Nozzle structure with prechamber and combustion chamber

Abstract

The present application relates to the technical field of combustion, and discloses a nozzle structure with a precombustion stage and a combustion chamber, wherein the nozzle structure comprises: a nozzle body, a precombustion stage assembly is arranged at the middle part of the nozzle body, the precombustion stage assembly is used for mixing and precombustion of reaction components, a plurality of nozzle channels are arranged on the nozzle body outside the precombustion stage assembly, and the nozzle channels are used for spraying the mixed reaction components. The nozzle structure with the precombustion stage and the combustion chamber provided by the present application are provided with a plurality of nozzle channels on the nozzle body, which is conducive to reducing the mixing unit of the reaction components and improving the uniformity of the mixed reaction components, and is suitable for stable combustion of flexible fuels such as hydrogen. Further, the precombustion stage assembly is arranged at the middle part of the nozzle body, the precombustion flame has a flame stabilizing effect under a low load condition, which is conducive to ensuring stable combustion of the fuel under the low load condition, thereby improving the load range of efficient work of the nozzle structure and reducing the flame combustion oscillation.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of combustion technology, in particular to a nozzle structure with a pre-combustion stage and a combustion chamber. BACKGROUND

[0002] Gas turbines are one of the important equipment in the field of energy power today. Traditional gas turbines mainly use natural gas as fuel. However, under the goal of low carbon emission, in the future low carbon clean energy ecosystem, the use of flexible fuel mainly using hydrogen gas mixed with other gas fuels such as carbon monoxide, short-chain alkanes, etc. is the main way for gas turbines to realize low carbon or even zero carbon power generation. However, due to the active chemical properties of hydrogen fuel and other flexible fuels, the traditional natural gas low emission combustion chamber directly using hydrogen fuel has a serious problem of self-ignition backfire oscillation, and needs to use new combustion technology.

[0003] Micro-mixing combustion technology can achieve ultra-low emission by reducing the mixing scale of fuel and oxidant, and its high-speed jet flow has strong anti-backfire ability and flexible fuel adaptability. Although the current developed micro-mixing combustion technology can realize hydrogen fuel combustion, due to the small size of the micro-mixing channel, there are problems of poor low load stability and insufficient wide range of efficient working load. SUMMARY

[0004] The present application provides a nozzle structure with a pre-combustion stage and a combustion chamber to solve the problem that the current micro-mixing combustion technology can realize hydrogen fuel combustion, but due to the small size of the micro-mixing channel, there are problems of poor low load stability and insufficient wide range of efficient working load.

[0005] The present application provides a nozzle structure with a pre-combustion stage, comprising: a nozzle body, a pre-combustion stage assembly is arranged at the middle part of the nozzle body, the pre-combustion stage assembly is used for mixing and pre-combusting reaction components, a plurality of nozzle channels are arranged at the periphery of the pre-combustion stage assembly of the nozzle body, and the nozzle channels are used for spraying the mixed reaction components.

[0006] According to the nozzle structure with a pre-combustion stage provided by the present application, the pre-combustion stage assembly comprises a swirler and a central body arranged inside the swirler, the central body is arranged close to the inlet end of the swirler, a first channel is arranged between the central body and the swirler, a second channel is arranged inside the wall surface of the swirler, a first injection hole is arranged through the wall surface of the swirler at the outlet end of the swirler and close to the inner wall surface of the swirler, the first injection hole communicates the first channel and the second channel, and the first channel and the second channel can be respectively used for introducing the reaction components.

[0007] According to the nozzle structure with a pre-combustion stage provided by the present application, the first channel introduces oxidant, and the second channel introduces fuel.

[0008] The nozzle structure with a pre-combustion stage provided by the application has a third channel in the center body, the third channel is communicated with the first channel, and the third channel is used for feeding the reaction component.

[0009] The nozzle structure with a pre-combustion stage provided by the application has a hollow center body, the outlet end of the center body is provided with a second nozzle hole in the circumferential direction, and the first channel and the third channel are communicated through the second nozzle hole.

[0010] The nozzle structure with a pre-combustion stage provided by the application has the first channel feeding the oxidant and the third channel feeding the fuel.

[0011] The nozzle structure with a pre-combustion stage provided by the application has the swirler including at least one stage of swirler blades.

[0012] The nozzle structure with a pre-combustion stage provided by the application has the nozzle channel provided with a first inlet and a second inlet, the first inlet is located upstream of the second inlet, the first inlet is used for feeding the first component, and the second inlet is used for feeding the second component, wherein the density of the second component is greater than the density of the first component.

[0013] The nozzle structure with a pre-combustion stage provided by the application has a plurality of nozzle channels arranged according to a Fibonacci sequence-Fermat spiral, or a plurality of nozzle channels are arranged on the nozzle body in a plurality of circles, and the nozzle channels in any circle are uniformly distributed in the circumferential direction.

[0014] The application further provides a combustion chamber comprising the nozzle structure with a pre-combustion stage.

[0015] The nozzle structure with a pre-combustion stage and the combustion chamber provided by the application have a plurality of nozzle channels arranged on the nozzle body, which is conducive to reducing the mixing unit of the reaction component, improving the uniformity of the mixed reaction component, and having the advantages of inhibiting backfire and self-ignition, and is suitable for stable combustion of flexible fuels such as hydrogen; further, a pre-combustion stage assembly is arranged at the middle part of the nozzle body, a stable pre-combustion flame can be formed at the middle part of the nozzle body, the pre-combustion flame has a flame stabilizing effect under low load conditions, which is conducive to ensuring stable combustion of the fuel under low load conditions, and further improves the load range of efficient work of the nozzle structure and reduces the situation of flame combustion oscillation. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the 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 application, and other drawings can be obtained by those skilled in the art without creative labor.

[0017] Figure 1 is a schematic view of a first pre-combustion stage assembly of a first nozzle structure according to the present application;

[0018] Figure 2 is a schematic view of a second pre-combustion stage assembly of a first nozzle structure according to the present application; Figure 1 is a cross-sectional view of the AA plane of the second pre-combustion stage assembly of the first nozzle structure according to the present application;

[0019] Figure 3 is a schematic view of a third pre-combustion stage assembly of a first nozzle structure according to the present application;

[0020] Figure 4 is a cross-sectional view of the AA plane of the third pre-combustion stage assembly of the first nozzle structure according to the present application; Figure 3

[0021] Figure 5 is a schematic view of a first pre-combustion stage assembly of a second nozzle structure according to the present application;

[0022] Figure 6 is a cross-sectional view of the AA plane of the first pre-combustion stage assembly of the second nozzle structure according to the present application; Figure 5

[0023] Figure 7 is a schematic view of a second pre-combustion stage assembly of a second nozzle structure according to the present application;

[0024] Figure 8 is a cross-sectional view of the AA plane of the second pre-combustion stage assembly of the second nozzle structure according to the present application;

[0025] Figure 9 is a schematic view of a third pre-combustion stage assembly of a second nozzle structure according to the present application;

[0026] Figure 10 is a cross-sectional view of the AA plane of the third pre-combustion stage assembly of the second nozzle structure according to the present application;

[0027] Figure 11 is a schematic view of a first pre-combustion stage assembly of a second nozzle structure according to the present application;

[0028] Figure 12 is a schematic view of a second pre-combustion stage assembly of a second nozzle structure according to the present application;

[0029] Figure 13 is a schematic view of a third pre-combustion stage assembly of a second nozzle structure according to the present application.

[0030] Reference signs:

[0031] ​​1: nozzle body; 2: nozzle channel; 21: first inlet; 22: second inlet; 23: mixing structure; 31: first precombustion stage assembly; 32: second precombustion stage assembly; 33: third precombustion stage assembly; 301: swirler; 3011: first swirler blade; 3012: second swirler blade; 302: central body; 303: first channel; 304: second channel; 305: first injection hole; 306: third channel; 307: second injection hole; 308: fourth channel. DETAILED DESCRIPTION

[0032] In order to make the objects, technical solutions and advantages of the present application clearer, the technical solutions in the present application will be described clearly and completely below in conjunction with the drawings in the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0033] The present application will be described below in conjunction with Figures 1-13 The nozzle structure with precombustion stages and the combustion chamber of the present application are described.

[0034] With reference to Figure 1 , the present embodiment provides a nozzle structure with precombustion stages, which comprises a nozzle body 1, wherein a precombustion stage assembly is arranged at the middle part of the nozzle body 1, the precombustion stage assembly is used for mixing and precombustion of reaction components, and a plurality of nozzle channels 2 are arranged at the periphery of the precombustion stage assembly of the nozzle body 1, the nozzle channels 2 are used for spraying the mixed reaction components.

[0035] The nozzle body 1 is a support body for the nozzle channels 2, the nozzle channels 2 are formed by opening channels on the nozzle body 1, or the nozzle channels 2 are formed by opening holes on the nozzle body 1 and arranging channels in the holes. A plurality of reaction components can be respectively introduced into the inside of the nozzle channels 2 and sprayed from the outlet end after mixing. The plurality of nozzle channels 2 form a plurality of reaction component mixing units, and each nozzle channel 2 mixes a plurality of reaction components and sprays after mixing. The nozzle structure provided by the present embodiment arranges a plurality of nozzle channels 2 on the nozzle body 1, which can form a micro-mixing nozzle structure, i.e. reduce the mixing unit of the reaction components, which is conducive to the uniform mixing of the reaction components and has the advantages of inhibiting backfire and self-ignition, and is suitable for stable combustion of hydrogen and other flexible fuels.

[0036] Further, the embodiment sets a pre-combustion stage assembly at the middle part of the nozzle body 1, and the reaction components of the combustion reaction can be respectively introduced into the pre-combustion stage assembly for mixing and pre-combustion. Thus, a stable pre-combustion flame is formed at the middle part of the nozzle body 1, and the pre-combustion flame has a flame stabilizing effect under low load conditions, which is conducive to ensuring stable combustion of the fuel under low load conditions and improving the combustion stability under low load conditions.

[0037] The nozzle structure with a pre-combustion stage provided by the embodiment has a plurality of nozzle channels 2 arranged on the nozzle body 1, which is conducive to reducing the mixing unit of the reaction components, improving the uniformity of the mixing of the reaction components, and having the advantages of inhibiting backfire and self-ignition, and is suitable for stable combustion of flexible fuels such as hydrogen; further, a pre-combustion stage assembly is arranged at the middle part of the nozzle body 1, and a stable pre-combustion flame can be formed at the middle part of the nozzle body 1, and the pre-combustion flame has a flame stabilizing effect under low load conditions, which is conducive to ensuring stable combustion of the fuel under low load conditions, and further improving the load range of efficient operation of the nozzle structure and reducing the situation of flame combustion oscillation.

[0038] Further, the plurality of nozzle channels 2 are arranged in axial parallel.

[0039] On the basis of the above embodiment, further, with reference to Figure 2 , the pre-combustion stage assembly includes a swirler 301 and a central body 302 arranged inside the swirler 301, the central body 302 is arranged close to the inlet end of the swirler 301, the central body 302 and the swirler 301 have a first channel 303 therebetween, the wall surface of the swirler 301 is provided with a second channel 304, the second channel 304 is provided with a first injection hole 305 penetrating the wall surface at the outlet end of the swirler 301 and close to the wall surface inside the swirler 301, the first injection hole 305 communicates the first channel 303 and the second channel 304, and the first channel 303 and the second channel 304 can be respectively used for introducing the reaction components.

[0040] The pre-combustion stage assembly and the nozzle channel 2 of the nozzle structure respectively have an inlet end and an outlet end. In the nozzle channel 2, the reaction components are introduced from the inlet end and flow out from the outlet end. In the pre-combustion stage assembly, the reaction components are also introduced from the inlet end and flow out from the outlet end. The central body 302 is arranged close to the inlet end of the swirler 301, that is, the central body 302 is inserted into the swirler 301 from the inlet end of the swirler 301, and the outlet end surface of the central body 302 and the outlet end surface of the swirler 301 can have a spacing to leave a reaction component mixing space.

[0041] The central body 302 is inside the swirler 301, and a gap between the central body 302 and the wall surface of the adjacent swirler 301 is the first channel 303, which is in communication with the inlet end and the outlet end of the swirler 301, that is, the two ends of the first channel 303 are in a through manner. The wall surface of the swirler 301 adjacent to the central body 302, that is, the wall surface outside the first channel 303 can be hollowed out to form a second channel 304 inside the wall surface, and the second channel 304 can extend from the inlet end to the outlet end, and the second channel 304 is provided with a through hole penetrating the wall surface on the wall surface inside the swirler 301 at the outlet end in a circumferential direction, which is a first injection hole 305, and the first injection hole 305 is in communication with the second channel 304 and the internal space of the swirler 301, that is, the first injection hole 305 is in communication with the second channel 304 and the first channel 303.

[0042] The first channel 303 and the second channel 304 can be used to pass the reaction components, and the reaction components can be selectively passed in the first channel 303 and the second channel 304 according to the actual combustion working condition, and the type of the reaction components passed in each channel is not limited. The first channel 303 or the second channel 304 can also be selectively not used to pass the reaction components, that is, the first channel 303 and the second channel 304 can also not be used to pass the reaction components; the type of the reaction components passed in the first channel 303 and the second channel 304 and whether the first channel 303 and the second channel 304 are used to pass the reaction components are not limited, and can be flexibly selected according to the actual situation.

[0043] On the basis of the above-mentioned embodiments, further, Figure 2 In the embodiment, the first channel 303 passes the oxidant, and the second channel 304 passes the fuel. That is, the reaction components in the embodiment include the fuel and the oxidant, the oxidant is passed from the first channel 303 between the central body 302 and the side wall of the swirler 301 and flows from the inlet end to the outlet end. The fuel is passed from the second channel 304 in the wall surface of the swirler 301 and is sprayed from the first injection hole 305 when flowing from the inlet end to the outlet end, and is sprayed to the inside of the outlet end of the swirler 301. The fuel is mixed with the oxidant at the outlet end and flows out of the outlet end of the swirler 301 for pre-combustion.

[0044] In the embodiment, the second channel 304 and the first injection hole 305 are arranged in the wall surface of the swirler 301, the fuel is sprayed from the first injection hole 305 to the flowing oxidant, the fuel distribution can be changed by the fuel injection mode, the combustion reaction area is changed to cause the difference of the temperature field distribution, and the unreasonable problem of the temperature field distribution in the conventional combustion chamber can be improved, so as to be beneficial to improve the fuel distribution, improve the combustion efficiency, and reduce the emission.

[0045] Further, the second channel 304 can be provided with an opening on the end face of the inlet end of the swirler 301 in the circumferential direction, and the opening is used to communicate with the inside of the second channel 304, and fuel can be introduced into the inside of the second channel 304 through the opening. Further, the first injection hole 305 can be inclined in the axial direction relative to the swirler 301, and can be inclined toward the first channel 303 in the flow direction, so as to better spray the fuel into the first channel 303 through the second injection hole 307 to mix with the oxidant, which is beneficial to improve the mixing uniformity, so as to improve the fuel effect.

[0046] On the basis of the above-mentioned embodiments, further, the inside of the center body 302 has a third channel 306, the third channel 306 communicates with the first channel 303, and the third channel 306 can be used to introduce the reaction component. That is, in the present embodiment, the third channel 306 can be formed in the inside of the center body 302, and the third channel 306 can also be used to introduce the reaction component.

[0047] Whether the first channel 303, the second channel 304 and the third channel 306 actually introduce the reaction component and the specific type of the reaction component introduced are not limited, and can be flexibly set according to the actual situation.

[0048] On the basis of the above-mentioned embodiments, further, with reference to Figure 3 and Figure 4 , the center body 302 is a hollow structure, the outlet end of the center body 302 is provided with a second injection hole 307 in the circumferential direction, and the first channel 303 and the third channel 306 communicate through the second injection hole 307. The center body 302 can be a hollow structure, and the end face of the outlet end of the center body 302 can be closed, and the first channel 303 and the third channel 306 are communicated by providing the second injection hole 307 penetrating the wall face of the outlet end of the center body 302.

[0049] On the basis of the above-mentioned embodiments, further, in the present embodiment, the first channel 303 introduces the oxidant, and the third channel 306 introduces the fuel. The fuel enters the third channel 306 from the inlet end of the center body 302, flows to the outlet end of the center body 302, and is mixed with the oxidant in the first channel 303 through the second injection hole 307, and then flows to the outlet end of the swirler 301 for pre-combustion.

[0050] In the present embodiment, the fuel is sprayed from the second injection hole 307 into the flowing oxidant, and the fuel injection mode can also change the spatial distribution of the fuel, change the combustion reaction area, and thus cause the difference of the temperature field distribution, so as to improve the problem of unreasonable temperature field distribution in the conventional combustion chamber, thereby being beneficial to improve the fuel distribution, improve the combustion efficiency, and reduce the emission.

[0051] Further, the second injection hole 307 is axially tiltable relative to the central body 302, and can be tilted towards the first channel 303 along the flow direction, so as to better inject the fuel through the second injection hole 307 into the first channel 303 to mix with the oxidant, thereby improving the mixing uniformity and fuel effect.

[0052] On the basis of the above-mentioned embodiments, further, the swirler 301 comprises at least one stage of swirler vanes.

[0053] With reference to Figure 5 and Figure 6 , in the present embodiment, a stage of swirler vanes is arranged on the periphery of the central body 302, i.e. the swirler 301 comprises one stage of swirler vanes. The reaction components can be introduced into the third channel 306 inside the central body 302 and the first channel 303 between the central body 302 and the wall of the swirler 301. In other embodiments, a second channel 304 can also be arranged inside the wall of the swirler 301, and the reaction components can be introduced through the second channel 304, which is not limited in particular.

[0054] Further, when the swirler 301 comprises a plurality of stages of swirler vanes, the plurality of stages of swirler vanes are arranged in sequence, and the gap between the adjacent two stages of swirler vanes forms a fourth channel 308, which can be used to introduce the reaction components. With reference to Figure 2 and Figure 4 , in the present embodiment, the swirler 301 is provided with two stages of swirler vanes, i.e. a first swirler vane 3011 and a second swirler vane 3012. A fourth channel 308 is also formed between the adjacent two stages of swirler vanes, which can also be used to introduce the reaction components, or can not be used to introduce the reaction components, which is not limited in particular.

[0055] In particular, with reference to Figure 2 , in the present embodiment, the fourth channel 308 can be used to introduce the oxidant.

[0056] On the basis of the above-mentioned embodiments, further, with reference to Figure 7 , the nozzle channel 2 is provided with a first inlet 21 and a second inlet 22, the first inlet 21 is located upstream of the second inlet 22, the first inlet 21 is used to introduce the first component, and the second inlet 22 is used to introduce the second component, wherein the density of the second component is greater than the density of the first component.

[0057] The nozzle channel 2 in the embodiment is a hollow structure for flowing multiple reaction components. The multiple reaction components can include a first component and a second component. The inlet end of the nozzle channel 2 is an upstream position, and the outlet end is a downstream position, that is, the flow direction of the reaction components in the nozzle channel 2 is from the inlet end to the outlet end. The first inlet 21 and the second inlet 22 are arranged at intervals, and the second inlet 22 is located at the downstream position, so that in the nozzle channel 2, the second component is injected into the flowing first component to mix with the first component.

[0058] Further, in the embodiment, the second component with a larger density is arranged to be injected at the downstream to mix with the flowing first component. The second component has a larger density and a stronger jet penetration capability. Compared with expanding and mixing the first component with a smaller density into the second component, the embodiment uses the diffusion and mixing of the second component to improve the mixing uniformity of the first component and the second component, improve the mixing effect, and is conducive to obtaining better combustion effect subsequently.

[0059] The nozzle channel 2 structure provided in the embodiment divides the reaction components according to the density, places the second component with a larger density at the downstream to be injected into the first component flowing at the upstream to mix, the second component has a stronger penetration capability and can better diffuse into the first component flow, which is conducive to improving the mixing uniformity of multiple reaction components, achieving a better mixing effect, and thus reducing the local high-temperature zone in the subsequent combustion process, inhibiting combustion oscillation, and improving the combustion effect.

[0060] In the embodiment, the first component and the second component are injected at intervals, which also avoids the risk of spontaneous combustion and tempering caused by early mixing of the reaction components, and ensures the safety of combustion. The nozzle structure is suitable for traditional fuels such as natural gas and flexible fuels such as hydrogen, has strong fuel adaptability, and has high safety.

[0061] Further, referring to Figure 8 , the nozzle channel 2 is provided with a mixing structure 23, and the first inlet 21 and the second inlet 22 are located upstream of the mixing structure 23. Thus, after the second component is injected into the flowing first component through the second inlet 22, the second component flows through the mixing structure 23 for sufficient mixing and then flows out from the outlet end of the nozzle channel 2. This is conducive to improving the uniformity of the mixing of multiple reaction components. The mixing structure 23 can be a swirling structure, and the specific form is not limited as long as it can sufficiently mix the first component and the second component.

[0062] Further, referring to Figure 8 , the inner diameter d of the nozzle channel 2 is 2-20 mm. The diameter of the nozzle channel 2 of this size can be selected according to the working condition of the combustion chamber. The nozzle channel 2 with a size in this range can achieve good mixing of reaction components, and the size of a single nozzle channel 2 is small, which can reduce the scale of fuel and air mixing to achieve micro-mixing combustion. In other embodiments, the size of the nozzle channel 2 can also be other, and the specific size is not limited.

[0063] Further, refer to Figure 7 and Figure 8 The inlet end of the nozzle channel 2 can be an open structure, and the inlet end can be set as a first inlet 21; the second inlet 22 can be set on the side wall of the nozzle channel 2, penetrating the side wall. Thus, the first component is sprayed from the inlet end of the nozzle channel 2 and flows circumferentially along the channel, and the second component is sprayed from the side wall onto the flowing first component for mixing.

[0064] Based on the above embodiments, furthermore, the plurality of nozzle channels 2 are arranged according to the Fibonacci sequence-Fermat spiral, such as... Figure 11 , Figure 12 and Figure 13 As shown; or, multiple nozzle channels 2 are arranged in multiple rings on the nozzle body 1, with any ring of nozzle channels 2 evenly distributed circumferentially, such as... Figure 1 , Figure 3 and Figure 5 As shown.

[0065] refer to Figure 9 This embodiment proposes that multiple nozzle channels 2 be arranged according to the Fibonacci sequence-Fermat spiral. Specifically, the multiple nozzle channels 2 are arranged in a spiral, and the spiral arrangement follows the Fibonacci sequence-Fermat spiral. This spiral arrangement is similar to the arrangement of sunflowers in nature, making the nozzle channels 2 spirally distributed. This arrangement not only improves the circumferential uniformity among the nozzle channels 2, but also helps to improve the radial uniformity of the nozzle channels 2 on the nozzle body 1, thereby improving the overall uniformity of the distribution of the nozzle channels 2 on the nozzle body 1.

[0066] In this embodiment, multiple nozzle channels 2 are arranged according to the Fibonacci sequence-Fermat spiral, which helps to maintain a uniform distribution of nozzle channels 2 in both the circumferential and radial directions of the nozzle body 1. This improves the overall uniformity of the distribution of nozzle channels 2, which in turn improves the uniformity of fuel distribution in space, avoids the formation of local high-temperature zones, effectively enhances the stability of the flame and the combustion performance, and ensures the combustion effect.

[0067] The nozzle structure provided in this embodiment has multiple nozzle channels 2 arranged according to the Fibonacci sequence-Fermat spiral, compared to... Figure 1 The concentric circle distribution shown is beneficial for maintaining a uniform distribution of nozzle channels 2 in both the circumferential and radial directions, thereby improving the overall uniformity of nozzle channel distribution and enhancing combustion performance. Furthermore, due to the excellent uniformity of the nozzle channels 2, only one larger nozzle body 1 can be used in the combustion chamber instead of multiple smaller nozzle bodies 1, resulting in better combustion performance than the concentric circle distribution structure when the combustion chamber size is large.

[0068] On the basis of the above-mentioned embodiments, further, the Fibonacci sequence-Fermat spiral arrangement is specifically:

[0069]

[0070]

[0071] wherein, referring to Figure 9 , R is the spacing between the center of the nth nozzle channel 2 and the center of the nozzle body 1, which can be obtained by the above formula. c is a size coefficient; it is related to the size of the nozzle body 1, that is, related to the size of the combustion chamber, and can be set according to the size of the nozzle body 1; specifically, c can be 0.6-2 times the diameter of the nozzle channel 2. n is a natural number, which can start from 1, and then take 2, 3, 4, and so on, to obtain the position information of the n nozzle channels 2. Alpha is the rotation angle of the nth nozzle channel 2 and the n+1 nozzle channel 2 about the center of the nozzle body 1; 0<alpha<360°, changing the angle value can obtain different arrangement modes, which can be used in different combustion chambers as appropriate.

[0072] Referring to Figure 10 , the position of the center of each nozzle channel 2 can be determined by polar coordinates; specifically, a polar coordinate system is constructed with the center of the nozzle body 1 as the zero point, wherein r is the polar coordinate radius; theta is the polar coordinate angle. Then the center of the nth nozzle channel 2, that is, the center, can be expressed as r equals R, and theta equals the remainder of n*alpha divided by pi. The coordinate positions of the first to nth nozzle channels 2 can be obtained in turn.

[0073] On the basis of the above-mentioned embodiments, further, alpha in the Fibonacci sequence-Fermat spiral arrangement is 50°-300°. The Fibonacci sequence-Fermat spiral arrangement in this angle range has higher uniformity, and different angle values can obtain different arrangements, and the specific angle value can be designed according to the actual application, which is not limited.

[0074] For example, alpha in the Fibonacci sequence-Fermat spiral arrangement can be 69°, 85.4°, 137.5°, 179°, 222.5° or 274.6°. This embodiment specifically provides six different alpha value examples, and the Fibonacci sequence-Fermat spiral arrangement under the six alpha values has higher uniformity in the circumferential and radial directions, which can make the overall distribution of the nozzle channels 2 more uniform, to obtain better combustion effect.

[0075] Alternatively, alpha in the Fibonacci sequence-Fermat spiral arrangement can be 69°, 85.4°, 137.5°, 222.5° or 274.6°, which has better distribution uniformity. In other embodiments, alpha in the Fibonacci sequence-Fermat spiral arrangement can also take other values, which can be flexibly selected according to the specific combustion chamber design and combustion working condition, and the specific value is not limited.

[0076] On the basis of the above-mentioned embodiments, further, the present embodiment provides a combustor comprising the nozzle structure with pre-combustion stage according to any one of the above-mentioned embodiments. The combustor can further comprise a flame tube assembly, and the nozzle structure can be arranged at an inlet end of the flame tube assembly.

[0077] The combustor further comprises some connecting pipes and other structures which are well known to those skilled in the art and will not be described here.

[0078] Further, in the above-mentioned embodiments, the nozzle structure is used in a combustor, and the combustion reaction of the combustor can comprise multiple reaction components, specifically can comprise two reaction components of a first component and a second component, and the two reaction components can be fuel and oxidant. The fuel can be flexible fuel such as hydrogen, or can be fuel such as natural gas; the oxidant can be air or oxygen, etc. In other embodiments, the reaction components can also comprise three components, for example, can comprise fuel, oxidant, and diluent or catalyst, etc., and the specific number and type of reaction components are not limited.

[0079] On the basis of the above-mentioned embodiments, further, the present embodiment is based on the fact that the conventional natural gas combustor cannot achieve safe and efficient combustion of hydrogen fuel-based flexible fuel, and the currently developed micro-mixing combustion technology can achieve hydrogen fuel combustion, but its low load stability is poor, the high efficient working load range is not wide enough, and the flame is prone to combustion oscillation. The purpose of the present embodiment is to provide a micro-mixing combustion nozzle with a pre-combustion stage, which can not only burn conventional fuel such as natural gas, but also achieve safe and efficient low-emission combustion of hydrogen fuel-based flexible fuel, and improve the flame stability and adjustment capacity of the nozzle.

[0080] The present embodiment provides a micro-mixing combustion nozzle with a pre-combustion stage, which is composed of a pre-combustion stage assembly and a combustor nozzle. The pre-combustion stage assembly comprises three forms, which are described below with reference to Figure 2 The first one is a first pre-combustion stage assembly 31, in which fuel is introduced from the second channel 304, oxidant is introduced from the first channel 303, and the fuel is sprayed from the first injection hole 305 to mix with the oxidant and then pre-combust. Referring to Figure 4 The second one is a second pre-combustion stage assembly 32, in which fuel is introduced from the third channel 306, oxidant is introduced from the first channel 303, and the fuel is sprayed from the second injection hole 307 to mix with the oxidant and then pre-combust. Referring to Figure 6 The third one is a third pre-combustion stage assembly 33, in which fuel is introduced from the third channel 306, oxidant is introduced from the first channel 303, and the fuel is sprayed from the second injection hole 307 to mix with the oxidant and then pre-combust.

[0081] Further, the nozzle structure has a plurality of nozzle channels 2 arranged in a concentric circle structure, such as Figure 1as shown; and structures arranged using bionics, such as Figure 11

[0082] The embodiment adopts a micro-mixing nozzle with a pre-combustion stage, has strong fuel adaptability, can realize efficient combustion of flexible fuel mainly with hydrogen fuel through micro-mixing combustion technology, realize low-carbon or even zero-carbon emission, can improve the fire stability and regulation capacity through the pre-combustion stage, effectively inhibit the spontaneous combustion backfire and combustion oscillation, and ensure the combustion safety, and has a wider efficient working load range and load rapid regulation capacity compared with a single micro-mixing nozzle.

[0083] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, but not to limit it; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solution deviate from the spirit and scope of the technical solutions of the embodiments of the present application.​

Claims

1. A nozzle structure with a prechamber stage, characterized in that The application relates to a nozzle structure with a precombustion stage. The precombustion stage comprises a swirler and a central body arranged inside the swirler. The first channel and the second channel are respectively used for feeding the reaction components. The central body is a hollow structure, and a second injection hole is arranged on the outlet end of the central body in the circumferential direction.

2. The prechamber nozzle structure according to claim 1, characterized in that The first channel is used for feeding oxidants, and the third channel is used for feeding fuel.

3. The prechamber nozzle structure according to claim 2, characterized in that The swirler comprises at least one stage of swirler blades.

4. The prechamber nozzle structure according to claim 2, characterized by The nozzle channel is provided with a first inlet and a second inlet, the first inlet is located upstream of the second inlet, the first inlet is used for feeding a first component, and the second inlet is used for feeding a second component, wherein the density of the second component is greater than that of the first component.

5. The prechamber nozzle structure according to any one of claims 1 to 4, characterized in that The nozzle channels are arranged according to a Fibonacci sequence-Fermat spiral, or a plurality of the nozzle channels are arranged in a plurality of circles on the nozzle body, and the nozzle channels in any one circle are uniformly distributed in the circumferential direction.

6. The prechamber nozzle structure according to any one of claims 1 to 4, characterized in that The application further relates to a nozzle structure with a precombustion stage.

7. The prechamber nozzle structure according to any one of claims 1 to 4, characterized in that ​ 8. A combustion chamber, characterized by ​

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