A diffuser coupling compressor outlet rectification and flame stabilization and a design method

Abstract

The present application relates to the technical field of gas turbine engine, in particular to a diffuser coupling compressor outlet rectification and flame stabilization and a design method, comprising: an oil injection rod, a plurality of rectification and stabilization vanes and a plurality of oil nozzles, the rectification and stabilization vane is an arc-shaped vane, and its tail edge is a wedge-shaped tail edge, which is arranged between the diffuser casing and the diffuser hub of the diffuser as the terminal stator blade of the compressor and the flame stabilizer of the combustion chamber, the oil injection rod penetrates into the rectification and stabilization vane in the diffuser along the radial direction of the diffuser casing; the plurality of oil nozzles are uniformly arranged on the wedge-shaped tail edge surface of the rectification and stabilization vane, and the oil nozzle and the oil injection rod are communicated in the rectification and stabilization vane. The terminal stator blade of the compressor, the oil injection rod and the flame stabilizer of the combustion chamber are coupled and integrated on the diffuser, thereby reducing the number of parts and the axial size without affecting the thrust of the aero gas turbine engine, and improving the thrust-to-weight ratio of the aero gas turbine engine.

Description

Technical Field

[0001] This invention relates to the field of gas turbine engine technology, specifically to a diffuser and its design method that couples compressor outlet rectification and flame stabilization. Background Technology

[0002] The thrust-to-weight ratio (the ratio of jet thrust to weight) is one of the most critical technical indicators for evaluating the performance level of an aero-gas turbine engine. Driven by the demand for higher thrust-to-weight ratios in aero-gas turbine engines, reducing weight and increasing thrust are the main paths to improve the thrust-to-weight ratio. The compressor, diffuser, and combustion chamber are spatially adjacent components of an aero-gas turbine engine through which airflow passes in sequence. Their weight accounts for approximately 60-80% of the total engine weight, and their axial dimension accounts for approximately 50-70% of the total engine size.

[0003] However, the compressor, diffuser, and combustor configurations have long been clearly defined and relatively independent, resulting in redundant structures and axial dimensions during coupled operation. This hinders the improvement of aero-gas turbine engine performance. On the one hand, traditional compressors require terminal stator blades in the final stage to rectify and diffuse the strong residual swirl airflow, allowing it to flow axially and decelerate for combustion in the combustor. On the other hand, after rectification and diffusion by the terminal stator blades of a traditional compressor, the airflow needs further deceleration and diffusion in the diffuser to participate in combustion. Simultaneously, downstream of the diffuser, fuel injectors, nozzles, flame stabilizers, and flame tubes are required to ensure stable combustion. In summary, the large number and complex functions of the diffuser and its upstream and downstream components in existing aero-gas turbine engines result in large axial dimensions and weight, leading to redundant structures and hindering performance improvements.

[0004] Therefore, there is a need to provide a diffuser and design method that couples compressor outlet rectification and flame stabilization to solve the above problems. Summary of the Invention

[0005] This invention provides a diffuser and its design method that couples compressor outlet rectification and flame stabilization to solve existing problems.

[0006] The first aspect of the present invention provides a diffuser that couples compressor outlet rectification and flame stabilization, the diffuser employing the following technical solution, including:

[0007] Multiple rectifier and flame stabilizer blades, which are arc-shaped blades with wedge-shaped trailing edges, are located between the diffuser casing and the diffuser hub of the diffuser. They serve as both end stator blades of the compressor and flame stabilizers of the combustion chamber. They are used to rectify the residual swirling airflow at the upstream compressor outlet and form a recirculation zone for flame stabilization at the wedge-shaped trailing edge.

[0008] The fuel injection rod extends radially into the rectifier and flame stabilizer blades inside the diffuser casing;

[0009] And multiple fuel injectors, which are evenly distributed on the wedge-shaped trailing edge surface of the rectifier and flame stabilizer blades, and the fuel injectors and fuel injector rods are connected inside the rectifier and flame stabilizer blades.

[0010] A further aspect of the present invention is that the axial length of the leading edge of the rectifier flame stabilizer blade from the diffuser inlet is less than or equal to 1 / 4 of the total axial length of the diffuser; and the axial chord length of the rectifier flame stabilizer blade is greater than or equal to 1 / 3 of the total axial length of the diffuser.

[0011] A further aspect of the present invention is that the leading edge blade angle of the rectifying and stabilizing blade is in the range of 50°~70° off the axial direction.

[0012] A further aspect of the present invention is that the mid-arc line and thickness distribution of the rectifying and flame-stabilizing blades both conform to a monotonic function.

[0013] A further aspect of the present invention is that the dimensionless width ratio of the rectifying flame stabilizer blade is in the range of 0.05 to 0.4, wherein the dimensionless width ratio is the ratio of the width of the wedge trailing edge to the distance between the center lines of two adjacent wedge trailing edges.

[0014] A further aspect of the present invention is that the dimensionless aspect ratio of the diffuser ranges from 0.8 to 5, wherein the dimensionless aspect ratio is the ratio of the total axial length of the diffuser to the inlet height.

[0015] A further aspect of the present invention is that the expansion angle of the upper wall and the expansion angle of the lower wall of the diffuser are both within the range of 0° to 15° deviating from the axial direction.

[0016] A second aspect of the present invention provides a design method for a diffuser that couples compressor outlet rectification and flame stabilization, the method comprising:

[0017] Based on the range of dimensionless aspect ratio and the structure of the diffuser, the inlet height and total axial length of the diffuser are set, and the dimensionless aspect ratio is determined. Based on the diffusion ratio requirement and the range of values ​​for the upper and lower wall expansion angles of the diffuser, the upper and lower wall expansion angles are selected. Based on the diffuser's inlet height, total axial length, upper and lower wall expansion angles, the initial diffuser is designed.

[0018] Based on the airflow distortion, the cosmog direction of the compressor outlet airflow, and the range of values ​​for the leading edge blade angle of the rectifier flame stabilizer, the leading edge blade angle of the rectifier flame stabilizer is obtained; the axial chord length of the rectifier flame stabilizer and the axial length of the leading edge of the rectifier flame stabilizer from the diffuser inlet are determined, and the mid-curvature and thickness distribution of the rectifier flame stabilizer are determined based on a monotonic function; based on the leading edge blade angle, axial chord length, mid-curvature, thickness distribution, and the axial length of the leading edge of the rectifier flame stabilizer from the diffuser inlet, the airfoil of the rectifier flame stabilizer is designed;

[0019] Based on the engine design requirements, the initial diffuser structure, and the range of values ​​for the dimensionless width ratio, the dimensionless width ratio is determined. Based on the dimensionless width ratio, the wedge-shaped trailing edge width of the rectifier flame stabilizer blade and the width between two adjacent rectifier flame stabilizer blades are determined.

[0020] The number of fuel injectors is determined based on the spatial region of the wedge-shaped trailing edge of the rectifier flame stabilizer blades; the air-fuel ratio is determined based on the number of fuel injectors and the airflow in the recirculation zone; the fuel injection quantity of a single fuel injector is obtained based on the air-fuel ratio, the airflow in the recirculation zone, and the number of fuel injectors; the fuel injector diameter and fuel injector rod diameter are obtained based on the fuel injection quantity of a single fuel injector; and the fuel injector rod and fuel injector are designed based on the fuel injector diameter and fuel injector rod diameter.

[0021] Based on the injector rod, injector nozzle, rectifier flame stabilizer blade, wedge trailing edge width of the rectifier flame stabilizer blade, width between two adjacent rectifier flame stabilizer blades, and initial diffuser, a diffuser is designed to couple compressor outlet rectification and flame stabilization.

[0022] A further aspect of the present invention is that the blade profile of the rectifier and flame stabilizer is formed by using a vertical stack based on the leading edge blade angle, axial chord length, mid-arc line, thickness distribution, and axial length of the leading edge of the rectifier and flame stabilizer blade from the diffuser inlet.

[0023] A further aspect of this invention involves obtaining the fuel injection quantity of a single fuel injector based on the air-fuel ratio, the airflow rate in the recirculation zone, and the number of fuel injectors.

[0024] Based on the air-fuel ratio, the air flow rate in the recirculation zone, and the number of fuel injectors, and according to the continuity equation and Bernoulli equation for the mass flow rate of the fuel injectors, the fuel injection quantity of a single fuel injector is obtained.

[0025] The beneficial effects of this invention are:

[0026] This invention designs rectification and flame stabilization blades in the diffuser, replacing both the compressor's end stator blades and the combustion chamber's flame stabilizer. The combustion chamber's fuel injector is also integrated onto the diffuser. This allows the diffuser to function as both the compressor and combustion chamber in a conventional aero-gas turbine engine. Compared to the traditional compressor and combustion chamber configuration, this invention integrates the compressor's end stator blades, the combustion chamber's fuel injector, and the flame stabilizer onto the diffuser. This enables the diffuser to perform rectification, diffusion, fuel injection, flame stabilization, and combustion functions simultaneously. Furthermore, without affecting the aero-gas turbine engine's thrust, this reduces the number of components and axial dimensions, thereby improving the thrust-to-weight ratio of the aero-gas turbine engine. Attached Figure Description

[0027] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] Figure 1 This is a schematic diagram of the structure of a diffuser and compressor used for coupling compressor outlet rectification and flame stabilization according to the present invention.

[0029] Figure 2 This is a schematic diagram of the meridional channel after the diffuser and compressor are integrated in an embodiment of the present invention;

[0030] Figure 3 This is a schematic diagram of the rectifier and flame stabilizer blade in an embodiment of the present invention;

[0031] Figure 4 This is a schematic diagram of the diffuser structure in an embodiment of the present invention;

[0032] Figure 5 This is a schematic diagram of the recirculation zone at the diffuser outlet in an embodiment of the present invention;

[0033] Figure 6 This is a flowchart of a diffuser design method for coupling compressor outlet rectification and flame stabilization according to the present invention.

[0034] In the diagram: 1. Compressor casing; 2. Compressor hub; 3. Upstream compressor rotor; 4. Upstream compressor stator; 5. Downstream compressor rotor; 6. Diffuser; 7. Injector nozzle; 8. Rectifier flame stabilizer blades; 9. Injector rod; 10. Wedge-shaped trailing edge; 11. Diffuser casing; 12. Diffuser hub; 13. Recirculation zone. Detailed Implementation

[0035] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0036] This invention discloses an embodiment of a diffuser that couples compressor outlet rectification and flame stabilization. In this embodiment, since the end stator blades, diffuser, fuel injector rod, and fuel injector of the compressor in an aero-gas turbine engine are all non-rotating components and are arranged sequentially in space, in order to reduce the number of components and axial dimensions of the aero-gas turbine engine and increase its thrust-to-weight ratio, this invention couples and integrates the end stator blades, combustion chamber fuel injector rod, fuel injector, and flame stabilizer of the compressor into the diffuser, forming a diffuser that couples compressor outlet rectification and flame stabilization. Figure 1 As shown, the diffuser coupling compressor outlet rectification and flame stabilization includes: an injection rod 9, multiple injection nozzles 7, and multiple rectification and flame stabilization blades 8. The rectification and flame stabilization blades 8 are arc-shaped blades, and the trailing edge of the rectification and flame stabilization blades 8 is a wedge-shaped trailing edge 10, as shown. Figure 1 As shown, in this embodiment, only the upstream rotor 3, the upstream stator 4, and the downstream rotor 5 of the compressor are provided between the compressor casing 1 and the compressor hub 2 from the inlet to the outlet. The rectifier and flame stabilizer blades 8 in the diffuser 6 serve as both the end stator blades of the compressor and the flame stabilizer of the combustion chamber. That is, in this embodiment, the rectifier and flame stabilizer blades 8 are located between the diffuser casing 11 and the diffuser hub 12 of the diffuser 6. The rectifier and flame stabilizer blades 8 are used to stabilize the upstream compressor... The residual swirl at the turbine outlet is rectified, forming a recirculation zone 13 for flame stabilization at the wedge-shaped trailing edge 10. Multiple rectifying and flame-stabilizing blades 8 are evenly distributed between the diffuser casing 11 and the diffuser hub 12 of the diffuser 6. The fuel injector rod 9 radially penetrates the rectifying and flame-stabilizing blades 8 within the diffuser 6 along the diffuser casing 11. Multiple fuel injectors 7 are evenly distributed on the wedge-shaped trailing edge 10 of the rectifying and flame-stabilizing blades 8, and the fuel injectors 7 and fuel injector rods 9 are connected within the rectifying and flame-stabilizing blades 8. It should be noted that, as... Figure 1 As shown, in this embodiment, the channel between the compressor casing 1 and the compressor hub 2 contains only the upstream rotor 3, the upstream stator 4, and the downstream rotor 5 of the compressor. The end stator blades of the compressor are coupled to the diffuser 6 in this embodiment; that is, the rectifier and flame stabilizer blades 8 in the diffuser 6 also serve as the end stator blades of the compressor. Figure 2 As shown, Figure 2 The diagram shows a meridional channel after the diffuser and compressor are integrated in this embodiment. In this embodiment, the diffuser after coupling has the functions of rectification, diffusion, fuel injection, flame stabilization and combustion.

[0037] For example, in one specific embodiment, the rectification of the compressor outlet airflow is mainly determined by the blade profile of the rectifying and stabilizing blades 8 with wedge-shaped trailing edges 10 inside the diffuser 6, such as... Figure 3 As shown, the airfoil of the rectifier flame stabilizer blade 8 is determined by the axial length from the leading edge of the diffuser 6 (i.e., the inlet of the diffuser 6). axial chord length Mid-arc line Leading edge blade angle and thickness distribution The following factors determine the blade's position in the meridional channel: firstly, the axial length and axial chord length from the diffuser leading edge; secondly, the mid-curve and thickness distribution determine the blade profile, particularly the leading edge blade angle. It directly receives the distorted incoming flow from upstream and determines the deflection of the airflow direction through the mid-arc line, thereby achieving rectification of the upstream airflow with residual swirl. Therefore, in this embodiment, the axial length of the leading edge of the rectifying and stabilizing blade 8 from the diffuser 6 inlet is less than or equal to 1 / 4 of the total axial length of the diffuser 6; the axial chord length of the rectifying and stabilizing blade 8 is greater than or equal to 1 / 3 of the total axial length of the diffuser 6; and the value range of the leading edge blade angle of the rectifying and stabilizing blade 8 is 50°~70° off the axial direction.

[0038] For example, in one specific embodiment, the deceleration and diffusion of the airflow is supported by the airflow channels of the diffuser 6, which have gradually increasing areas. A schematic diagram of the airflow channel structure of the diffuser 6 is shown below. Figure 4 As shown, the change in the airflow channel area of ​​diffuser 6 is mainly affected by the dimensionless aspect ratio. (Total axial length of diffuser 6) Highly comparable to imports (ratio), upper wall expansion angle and lower wall expansion angle The diffuser's deceleration and diffusion capacity is determined by the control of the diffuser. Therefore, in this embodiment, the dimensionless aspect ratio of the diffuser 6 is in the range of 0.8 to 5, and the expansion angles of the upper and lower walls of the diffuser 6 are both in the range of 0° to 15° from the axial direction.

[0039] For example, in one specific embodiment, the flame stabilization required for combustion is primarily determined by the wedge-shaped trailing edge 10 of the rectifier flame stabilizer blades 8 of the diffuser 6, such as... Figure 5 As shown, the air recirculation contact area is affected by the dimensionless width ratio (width of the wedge-shaped trailing edge 10). The distance between the wedge-shaped trailing edge centerline of the two adjacent rectifying flame stabilizer blades 8 The influence of the dimensionless width ratio: A dimensionless width ratio that is too small will result in a smaller air recirculation contact area, leading to insufficient mixing of air and fuel and unstable combustion flame; conversely, a dimensionless width ratio that is too large will result in a larger air recirculation contact area, causing the ratio of the outlet to the inlet area of ​​the diffuser 6 to be too small, affecting the deceleration and diffusion capacity of the diffuser 6, resulting in the airflow still having a high velocity when exiting the diffuser 6, making it difficult to meet the ignition requirements and causing unstable combustion flame; therefore, in this embodiment, the value range of the dimensionless width ratio is 0.05~0.4. The specific dimensionless width ratio can be selected according to the engine design requirements and the specific structure of the diffuser; at the same time, the width of the wedge-shaped trailing edge 10 is ensured. It is larger than the diameter of the fuel injector 9.

[0040] A design method for a diffuser that couples compressor outlet rectification and flame stabilization, such as Figure 6 As shown, it includes:

[0041] S1. Design of the initial diffuser:

[0042] Specifically, based on the range of the dimensionless aspect ratio and the structure of the diffuser, the inlet height and total axial length of the diffuser are set, and the dimensionless aspect ratio is determined. Based on the diffusion ratio requirements and the range of the upper and lower wall expansion angles of the diffuser, the upper and lower wall expansion angles are selected. The initial diffuser is designed based on the inlet height, total axial length, upper and lower wall expansion angles of the diffuser.

[0043] S2. Design the blade profile for the rectifier and flame stabilizer;

[0044] Specifically, based on airflow distortion, the direction of cosmog in the compressor outlet airflow, and the range of values ​​for the leading edge blade angle of the rectifier flame stabilizer blade, the leading edge blade angle of the rectifier flame stabilizer blade is obtained; the axial chord length and the axial length of the leading edge of the rectifier flame stabilizer blade from the diffuser inlet are determined, and the mid-curvature and thickness distribution of the rectifier flame stabilizer blade are determined based on a monotonic function; based on the leading edge blade angle, axial chord length, mid-curvature, thickness distribution, and the axial length of the leading edge of the rectifier flame stabilizer blade from the diffuser inlet, the airfoil of the rectifier flame stabilizer blade is designed;

[0045] For example, the steps to determine the cosine direction of the compressor outlet airflow are as follows: the cosine direction is essentially the rotor rotation direction, that is, the direction of the airflow circumferential velocity.

[0046] For example, in one specific embodiment, the airfoil of the rectifier flame stabilizer is formed by using a vertical stack based on the leading edge blade angle, axial chord length, mid-curvature, thickness distribution, and axial length of the leading edge of the rectifier flame stabilizer from the diffuser inlet. The method of forming the airfoil of the rectifier flame stabilizer using a vertical stack is prior art and will not be described in detail in this embodiment.

[0047] S3. Design the wedge-shaped trailing edge width of the rectifier flame stabilizer blades and the width between two adjacent rectifier flame stabilizer blades;

[0048] Based on the engine design requirements, the initial diffuser structure, and the range of values ​​for the dimensionless width ratio, the dimensionless width ratio is determined. Based on the dimensionless width ratio, the wedge-shaped trailing edge width of the rectifier flame stabilizer blade and the width between two adjacent rectifier flame stabilizer blades are determined.

[0049] S4. Design the fuel injector rod and fuel injector;

[0050] Specifically, the number of fuel injectors is determined based on the spatial region of the wedge-shaped trailing edge of the rectifier flame stabilizer blades; the air-fuel ratio is determined based on the number of fuel injectors and the airflow in the recirculation zone; the fuel injection quantity of a single fuel injector is obtained based on the air-fuel ratio, the airflow in the recirculation zone, and the number of fuel injectors; the fuel injector diameter and fuel injector rod diameter are obtained based on the fuel injection quantity of a single fuel injector; and the fuel injector rod and fuel injector are designed based on the fuel injector diameter and fuel injector rod diameter.

[0051] It should be noted that the fuel supply required for combustion is mainly supported by the injector rod and nozzle embedded in the diffuser's internal support plate. Generally speaking, the main structural parameters of the fuel injection system are determined by the air flow rate in the recirculation zone. Once the air-fuel ratio (the ratio of air to fuel flow rate) is determined, the fuel injection quantity per unit time can be determined. Then, based on the continuity equation and Bernoulli's equation, the diameter of the injector rod and nozzle can be determined.

[0052] For example, in one specific embodiment, the step of determining the number of fuel injectors based on the spatial region of the wedge-shaped trailing edge of the rectifier flame stabilizer blade is as follows: In this embodiment, the specific number of fuel injectors is evenly arranged on the wedge-shaped trailing edge of a certain spatial region to meet the actual engineering requirements.

[0053] For example, in one specific embodiment, the step of obtaining the fuel injection quantity of a single fuel injector based on the air-fuel ratio, the air flow rate in the recirculation zone, and the number of fuel injectors is as follows:

[0054]

[0055] In the formula, The injection flow rate of a single fuel injector. For the air flow rate to participate in combustion, For the number of fuel injectors, It refers to the air-fuel ratio.

[0056] For example, in one specific embodiment, the steps of obtaining the injector diameter and injector rod diameter based on the fuel injection quantity of a single injector are as follows:

[0057] Continuous equations based on fuel injection quantity and fuel injector mass flow rate of a single injector And Bernoulli equation The diameter of the fuel injector can be determined. for:

[0058]

[0059] In the formula, The diameter of the fuel injector; This refers to the overall flow resistance coefficient of the fuel injector; The density of fuel; The nozzle outlet area is based on the nozzle diameter; This is the theoretical fuel injection speed of the fuel injector under a certain internal and external pressure difference; This refers to the pressure difference between the inside and outside of the fuel injector.

[0060] Total fuel flow rate of the fuel injector:

[0061]

[0062] Meanwhile, the continuity equation based on the mass flow rate of the fuel injector rod. ， The diameter of the fuel injector can be determined. :

[0063]

[0064] In the formula, The flow rate of the fuel injector; This is the overall flow resistance coefficient of the fuel injector rod; This represents the average fuel flow rate within the fuel injector.

[0065] At this point, the fuel injector can be designed based on its diameter, and the fuel injector rod can be designed based on its diameter.

[0066] S5. Design a diffuser that couples compressor outlet rectification and flame stabilization;

[0067] Based on the injector rod, injector nozzle, rectifier flame stabilizer blade, wedge trailing edge width of the rectifier flame stabilizer blade, width between two adjacent rectifier flame stabilizer blades, and initial diffuser, a diffuser is designed to couple compressor outlet rectification and flame stabilization.

[0068] In summary, the invention is described above with reference to specific embodiments. It can be concluded that this invention differs from the traditional spatial structure of aero-gas turbine engines, where the compressor stator blades, diffuser, fuel nozzle / flame swirl stabilizer are sequentially distributed along the axial direction. Instead, it adopts a "component integration" approach, coupling and integrating the compressor stator blades, combustion chamber injector, and flame stabilizer into the diffuser. This allows the diffuser to perform functions such as rectification, diffusion, fuel injection, flame stabilization, and combustion. The diffuser configuration of this invention combines the design concepts of the compressor stator blades, diffuser, and fuel injection system. Without affecting the thrust of the aero-gas turbine engine, it reduces the number of components and axial dimensions, improving the thrust-to-weight ratio and other performance levels of the aero-gas turbine engine. It has the advantages of simple component structure, compact axial dimensions, and complete functionality. Furthermore, the diffuser configuration proposed in this invention is not only applicable to the fields of aero-gas turbine engines and jet propulsion devices, but also to the fields of ground-based or shipboard gas turbine systems.

[0069] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A diffuser that couples compressor outlet rectification and flame stabilization, characterized in that, include: Multiple rectifying and flame-stabilizing blades, which are arc-shaped blades with wedge-shaped trailing edges, serve as both end stator blades of the compressor and flame stabilizers of the combustion chamber. They are located between the diffuser casing and the diffuser hub of the diffuser, rectifying the residual swirl airflow at the upstream compressor outlet and forming a recirculation zone for flame stabilization at the wedge-shaped trailing edges. The axial length of the leading edge of the rectifying and flame-stabilizing blade from the diffuser inlet is less than or equal to 1 / 4 of the total axial length of the diffuser. The axial chord length of the rectifying and flame-stabilizing blade is greater than or equal to 1 / 3 of the total axial length of the diffuser. The fuel injection rod extends radially into the rectifier and flame stabilizer blades inside the diffuser casing; And multiple fuel injectors, which are evenly distributed on the wedge-shaped trailing edge surface of the rectifier and flame stabilizer blades, and the fuel injectors and fuel injector rods are connected inside the rectifier and flame stabilizer blades.

2. A diffuser for coupling compressor outlet rectification and flame stabilization according to claim 1, characterized in that, The leading edge blade angle of the rectifier flame stabilizer blades ranges from 50° to 70° off the axial direction.

3. A diffuser for coupling compressor outlet rectification and flame stabilization according to claim 1, characterized in that, The mid-curve and thickness distribution of the rectifier flame stabilizer blades both conform to a monotonic function.

4. A diffuser for coupling compressor outlet rectification and flame stabilization according to claim 1, characterized in that, The dimensionless width ratio of the rectifier flame stabilizer blade ranges from 0.05 to 0.4, where the dimensionless width ratio is the ratio of the width of the wedge trailing edge to the distance between the center lines of two adjacent wedge trailing edges.

5. A diffuser for coupling compressor outlet rectification and flame stabilization according to claim 1, characterized in that, The dimensionless aspect ratio of the diffuser ranges from 0.8 to 5, where the dimensionless aspect ratio is the ratio of the total axial length of the diffuser to the inlet height.

6. A diffuser for coupling compressor outlet rectification and flame stabilization according to claim 1, characterized in that, The expansion angles of the upper and lower walls of the diffuser are both within the range of 0° to 15° off the axial direction.

7. A design method for a diffuser that couples compressor outlet rectification and flame stabilization as described in any one of claims 1-6, characterized in that, include: Based on the range of dimensionless aspect ratio and the structure of the diffuser, the inlet height and total axial length of the diffuser are set, and the dimensionless aspect ratio is determined. Based on the diffusion ratio requirement and the range of values ​​for the upper and lower wall expansion angles of the diffuser, the upper and lower wall expansion angles are selected. Based on the diffuser's inlet height, total axial length, upper and lower wall expansion angles, the initial diffuser is designed. The leading edge angle of the rectifier and flame stabilizer is obtained based on the airflow distortion, the direction of the co-swirl of the compressor outlet airflow, and the range of values ​​for the leading edge blade angle of the rectifier and flame stabilizer. The axial chord length of the rectifier flame stabilizer blade and the axial length of the leading edge of the rectifier flame stabilizer blade from the diffuser inlet are determined, and the mid-arc line and thickness distribution of the rectifier flame stabilizer blade are determined based on monotonic functions. Based on the leading edge blade angle, axial chord length, mid-curvature, thickness distribution, and axial length of the leading edge of the rectifier flame stabilizer blade from the diffuser inlet, the blade profile of the rectifier flame stabilizer blade is designed. Based on the engine design requirements, the initial diffuser structure, and the range of values ​​for the dimensionless width ratio, the dimensionless width ratio is determined. Based on the dimensionless width ratio, the wedge-shaped trailing edge width of the rectifier flame stabilizer blade and the width between two adjacent rectifier flame stabilizer blades are determined. The number of fuel injectors is determined based on the spatial region of the wedge-shaped trailing edge of the rectifier flame stabilizer blades; the air-fuel ratio is determined based on the number of fuel injectors and the airflow in the recirculation zone; the fuel injection quantity of a single fuel injector is obtained based on the air-fuel ratio, the airflow in the recirculation zone, and the number of fuel injectors; the fuel injector diameter and fuel injector rod diameter are obtained based on the fuel injection quantity of a single fuel injector; and the fuel injector rod and fuel injector are designed based on the fuel injector diameter and fuel injector rod diameter. Based on the injector rod, injector nozzle, rectifier flame stabilizer blade, wedge trailing edge width of the rectifier flame stabilizer blade, width between two adjacent rectifier flame stabilizer blades, and initial diffuser, a diffuser is designed to couple compressor outlet rectification and flame stabilization.

8. The diffuser design method for coupling compressor outlet rectification and flame stabilization according to claim 7, characterized in that, Based on the leading edge blade angle, axial chord length, mid-curve, thickness distribution, and axial length of the leading edge of the rectifier flame stabilizer blade from the diffuser inlet, the blade profile of the rectifier flame stabilizer blade is formed by vertical stacking.

9. The design method of a diffuser coupling compressor outlet rectification and flame stabilization according to claim 7, characterized in that, Based on the air-fuel ratio, airflow in the recirculation zone, and the number of fuel injectors, the steps to obtain the fuel injection quantity of a single fuel injector are as follows: Based on the air-fuel ratio, the air flow rate in the recirculation zone, and the number of fuel injectors, and according to the continuity equation and Bernoulli equation for the mass flow rate of the fuel injectors, the fuel injection quantity of a single fuel injector is obtained.

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