Combustion chamber structure

Abstract

The present application relates to the technical field of combustion chamber, more particularly to a combustion chamber structure. The present application provides a combustion chamber structure, comprising a combustion chamber body and a head assembly: the head assembly is used for supplying fuel; the head assembly comprises a pipeline, a head disc cavity center part and a plurality of fuel channels: the pipeline is connected to the head disc cavity center part and is used for conveying fuel; the head disc cavity center part is used for guiding fuel to distribute to the fuel channels on the outside; the plurality of fuel channels are connected with the outside of the head disc cavity center part in a way of outward radiation; each of the fuel channels is provided with a micropore structure, and the micropores spray fuel in the form of a transverse jet flow. The combustion chamber structure provided by the present application effectively inhibits the deterioration of combustion oscillation caused by symmetry by combining the bionics micropore layout and the transverse jet flow combustion organization mode, and significantly improves the hydrogen combustion stability and efficiency.

Description

Technical Field

[0001] This invention relates to the field of combustion chamber technology, and more specifically, to a combustion chamber structure, an aero-engine, and a gas turbine. Background Technology

[0002] With the continuous increase in carbon emissions from human activities, the greenhouse effect is intensifying, seriously threatening the balance of global ecosystems and the sustainable survival of humankind. To address this global challenge, significantly reducing carbon emissions and achieving carbon peaking and carbon neutrality as soon as possible has become an urgent task. Among many low-carbon energy sources, hydrogen, as a zero-carbon emission energy source, is considered one of the effective ways to solve the carbon emission problem due to its advantages such as small molecular weight, high activity, and high calorific value. Compared with traditional high-carbon fuels such as aviation kerosene commonly used in aircraft engines and gas turbines, hydrogen's combustion characteristics, including rapid combustion speed, wide explosion limits, and high combustion temperature, present numerous technical challenges when applied to aircraft engines and gas turbines, especially in the case of pure hydrogen combustion, such as easy backfire, high NOx emissions, and combustion oscillations. Simply optimizing existing combustion modes cannot effectively solve these problems; therefore, it is urgent to develop an energy-saving and low-emission combustion organization method suitable for pure hydrogen combustion.

[0003] To address these technical challenges, microscale channel diffusion combustion can significantly reduce fuel residence time in high-temperature zones, thereby effectively reducing NOx formation; non-premixed combustion can reduce the risk of backfire. However, current micropore-based combustion methods commonly suffer from combustion oscillation problems in practical applications. Existing micropore designs typically employ a ring-shaped symmetrical layout. While this layout efficiently utilizes limited space, its symmetry easily induces high-frequency and low-frequency combustion oscillations within the burner, adversely affecting the system's combustion stability.

[0004] Therefore, it is urgent to explore an innovative micropore distribution design to optimize combustion organization, overcome oscillation problems, and achieve the goals of high efficiency, stability, and low emissions in hydrogen combustion. Summary of the Invention

[0005] The purpose of this invention is to provide a combustion chamber structure that solves the problems of existing combustion chambers being unable to achieve low NOx emissions and combustion backfire.

[0006] Another objective of this invention is to provide a combustion chamber structure that solves the problem of combustion stability caused by combustion oscillations in existing combustion chambers.

[0007] To achieve the above objectives, the present invention provides a combustion chamber structure, including a combustion chamber body and a head assembly:

[0008] The head assembly is used to supply fuel;

[0009] The head assembly includes conduits, a central portion of the head disc cavity, and several fuel passages:

[0010] The pipe is connected to the central part of the head disc cavity for transporting fuel;

[0011] The central portion of the head disc cavity is used to guide the fuel distribution to the outer side of the fuel channel;

[0012] The plurality of fuel channels are connected to the outer side of the central portion of the head disc cavity in an outward radial manner;

[0013] Each of the fuel channels is provided with a number of micro-holes, which inject fuel in the form of a cross-jet stream.

[0014] In some embodiments, the streamlines of the fuel passage are fitted according to the layout of the micropores;

[0015] The microporous structure adopts a biomimetic spiral layout.

[0016] In some embodiments, the layout of the microporous structure is based on the center point and presents a distribution pattern of a certain number of forward and / or reverse spirals in a polar coordinate system.

[0017] In some embodiments, the number of the forward and reverse spirals conforms to the adjacent numbers in the Fibonacci sequence.

[0018] In some embodiments, the direction of each micropore is determined by a vertical line perpendicular to the fuel channel, originating from the center of the micropore, to achieve a cross-jet flow.

[0019] In some embodiments, the radius of the micropore increases with increasing distance from the center point.

[0020] In some embodiments, the layout characteristic parameters of the biomimetic spiral layout include:

[0021] The polar diameter β of the center of the nth micropore n ;

[0022] The polar angle θ of the center of the nth micropore n ;

[0023] The radius r of the nth micropore n .

[0024] In some embodiments, the polar diameter β of the center of the nth micropore n The corresponding expression is:

[0025]

[0026] Where β0 is the initial polar radius and Δβ is the interval setting value.

[0027] In some embodiments, the polar angle θ of the center of the nth micropore n The corresponding expression is:

[0028] θ n =2πnθ0;

[0029] Where θ0 is the polar angle difference.

[0030] In some embodiments, the radius r of the nth micropore n The corresponding expression is:

[0031] r n =kβ n

[0032] Where k is the radius control parameter.

[0033] To achieve the above objectives, the present invention provides an aircraft engine comprising at least a compressor, a combustion chamber, and a turbine:

[0034] The compressor compresses outside air to form high-pressure air which then enters the combustion chamber.

[0035] The combustion chamber mixes and burns high-pressure air with fuel to form high-temperature gas, which drives the turbine to rotate.

[0036] The combustion chamber adopts the combustion chamber structure described above.

[0037] To achieve the above objectives, the present invention provides a gas turbine, comprising at least a compressor, a combustion chamber, and a turbine:

[0038] The compressor compresses outside air to form high-pressure air which then enters the combustion chamber.

[0039] The combustion chamber mixes and burns high-pressure air with fuel to form high-temperature gas, which drives the turbine to rotate.

[0040] The combustion chamber adopts the combustion chamber structure described above.

[0041] This invention proposes a combustion chamber structure, an aero-engine, and a gas turbine. The combustion chamber structure combines a biomimetic micropore layout with a cross-jet combustion organization method, which effectively suppresses the deterioration of combustion oscillations caused by symmetry while ensuring uniform fuel injection distribution, thus significantly improving the stability and efficiency of hydrogen combustion. Attached Figure Description

[0042] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features, wherein:

[0043] Figure 1 A schematic diagram of the basic layout of a core component of an aero-engine or gas turbine according to an embodiment of the present invention is disclosed.

[0044] Figure 2 A schematic diagram of a combustion chamber according to an embodiment of the present invention is shown;

[0045] Figure 3a A front view of a head component according to an embodiment of the present invention is disclosed;

[0046] Figure 3b A head assembly according to an embodiment of the present invention is disclosed along Figure 3a Schematic diagram of section AA;

[0047] Figure 4 A head assembly according to an embodiment of the present invention is disclosed along Figure 3b Schematic diagram of the BB section;

[0048] Figure 5 A schematic diagram of a first biomimetic layout of micropores according to an embodiment of the present invention is disclosed;

[0049] Figure 6 A schematic diagram of a second biomimetic layout of micropores according to an embodiment of the present invention is disclosed;

[0050] Figure 7 A schematic diagram illustrating the combination of micropore distribution and cross-jet combustion organization according to an embodiment of the present invention is shown.

[0051] The meanings of the labels in the figures are as follows:

[0052] 1. Outside air;

[0053] 2. Compressors;

[0054] 3. High-pressure air;

[0055] 4. Combustion chamber;

[0056] 5 axes;

[0057] 6. High-temperature gas;

[0058] 7 turbochargers;

[0059] 8. Airflow;

[0060] 9. Header components;

[0061] 10 Flames;

[0062] 11 pipes;

[0063] 12. The central part of the head disc cavity;

[0064] 13 fuel passages;

[0065] 14 micropores. Detailed Implementation

[0066] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the invention.

[0067] This invention proposes a combustion chamber structure, primarily targeting hydrogen-based fuel combustion chambers. Under the conditions of low NOx emissions and no backfire, it designs a combustion organization mode that can suppress oscillating combustion. By combining a biomimetic micropore layout with a cross-jet flow combustion organization mode, it effectively suppresses the deterioration of combustion oscillations caused by symmetry while ensuring uniform fuel injection distribution, thus significantly improving combustion stability and efficiency.

[0068] Based on the combustion chamber structure proposed in this invention, this invention also provides an aero-engine or gas turbine.

[0069] Figure 1 A basic layout schematic diagram of a core component of an aero-engine or gas turbine according to an embodiment of the present invention is shown, such as... Figure 1 As shown, the core components of an aero-engine or gas turbine include at least a compressor 2, a combustion chamber 4, and a turbine 7.

[0070] The compressor 2 compresses outside air to form high-pressure air which then enters the combustion chamber 4.

[0071] The combustion chamber 4 mixes and burns high-pressure air with fuel to form high-temperature gas, which drives the turbine 7 to rotate.

[0072] More specifically, such as Figure 1 As shown, outside air 1 is compressed into high-pressure air 3 by compressor 2 and enters combustion chamber 4. Fuel and air are burned in combustion chamber, releasing heat and forming high-temperature gas 6.

[0073] High-temperature gas 6 drives turbine 7, which transmits some of its energy to compressor 2 through shaft 5, providing power for compressor 2 to compress gas. After passing through compressor 2, the gas is released into the air.

[0074] High-temperature gas 6 is discharged from turbine 7, forming an airflow 8.

[0075] The combustion chamber structure proposed in this invention is applicable to aero engines and gas turbines. The combustion chamber structure proposed in this invention mainly focuses on the design of the nozzles in combustion chamber 4, and is suitable for both hydrogen-based fuels and other fuels.

[0076] The present invention proposes a combustion chamber structure, comprising a combustion chamber body and a head assembly:

[0077] The head assembly is used to supply fuel;

[0078] The head assembly includes conduits, a central portion of the head disc cavity, and several fuel passages:

[0079] The pipe is connected to the central part of the head disc cavity for transporting fuel;

[0080] The central portion of the head disc cavity is used to guide the fuel distribution to the outer side of the fuel channel;

[0081] The plurality of fuel channels are connected to the outer side of the central portion of the head disc cavity in an outward radial manner;

[0082] Each of the fuel channels is provided with a microporous structure, and the microporous structure injects fuel in the form of a cross-jet stream to achieve fuel supply.

[0083] To reduce combustion oscillations while ensuring efficient use of space, the combustion chamber structure proposed in this invention is based on a microporous non-premixed combustion method. It incorporates a biomimetic spiral layout for the microporous arrangement, utilizing its uniform layout and asymmetric and non-periodic characteristics to effectively suppress combustion oscillations.

[0084] In this embodiment, the microporous structure is not merely a simple channel for fuel injection in the traditional sense, but a specially designed injection structure with a specific geometric distribution and orientation, which can be considered as the nozzle unit of the designed combustion chamber 4.

[0085] Please refer to the following. Figures 2 to 7 The combustion chamber structure proposed in this invention will be described in detail.

[0086] Figure 2 A schematic diagram of a combustion chamber according to an embodiment of the present invention is shown, such as Figure 2 As shown, combustion chamber 4 includes a combustion chamber body and a head assembly:

[0087] The combustion chamber is the core of the entire system, used to mix fuel and air, burn fuel, and release heat.

[0088] The design of the main body of the combustion chamber mainly includes two stages: the air expansion and guide section and the diffusion combustion section, in order to achieve a high-efficiency, low-emission combustion process.

[0089] like Figure 2The left side is the air expansion and guide section, which is responsible for guiding external air into the combustion chamber. The air gradually expands and adjusts its flow rate through the air expansion section to match the direction of the fuel injection flow. The guide section optimizes the mixing conditions of fuel and air, while reducing the degree of turbulence in the flow, providing a uniform gas mixture for the diffusion combustion stage.

[0090] like Figure 2 The right side is the diffusion combustion section, where hydrogen-based fuel is mixed with air and burned to form flame 10, which ultimately generates high-temperature gas 6, driving the subsequent turbine 7 to output power.

[0091] The head assembly 9 is responsible for the supply and distribution of hydrogen-based fuel, and its design directly affects the combustion efficiency and combustion stability within the combustion chamber.

[0092] Hydrogen-based fuel is supplied by head assembly 9. The hydrogen-based fuel enters the incoming air through the micro-holes 14 of head assembly 9, and then enters the combustion chamber body to burn, forming flame 10. After complete combustion, the high-temperature gas 6 produced will enter turbine 7 to do work.

[0093] Figure 3a A front view of a head component according to an embodiment of the present invention is disclosed. Figure 3b Revealed the root head component along Figure 3a A schematic diagram of section AA. Figure 4 Revealed the head component along Figure 3b A schematic diagram of the BB section is shown below. Figures 3a to 4 In the illustrated embodiment, the head assembly 9 includes at least a conduit 11, a central portion 12 of the head disc cavity, and several fuel passages 13.

[0094] The pipe 11 is connected to the central part 12 of the head disc cavity for conveying hydrogen-based fuel;

[0095] The central portion 12 of the head disc cavity is used to guide the fuel to the outer fuel channel distribution;

[0096] The plurality of fuel channels 13 are connected to the outer side of the central portion 12 of the head disc cavity in an outward radial manner, extending outward from the center;

[0097] like Figure 3a As shown, the streamlines of fuel channel 13 are designed based on the micropore layout, which will be described in detail later.

[0098] like Figure 3b As shown, hydrogen-based fuel enters the central portion 12 of the head disc cavity along the pipe 11, and there is a fuel channel 13 radiating outward inside the central portion 12 of the head disc cavity.

[0099] Micro-holes 14 are located on the sidewall of fuel passage 13 and inject hydrogen-based fuel into the combustion chamber in the form of a cross-jet stream, where it mixes with the incoming air. This injection method effectively improves the mixing uniformity and avoids backfire problems.

[0100] like Figure 4 As shown, hydrogen-based fuel is supplied by entering the incoming air in a cross-jet manner through the micro-holes 14 on both sides of these fuel channels 13.

[0101] Figure 5 A schematic diagram of a first biomimetic layout of micropores according to an embodiment of the present invention is disclosed. Figure 6 A schematic diagram of a second biomimetic layout of micropores according to an embodiment of the present invention is shown, such as... Figure 5 and Figure 6 As shown, the micropore 14 structure in this invention utilizes a biomimetic spiral layout.

[0102] Bionic spiral layouts are commonly found in sunflowers, succulents, and other plants. Thanks to their unique non-periodic and asymmetric characteristics, bionic spiral layouts have been widely used in the distribution design of grinding, heat exchange, solar energy, and optical lenses.

[0103] More specifically, the layout characteristic parameters of the microporous structure include:

[0104] The polar diameter β of the center of the nth micropore n ;

[0105] The polar angle θ of the center of the nth micropore n ;

[0106] The radius r of the nth micropore n .

[0107] The polar coordinates of the layout characteristic parameters of the microporous structure are defined as follows:

[0108]

[0109] θ n =2πnθ0

[0110] r nn =kβ n

[0111] Where, β n The polar diameter of the nth micropore center determines the distance of each micropore, which is gradually distributed outward from the center;

[0112] θ n The polar angle of the center of the nth micropore ensures that the distribution of micropores forms a spiral shape;

[0113] β0 is the initial polar diameter, which is related to the size limitation of the central part 12 of the head disk cavity during the design process;

[0114] Δβ is the interval setting value, used to adjust the distance between the centers of different micropores, thereby controlling the density and uniformity of the micropore distribution. When designing micropore structures, this parameter can be adjusted appropriately according to specific needs; typically, it should not exceed 1.5 times the maximum micropore diameter.

[0115] θ0 is the polar angle difference value, used to determine the polar angle difference between two consecutive micropores;

[0116] To achieve a biologically specific micropore distribution, values ​​are taken as follows:

[0117] r n The radius of the nth micro-orifice increases as the micro-orifice moves further away from the center, optimizing spray performance or other functions;

[0118] k is a radius control parameter used to adjust the size of the micropores;

[0119] The diameter of the micropores is generally set between 0.5 mm and 2 mm.

[0120] It's important to note that the numbering of the nth micropore refers to the total number across all helices, not just the number on a single helice. Micropores on each helice (whether clockwise or counterclockwise) are arranged according to a specific rule, but the micropore numbering is continuous and global, rather than being renumbered independently for each helice. This numbering system allows for unified management of all micropores, facilitating structural design and analysis, while ensuring the rational distribution and positioning of micropores across different helices.

[0121] like Figure 5 and Figure 6 As shown, the layout of the microporous structure, with the center point as the reference, presents a distribution pattern of a certain number of forward spirals and / or reverse spirals in the polar coordinate system.

[0122] The arrangement of micropores can be viewed as being composed of a certain number of alternating forward spirals (clockwise) and reverse spirals (counterclockwise), and these spirals are not perfectly symmetrical.

[0123] This invention, through the layout of a microporous structure and by breaking the traditional method of complete symmetry, can more effectively solve problems such as combustion oscillation.

[0124] In this embodiment, the number of the forward and reverse spirals conforms to the adjacent numbers in the Fibonacci sequence.

[0125] The Fibonacci sequence is 1, 1, 2, 3, 5, 8, 13, 21, 34, 55, 89... Starting from the third number, the next number is the sum of the previous two numbers.

[0126] Figure 5 and Figure 6 This refers to the layout of microporous structures under different initial parameter conditions, such as... Figure 5 and Figure 6 As shown, near the center region, the curvature and pore size distribution of the spiral exhibit certain differences, reflecting the influence of initial parameters on the micropore layout.

[0127] like Figure 5 and Figure 6 The two biomimetic spiral layouts shown have 34 forward spirals and 21 reverse spirals, a number that corresponds to the combination of adjacent numbers in the Fibonacci sequence (21 and 34). This means that the distribution of micropores is not random, but optimized based on mathematical patterns commonly found in nature (such as the Fibonacci sequence). This design approach can achieve more uniform airflow distribution and combustion performance through more complex geometric and hydrodynamic optimizations.

[0128] By utilizing the asymmetric distribution of this spiral and the regularity of the Fibonacci sequence, the layout design of the microporous structure can avoid high-frequency or low-frequency combustion oscillations caused by combustion symmetry, thereby improving combustion stability and efficiency.

[0129] like Figure 5 and Figure 6 As shown, the radius of the micropores gradually increases with the distance from the center point. That is, the micropores closer to the center have smaller diameters, while those farther from the center have larger diameters.

[0130] The pore size of a micropore increases with its distance from the center point. When a fluid flows through a micropore, its pressure and velocity are affected, and adjusting the pore size can compensate for these changes.

[0131] For small holes near the center, the smaller diameter helps maintain uniform fluid flow and avoids excessive spraying in the center due to the short distance and high pressure.

[0132] For large orifices far from the center, the fluid pressure in the area away from the center is usually lower. By increasing the orifice diameter, the consistency of the overall flow rate can be ensured.

[0133] This aperture distribution optimizes the distribution of fluid after it is injected from the micropores, making the fluid mix more uniformly in the combustion chamber, improving combustion efficiency and reducing the risk of incomplete combustion.

[0134] Figure 7A schematic diagram illustrating the combination of micropore distribution and cross-jet combustion organization according to an embodiment of the present invention is shown, such as... Figure 7 As shown, this invention combines micropore distribution and cross-jet combustion organization to optimize burner performance, reduce problems caused by symmetry in traditional annular layouts, and provide a solution for stable and efficient combustion organization.

[0135] The fuel passage 13 is arranged along the fitted curves, which are distributed in a forward or reverse spiral shape, avoiding the symmetric oscillation problem caused by the annular layout of traditional burners.

[0136] The direction of each micro-orifice 14 is determined by a vertical line perpendicular to the fuel channel 13, starting from the center of the micro-orifice, to achieve a cross-jet flow.

[0137] More specifically, each spiral fuel channel 13 has micropores 14 on its side, and the orientation of the micropores 14 is determined by the following method:

[0138] Draw a perpendicular line from the center of the micro-orifice 14 to the spiral fuel channel 13 to define the direction of the micro-orifice, so that the injected fuel is a transverse jet.

[0139] The diameter of each side micro-orifice remains consistent with the original design, ensuring stable fuel injection characteristics.

[0140] The micro-holes 14 on both sides of the fuel passage 13 inject fuel into the combustion zone through a cross-jet flow pattern.

[0141] This invention proposes a combustion chamber structure, an aero-engine, and a gas turbine, which have the following beneficial effects:

[0142] 1) By using the micro-mixing unit structure (fuel channel 13 and its micropores 14) of the hydrogen-based fuel horizontal injection non-premixed jet, low NOx in hydrogen combustion and avoidance of backfire are achieved.

[0143] 2) By utilizing the biomimetic spiral fractal micropore distribution, an asymmetric and non-periodic layout scheme for the burner nozzle micropores is achieved, effectively solving the combustion oscillation problem caused by symmetrical distribution;

[0144] 3) By designing the aperture diameter according to the position of the micropores based on the biomimetic spiral fractal micropore layout, the flame is evenly distributed, and the uniformity of the outlet temperature distribution is improved.

[0145] This invention proposes a combustion chamber structure with the following significant advantages: it improves the design system by introducing an innovative nozzle unit layout design method, which further enriches the design process and system of hydrogen fuel combustion heads; and it can significantly reduce combustion oscillation problems caused by symmetry, thereby effectively extending the service life of test pieces.

[0146] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0147] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more, unless explicitly defined otherwise.

[0148] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0149] The above embodiments are provided for those skilled in the art to implement or use the present invention. Those skilled in the art can make various modifications or changes to the above embodiments without departing from the inventive concept of the present invention. Therefore, the protection scope of the present invention is not limited to the above embodiments, but should be the maximum scope that conforms to the innovative features mentioned in the claims.

Claims

1. A combustion chamber structure, characterized in that, Including the combustion chamber body and head assembly: The head assembly is used to supply fuel; The head assembly includes conduits, a central portion of the head disc cavity, and several fuel passages: The pipe is connected to the central part of the head disc cavity for transporting fuel; The central portion of the head disc cavity is used to guide the fuel distribution to the outer side of the fuel channel; The plurality of fuel channels are connected to the outer side of the central portion of the head disc cavity in an outward radial manner; Each of the fuel channels is provided with a number of micro-holes, which inject fuel in the form of a cross-jet stream.

2. The combustion chamber structure according to claim 1, characterized in that, The streamlines of the fuel channel are fitted according to the layout of the micropores; The micropores are arranged in a biomimetic spiral pattern.

3. The combustion chamber structure according to claim 1 or claim 2, characterized in that, The layout of the microporous structure is based on the center point, and in the polar coordinate system, it presents a distribution pattern of a certain number of forward spirals and / or reverse spirals.

4. The combustion chamber structure according to claim 3, characterized in that, The number of the forward and reverse spirals conforms to the adjacent numbers in the Fibonacci sequence.

5. The combustion chamber structure according to claim 1, characterized in that, The direction of each micro-orifice is determined by a vertical line perpendicular to the fuel channel, starting from the center of the micro-orifice, to achieve a cross-jet flow.

6. The combustion chamber structure according to claim 1, characterized in that, The radius of the micropore increases with the distance from the center point.

7. The combustion chamber structure according to claim 2, characterized in that, The layout characteristic parameters of the biomimetic spiral layout include: Polar radius of the center of the nth microwell β n ; Polar angle Θ of the center of the nth microwell n ; radius r of the nth microwell n .

8. The combustion chamber structure according to claim 7, characterized in that, The polar diameter β of the center of the nth micropore n The corresponding expression is: Where β0 is the initial polar radius and Δβ is the interval setting value.

9. The combustion chamber structure according to claim 7, characterized in that, The polar angle θ of the center of the nth micropore n The corresponding expression is: i n =2πnθ0; Where θ0 is the polar angle difference.

10. The combustion chamber structure according to claim 7, characterized in that, The radius r of the nth micropore n The corresponding expression is: r n ＝kβ n Where k is the radius control parameter.

11. An aircraft engine, characterized in that, It includes at least a compressor, a combustion chamber, and a turbine: The compressor compresses outside air to form high-pressure air which then enters the combustion chamber. The combustion chamber mixes and burns high-pressure air with fuel to form high-temperature gas, which drives the turbine to rotate. The combustion chamber adopts the combustion chamber structure as described in any one of claims 1 to 10.

12. A gas turbine, characterized in that, It includes at least a compressor, a combustion chamber, and a turbine: The compressor compresses outside air to form high-pressure air which then enters the combustion chamber. The combustion chamber mixes and burns high-pressure air with fuel to form high-temperature gas, which drives the turbine to rotate. The combustion chamber adopts the combustion chamber structure as described in any one of claims 1 to 10.

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