air cyclone and enhances the cyclone effect, thereby further promoting the mixing of the fuel and the air.

[0080] According to one embodiment of the present application, the cyclone burner comprises a plurality of anti-vibration stacks 10, the anti-vibration stacks 10 are connected to the outer wall ring 4, the anti-vibration stacks 10 are located at the outlet of the cyclone burner, and the anti-vibration stacks 10 are arranged circumferentially along the outer wall ring 4. It can be understood that the anti-vibration stacks 10 play a role in reducing the volume of the corner vortex region and adjusting the outlet velocity distribution of the cyclone, thereby achieving the purpose of preventing combustion oscillation.

[0081] In one embodiment, the anti-vibration stacks 10 are arranged at four corners of the outer wall ring 4 in the circumferential direction.

[0082] In one embodiment, please refer to Figures 9 to 14 , the anti-vibration stacks 10 are in the shape of a triangular pyramid, and the length w1 of the first edge, the length w2 of the second edge, and the length w3 of the third edge of the anti-vibration stacks 10 are all in the range of 4mm to 16mm.

[0083] According to one embodiment of the present application, please refer to Figures 15 to 20 , 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.

[0084] In one embodiment, 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 15mm to 60mm, the thickness L of the outer wall ring 4 is in the range of 10mm to 60mm, the inlet inner diameter D ii of the outer wall ring 4 is in the range of 10mm to 55mm, and the outlet inner diameter D eo of the outer wall ring 4 is in the range of 8mm to 53mm.

[0085] According to one embodiment of the present application, the hollow cyclone vane is one of a twisted vane, a non-twisted vane, a curved vane, and a straight vane.

[0086] In one embodiment, the hollow swirl vane is a non-twisted vane, the blade angle a of the hollow swirl vane ranges from 20° to 70°, the blade length L of the hollow swirl vane ranges from 5 mm to 25 mm, and the number n of the hollow swirl vanes is 4 to 16. A h h

[0087] 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.

[0088] According to one embodiment of the present application, please refer to Figures 15 to 20 , the first fuel injection hole 6 is one of a circular hole, an elliptical hole, an arcuate hole, a rounded rectangular hole, and a triangular hole.

[0089] In one embodiment, the number n of the first fuel injection hole 6 ranges from 2 to 30, the diameter d of the first fuel injection hole 6 ranges from 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 ranges from 0 mm to 6 mm. h h

[0090] According to one embodiment of the present application, please refer to Figures 21 to 25 , the second fuel injection hole 7 is one of a circular hole, an elliptical hole, an arcuate hole, a rounded rectangular hole, and a triangular hole.

[0091] In one embodiment, the number n of the second fuel injection hole 7 ranges from 2 to 30, the diameter d of the second fuel injection hole 7 ranges from 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 ranges from 0 mm to 6 mm. l l

[0092] According to one embodiment of the present application, please refer to ​ , the outer contour of the spoiler bluff body 9 is one of a pyramid, a cylinder, a cone, a cuboid, and a blade.

[0093] 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 ranges from 0.5 mm to 10 mm, the inclination angle β of the spoiler bluff body 9 ranges from 5° to 80°, the height h of the spoiler bluff body 9 ranges from 0.8 mm to 20 mm, and the distance l between the mounting position of the spoiler bluff body 9 and the end surface of the outer wall ring 4 ranges from 0 to 5 mm.

[0094] ​​​It should be pointed out finally that the above embodiments are only used to illustrate the technical solutions of the present application, but not to limit the same; and although the present application has been described in detail with reference to the foregoing embodiments, it should be appreciated by those skilled in the art that the technical solutions recorded in the foregoing embodiments can be modified, or some technical features thereof can be replaced equivalently; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A swirl burner, characterized by The application relates to a rotating flow combustor, which comprises the following parts: an outer wall ring (4) with a central passage formed in the middle part; a central blunt body (11) located in the central passage, wherein the inside of the central blunt body (11) is provided with a first fuel passage (2) and a second fuel passage (3), the first fuel passage (2) is arranged around the second fuel passage (3), the downstream of the central blunt body (11) is provided with a first fuel injection hole (6) and a second fuel injection hole (7), the first fuel injection hole (6) and the second fuel injection hole (7) are distributed along the downstream circumference of the central blunt 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 with the first fuel passage (2), and the second fuel injection hole (7) is connected with the second fuel passage (3); a plurality of rotating flow vanes (8) connecting the central blunt body (11) and the outer wall ring (4); a spoiler blunt body (9) distributed along the downstream circumference of the central blunt body (11), wherein the spoiler blunt body (9) is located upstream of the first fuel injection hole (6); a rotating flow passage is formed between the outer wall ring (4), the central blunt body (11), the spoiler blunt body (9) and the rotating flow vane (8), air flows through the rotating flow passage to form air rotating flow, the first fuel injection hole (6) and the second fuel injection hole (7) are used for injecting fuel to mix with the air rotating flow in the form of a transverse jet flow and combust; a vibration-proof stack (10) connected with the outer wall ring (4), wherein the vibration-proof stack (10) is located at the outlet of the rotating flow combustor and is arranged along the circumference of the outer wall ring (4); the first fuel injection hole (6) and the second fuel injection hole (7) are distributed along the circumference of the central blunt body (11) in a staggered mode; the rotating flow passage comprises an air inlet annular passage (1) and an air outlet annular passage (5), the air inlet annular passage (1) is connected with the air outlet annular passage (5), the rotating flow vane (8) is a hollow rotating flow vane, the air inlet annular passage (1) is located on the first side of the hollow rotating flow vane, the air outlet annular passage (5) is located on the second side of the hollow rotating flow vane, and the opening of the air outlet annular passage (5) gradually decreases along the flow direction of air to form a tapered passage; the vibration-proof stack (10) is a three-prism structure, and the length w1 of the first prism, the length w2 of the second prism and the length w3 of the third prism of the vibration-proof stack (10) are all in the range of 4mm-16mm.

2. The swirl burner of claim 1, wherein the first fuel passage (2) is an annular passage, and the annular passage is arranged around the second fuel passage (3).

3. The swirl burner according to any one of claims 1 to 2, characterized in that The outer contour of the outer wall ring (4) is one of hexagon, pentagon, rectangle, square, triangle and circle. In the case that the outer contour of the outer wall ring (4) is 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 ii of the outer wall ring (4) ranges from 10 mm to 55 mm; and the outlet inner diameter D eo of the outer wall ring (4) ranges from 8 mm to 53 mm.

4. The swirl burner according to any one of claims 1 to 2, characterized in that The hollow cyclone vane is one of twisted vane, non-twisted vane, curved vane and straight vane, and the vane rake angle α of the hollow cyclone vane ranges from 20° to 70° when the hollow cyclone vane is a non-twisted vane; the vane length L of the hollow cyclone vane ranges from 5mm to 25mm; and the number n of the hollow cyclone vanes is 4 to 16. A 4 to 16.

5. The swirl burner according to any one of claims 1 to 2, characterized in that the outer diameter D of the central blunt body (11) is in the range of 5mm-55mm.

6. The swirl burner of any one of claims 1 to 2, wherein, The first fuel nozzle (6) is one of the following: a circular nozzle, an elliptical nozzle, an arched nozzle, a rounded rectangular nozzle, or a triangular nozzle. The number of the first fuel nozzles (6) is n. h The range is 2 to 30, and the diameter d of the first fuel injection hole (6) is... h The range is 0.1mm to 2.5mm, and the distance h1 between the plane where the first fuel injection hole (6) is located and the end face of the outer wall ring (4) is 0mm to 6mm.

7. The swirl burner of any one of claims 1 to 2, wherein, The second fuel injection hole (7) 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 second fuel injection holes (7) ranges from 2 to 30, the diameter d of the second fuel injection hole (7) ranges from 0.5 mm to 4 mm, and the distance h2 between the plane in which the second fuel injection hole (7) is located and the end surface of the outer wall ring (4) ranges from 0 mm to 6 mm. l is 2~30, the diameter d l of the second fuel injection hole (7) ranges from 0.5 mm to 4 mm, and the distance h2 between the plane in which the second fuel injection hole (7) is located and the end surface of the outer wall ring (4) ranges from 0 mm to 6 mm.

8. The swirl burner of any one of claims 1 to 2, wherein, The outer contour of the spoiler bluff body (9) is one of a pyramid, a cylinder, a cone, a cuboid, and a blade. In the case where the outer contour of the spoiler bluff body (9) is a triangular pyramid, the width w of the spoiler bluff body (9) ranges from 0.5 mm to 10 mm, the inclination angle β of the spoiler bluff body (9) ranges from 5° to 80°, the height h of the spoiler bluff body (9) ranges from 0.8 mm to 20 mm, and the distance l between the mounting position of the spoiler bluff body (9) and the end face of the outer wall ring (4) ranges from 0 to 5 mm.

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