Multi-parameter pneumatic construction method and system for small-windward-area compressor stator

Abstract

The invention relates to the technical field of aero-engines, and discloses a small-windward-area compressor stator multi-parameter pneumatic construction method and system.The front edge line blade tip point of the meridian projection of a small-windward-area compressor stator is moved forwards, the rear edge line blade tip point is moved backwards, the consistency of the stator tip part can be increased, and the consistency of the stator tip part is improved; flow separation at the tip of the stator is reduced, so that the efficiency and the stability margin of the small-windward-area compressor are improved. Besides, under the condition of the same hub ratio, the consistency of the stator root of the small-windward-area gas compressor can be reduced by further reducing the number of the stator blades, so that the flow capacity of the stator root is improved, and the efficiency and the stability margin of the small-windward-area gas compressor are further improved. According to the method, the design efficiency can be improved, the design period can be shortened, and the working envelope of the engine can be improved; particularly, the stator can be directly used for designing a small-windward-area compressor stator, and the windward area of an engine inlet can be effectively reduced, so that the purpose of reducing weight is achieved.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and discloses a multi-parameter aerodynamic construction method and system for a stator of a compressor with a small frontal area. Background Art

[0002] Aircraft engines require compressor components to be highly efficient and lightweight. To adapt to this trend, compressors are moving towards smaller inlet sizes, that is, smaller inlet frontal areas. Usually, to ensure the same inlet axial speed, the smaller the inlet frontal area, the smaller the inlet hub ratio.

[0003] At present, the inlet hub ratio of conventional frontal area compressor stators is usually 0.6-0.7. The conventional range of stator design parameters cannot meet the aerodynamic design requirements of small frontal area compressor stators. Summary of the invention

[0004] The purpose of the present invention is to provide a multi-parameter aerodynamic construction method and system for a small frontal area compressor stator, which can reduce the flow separation at the tip of the small frontal area compressor stator, increase the flow capacity at the root of the stator under the same hub ratio, and further improve the efficiency and stability margin of the small frontal area compressor. The method has high design efficiency, short design cycle, and can improve the working envelope of the engine; in particular, it can be directly used for the design of a small frontal area compressor stator, which can effectively reduce the engine inlet frontal area, thereby achieving the purpose of weight reduction.

[0005] In order to achieve the above technical effects, the technical solution adopted by the present invention is:

[0006] A multi-parameter aerodynamic construction method for a small frontal area compressor stator, comprising:

[0007] According to the design index requirements of the small windward area compressor, the flow coefficient distribution law of the inlet stage of the small windward area compressor is constructed, so that the flow coefficient of the small windward area compressor is gradually reduced from the first stage to the outlet stage, and the first stage flow coefficient of the small windward area compressor is 1.27 to 1.6 times that of the first stage flow coefficient of the conventional compressor, and the first stage flow coefficient of the small windward area compressor is 0.7 to 0.8; wherein, the small windward area compressor has a unit inlet annular flow of 200 to 220 kg / (sm 2 ), a compressor with a stator inlet hub ratio of 0.4 to 0.5; the conventional compressor has a unit inlet annular flow rate of 160 to 180 kg / (sm 2 ), compressors with a stator inlet hub ratio of 0.6-0.7;

[0008] According to the ratio H of the flow coefficients of the first stage of the small frontal area compressor and the first stage of the conventional compressor, under the condition that the leading edge point and the trailing edge point of the blade root of the small frontal area compressor are kept consistent with the leading edge point and the trailing edge point of the blade root of the conventional compressor, the meridian projection distribution law of the stator of the small frontal area compressor is adjusted so that the tip apex of the leading edge line of the stator of the small frontal area compressor moves forward relative to the tip apex of the leading edge line of the stator of the conventional compressor, and the forward movement distance is 0.16H times the axial chord length of the stator tip of the conventional compressor; and the tip apex of the trailing edge line of the stator of the small frontal area compressor moves backward relative to the tip apex of the trailing edge line of the stator of the conventional compressor, and the backward movement distance is 0.075H times the axial chord length of the stator tip of the conventional compressor;

[0009] According to the design index requirements of the small frontal area compressor, the attack angle, backward angle, density and mid-arc curvature ratio of the small frontal area compressor stator are determined, and the blade shape of the small frontal area compressor stator is constructed.

[0010] Furthermore, the flow coefficient of the small frontal area compressor drops to within 0.55 starting from the middle stage, and the middle stage number is the number of the middle stages of the small frontal area compressor, is the total number of compressor stages, and is a rounding function.

[0011] Furthermore, the consistency of the root section of the stator blade of the small frontal area compressor is 1.1 to 1.4 times that of the root section of the stator blade of the conventional compressor, the consistency of the tip section of the stator blade of the small frontal area compressor is 0.85 to 0.98 times that of the tip section of the stator blade of the conventional compressor, and the consistency distribution of the stator of the small frontal area compressor has a smooth transition from the blade root to the blade tip.

[0012] Furthermore, an increase in the angle of attack of the cross-section of the stator blade root of the small frontal area compressor relative to the angle of attack of the cross-section of the stator blade root of the conventional compressor is 20% to 100% of the angle of attack of the cross-section of the stator blade root of the conventional compressor, a relative deviation between the angle of attack of the cross-section of 50% of the blade height and above of the stator of the small frontal area compressor and the angle of attack of the cross-section of 50% of the blade height and above of the stator of the conventional compressor is less than a first preset threshold, and the angle of attack of the stator of the small frontal area compressor has a smooth transition from the blade root to the cross-section of 50% of the blade height.

[0013] Furthermore, the mid-arc curvature ratio of the cross-section of the blade root of the stator of the small frontal area compressor is 1.1 to 1.25 times the mid-arc curvature ratio of the cross-section of the blade root of the stator of the conventional compressor, the relative deviation between the mid-arc curvature ratio of the cross-section of 50% of the blade height and above of the stator of the small frontal area compressor and the mid-arc curvature ratio of the cross-section of 50% of the blade height and above of the stator of the conventional compressor is less than a second preset threshold value, and the mid-arc curvature ratio of the stator of the small frontal area compressor from the blade root to the cross-section of 50% of the blade height has a smooth transition.

[0014] Furthermore, the trailing angle of the root section of the stator blade of the small frontal area compressor is 1.1 to 1.25 times the trailing angle of the root section of the stator blade of a conventional compressor, the relative deviation between the trailing angle of the section at 50% of the blade height and above of the stator blade of the small frontal area compressor and the trailing angle of the section at 50% of the blade height and above of the stator blade of the conventional compressor is less than a third preset threshold value, and the trailing angle of the stator blade of the small frontal area compressor transitions smoothly from the blade root to the section at 50% of the blade height.

[0015] In order to achieve the above technical effects, the present invention also provides a multi-parameter aerodynamic construction system for a small frontal area compressor stator, comprising:

[0016] The flow coefficient distribution module is used to construct the flow coefficient distribution law of the inlet stage of the small windward area compressor according to the design index requirements of the small windward area compressor, so that the flow coefficient of the small windward area compressor is gradually reduced from the first stage to the outlet stage, and the first stage flow coefficient of the small windward area compressor is 1.27 to 1.6 times the first stage flow coefficient of the conventional compressor, and the first stage flow coefficient of the small windward area compressor is 0.7 to 0.8; wherein, the small windward area compressor has a unit inlet annular flow of 200 to 220 kg / (sm 2 ), a compressor with a stator inlet hub ratio of 0.4 to 0.5; the conventional compressor has a unit inlet annular flow rate of 160 to 180 kg / (sm 2 ), compressors with a stator inlet hub ratio of 0.6-0.7;

[0017] A first adjustment module is used to adjust the meridian projection distribution law of the stator of the small frontal area compressor according to the ratio H of the flow coefficient of the first stage of the small frontal area compressor and the first stage of the conventional compressor, while keeping the leading edge point and the trailing edge point of the blade root of the small frontal area compressor consistent with the leading edge point and the trailing edge point of the blade root of the conventional compressor, so that the tip apex of the leading edge line of the stator of the small frontal area compressor moves forward relative to the tip apex of the leading edge line of the stator of the conventional compressor, and the forward movement distance is 0.16H times the axial chord length of the stator tip of the conventional compressor; and the tip apex of the trailing edge line of the stator of the small frontal area compressor moves backward relative to the tip apex of the trailing edge line of the stator of the conventional compressor, and the backward movement distance is 0.075H times the axial chord length of the stator tip of the conventional compressor;

[0018] The blade shape construction module is used to determine the attack angle, backward angle, density and mid-arc curvature ratio of the stator of the small frontal area compressor according to the design index requirements of the small frontal area compressor, and construct the blade shape of the stator of the small frontal area compressor.

[0019] Furthermore, in the flow coefficient allocation module, the flow coefficient of the small frontal area compressor is controlled to drop to within 0.55 starting from the intermediate stage, and the intermediate stage number is the number of intermediate stages of the small frontal area compressor, which is the total number of compressor stages and is a rounding function.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. The present invention moves the leading edge line blade tip point of the meridional projection of the stator of the small frontal area compressor forward and moves the trailing edge line blade tip apex backward, so as to increase the consistency of the stator tip to reduce the flow separation at the stator tip, thereby improving the efficiency and stability margin of the small frontal area compressor; in addition, under the same hub ratio condition, the consistency of the stator root of the small frontal area compressor can be reduced by further reducing the number of stator blades, thereby increasing the flow capacity of the stator root and further improving the efficiency and stability margin of the small frontal area compressor.

[0022] 2. The multi-parameter aerodynamic construction method of a small frontal area compressor stator of the present invention can not only improve the design efficiency and shorten the design cycle, but also improve the working envelope of the engine; in particular, it can be directly used in the design of a small frontal area compressor stator, which can effectively reduce the engine inlet frontal area, thereby achieving the purpose of weight reduction. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 Schematic diagram of flow coefficient distribution of a small frontal area compressor and a conventional compressor in Example 2;

[0024] Figure 2 Schematic diagram of the position relationship between the leading edge line and the trailing edge line of the stator of a small frontal area compressor and a conventional compressor in Example 2;

[0025] Figure 3 Schematic diagram of stator density distribution of a small frontal area compressor and a conventional compressor in Example 2;

[0026] Figure 4 Schematic diagram of the stator attack angle distribution of a small frontal area compressor and a conventional compressor in Example 2;

[0027] Figure 5 Schematic diagram of the distribution of the camber ratio of the stator of the small frontal area compressor and the conventional compressor in Example 2;

[0028] Figure 6 Schematic diagram of the stator backward angle distribution of a small frontal area compressor and a conventional compressor in Example 2;

[0029] Among them, 1. Optimization area; 2. Non-optimization area; 3. Topological structure; 4. Skeleton structure; 5. Geometric model building module; 6. Area division module; 7. Data acquisition module; 8. Optimization module; 9. Output module. DETAILED DESCRIPTION

[0030] The present invention is further described in detail below in conjunction with the embodiments and drawings. However, it should not be understood that the scope of the above subject matter of the present invention is limited to the following embodiments, and all technologies realized based on the content of the present invention belong to the scope of the present invention.

[0031] Example 1

[0032] A multi-parameter aerodynamic construction method for a small frontal area compressor stator, comprising:

[0033] According to the design index requirements of the small windward area compressor, the flow coefficient distribution law of the inlet stage of the small windward area compressor is constructed, so that the flow coefficient of the small windward area compressor is gradually reduced from the first stage to the outlet stage, and the first stage flow coefficient of the small windward area compressor is 1.27 to 1.6 times that of the first stage flow coefficient of the conventional compressor, and the first stage flow coefficient of the small windward area compressor is 0.7 to 0.8; wherein, the small windward area compressor has a unit inlet annular flow of 200 to 220 kg / (sm 2 ), a compressor with a stator inlet hub ratio of 0.4 to 0.5; the conventional compressor has a unit inlet annular flow rate of 160 to 180 kg / (sm 2 ), compressors with a stator inlet hub ratio of 0.6-0.7;

[0034] According to the ratio H of the flow coefficients of the first stage of the small frontal area compressor and the first stage of the conventional compressor, under the condition that the leading edge point and the trailing edge point of the blade root of the small frontal area compressor are kept consistent with the leading edge point and the trailing edge point of the blade root of the conventional compressor, the meridian projection distribution law of the stator of the small frontal area compressor is adjusted so that the tip apex of the leading edge line of the stator of the small frontal area compressor moves forward relative to the tip apex of the leading edge line of the stator of the conventional compressor, and the forward movement distance is 0.16H times the axial chord length of the stator tip of the conventional compressor; and the tip apex of the trailing edge line of the stator of the small frontal area compressor moves backward relative to the tip apex of the trailing edge line of the stator of the conventional compressor, and the backward movement distance is 0.075H times the axial chord length of the stator tip of the conventional compressor;

[0035] According to the design index requirements of the small frontal area compressor, the attack angle, backward angle, density and mid-arc curvature ratio of the small frontal area compressor stator are determined, and the blade shape of the small frontal area compressor stator is constructed.

[0036] In this embodiment, by moving the leading edge line blade tip point of the small frontal area compressor stator meridian projection forward and the trailing edge line blade tip apex backward, the consistency of the stator tip can be increased to reduce the flow separation at the stator tip, thereby improving the efficiency and stability margin of the small frontal area compressor; in addition, under the same hub ratio condition, the consistency of the stator root of the small frontal area compressor can be reduced by further reducing the number of stator blades, thereby increasing the flow capacity of the stator root and further improving the efficiency and stability margin of the small frontal area compressor. The multi-parameter aerodynamic construction method of the small frontal area compressor stator of the present invention can not only improve the design efficiency and shorten the design cycle, but also improve the working envelope of the engine; in particular, it can be directly used in the design of the small frontal area compressor stator, which can effectively reduce the engine inlet frontal area, thereby achieving the purpose of weight reduction.

[0037] Based on the same inventive concept, this embodiment also provides a multi-parameter aerodynamic construction system for a small frontal area compressor stator, comprising:

[0038] The flow coefficient distribution module is used to construct the flow coefficient distribution law of the inlet stage of the small windward area compressor according to the design index requirements of the small windward area compressor, so that the flow coefficient of the small windward area compressor is gradually reduced from the first stage to the outlet stage, and the first stage flow coefficient of the small windward area compressor is 1.27 to 1.6 times the first stage flow coefficient of the conventional compressor, and the first stage flow coefficient of the small windward area compressor is 0.7 to 0.8; wherein, the small windward area compressor has a unit inlet annular flow of 200 to 220 kg / (sm 2 ), a compressor with a stator inlet hub ratio of 0.4 to 0.5; the conventional compressor has a unit inlet annular flow rate of 160 to 180 kg / (sm 2 ), compressors with a stator inlet hub ratio of 0.6-0.7;

[0039] A first adjustment module is used to adjust the meridian projection distribution law of the stator of the small frontal area compressor according to the ratio H of the flow coefficient of the first stage of the small frontal area compressor and the first stage of the conventional compressor, while keeping the leading edge point and the trailing edge point of the blade root of the small frontal area compressor consistent with the leading edge point and the trailing edge point of the blade root of the conventional compressor, so that the tip apex of the leading edge line of the stator of the small frontal area compressor moves forward relative to the tip apex of the leading edge line of the stator of the conventional compressor, and the forward movement distance is 0.16H times the axial chord length of the stator tip of the conventional compressor; and the tip apex of the trailing edge line of the stator of the small frontal area compressor moves backward relative to the tip apex of the trailing edge line of the stator of the conventional compressor, and the backward movement distance is 0.075H times the axial chord length of the stator tip of the conventional compressor;

[0040] The blade shape construction module is used to determine the attack angle, backward angle, density and mid-arc curvature ratio of the stator of the small frontal area compressor according to the design index requirements of the small frontal area compressor, and construct the blade shape of the stator of the small frontal area compressor.

[0041] Example 2

[0042] See also Figure 1-Figure 6 In this embodiment, the stator aerodynamic design of a small frontal area compressor with a stator inlet hub ratio of 0.45 is taken as an example to explain in detail the process of the multi-parameter aerodynamic construction method of the stator of a small frontal area compressor of the present invention; wherein, the small frontal area compressor has a unit inlet annular flow rate of 200-220 kg / (sm 2 ), a compressor with a stator inlet hub ratio of 0.4 to 0.5; the conventional compressor has a unit inlet annular flow rate of 160 to 180 kg / (sm 2 ), the compressor with a stator inlet hub ratio of 0.6-0.7, and both stages are 9; the specific design steps include:

[0043] Step 1: According to the design index requirements of the small windward area compressor, a flow coefficient distribution law of the inlet stage of the small windward area compressor is constructed, so that the flow coefficient of the small windward area compressor is gradually reduced from the first stage to the outlet stage, and the first stage flow coefficient of the small windward area compressor is 1.27 to 1.6 times the first stage flow coefficient of the conventional compressor, and the first stage flow coefficient of the small windward area compressor is 0.7 to 0.8;

[0044] The flow coefficient distribution of the small frontal area compressor and the conventional compressor in this embodiment is as follows: Figure 1 As shown, Figure 1 It can be seen that the flow coefficient of the first stage of the conventional compressor is 0.529. According to the proportional range, the first stage flow coefficient of the small frontal area compressor is selected to be 1.46 times the first stage flow coefficient of the conventional compressor. Therefore, the flow coefficient of the first stage of the small frontal area compressor in this embodiment is determined to be 0.773.

[0045] In addition, starting from the middle stage, the flow coefficient drops to less than 0.55. U mid is the technology of the intermediate stage of the small frontal area compressor, N is the total number of compressor stages, and Round(*) is a rounding function; for example, in this embodiment, for a 9-stage compressor, the intermediate stage is the fifth stage, such as Figure 1 As shown, the flow coefficient of the middle stage (fifth stage) of the small frontal area compressor is 0.516, which is within 0.55.

[0046] Step 2: According to the ratio H of the flow coefficients of the first stage of the small frontal area compressor and the first stage of the conventional compressor, while keeping the leading edge point and the trailing edge point of the blade root of the small frontal area compressor consistent with the leading edge point and the trailing edge point of the blade root of the conventional compressor, adjust the meridian projection distribution law of the stator of the small frontal area compressor, so that the tip apex of the leading edge line of the stator of the small frontal area compressor moves forward relative to the tip apex of the leading edge line of the stator of the conventional compressor, and the forward movement distance is 0.16H times the axial chord length of the stator tip of the conventional compressor; and the tip apex of the trailing edge line of the stator of the small frontal area compressor moves backward relative to the tip apex of the trailing edge line of the stator of the conventional compressor, and the backward movement distance is 0.075H times the axial chord length of the stator tip of the conventional compressor;

[0047] In this embodiment, the ratio of the flow coefficient of the first stage of the small frontal area compressor to the first stage of the conventional compressor is H=1.46, that is, the relative forward displacement distance of the tip apex of the stator leading edge line of the small frontal area compressor is 23.36% of the axial chord length of the conventional tip; the relative backward displacement distance of the tip apex of the stator trailing edge line of the small frontal area compressor is 10.95% of the axial chord length of the stator tip of the conventional frontal area compressor. Figure 2 As shown, the conventional tip axial chord length in this embodiment is 0.077 meters, so the forward displacement distance of the blade tip apex of the small frontal area compressor stator leading edge line relative to the blade tip apex of the conventional compressor stator leading edge line is 0.018 meters; the backward displacement distance of the blade tip apex of the small frontal area compressor stator trailing edge line relative to the blade tip apex of the conventional compressor stator trailing edge line is 0.0084 meters.

[0048] Step 3: According to the design index requirements of the small frontal area compressor, the attack angle, backward angle, density and mid-arc curvature ratio of the small frontal area compressor stator are determined, and the blade shape of the small frontal area compressor stator is constructed;

[0049] like Figure 3 As shown, in this embodiment, the consistency of the root section of the stator blade of the small frontal area compressor is 1.1 to 1.4 times that of the stator blade root section of the conventional compressor, the consistency of the tip section of the stator blade of the small frontal area compressor is 0.85 to 0.98 times that of the stator blade tip section of the conventional compressor, and the consistency distribution of the stator of the small frontal area compressor has a smooth transition from the blade root to the blade tip.

[0050] like Figure 4As shown, the increase of the angle of attack of the root section of the stator blade of the small frontal area compressor relative to the angle of attack of the root section of the stator blade of the conventional compressor is 20% to 100% of the angle of attack of the root section of the stator blade of the conventional compressor, the relative deviation of the angle of attack of the section of 50% of the blade height and above of the stator blade of the small frontal area compressor and the angle of attack of the section of 50% of the blade height and above of the stator blade of the conventional compressor is less than the first preset threshold value, and the angle of attack of the stator blade of the small frontal area compressor has a smooth transition from the blade root to the section of 50% of the blade height.

[0051] like Figure 5 As shown, the mid-arc curvature ratio of the small frontal area compressor stator blade root section is 1.1 to 1.25 times the mid-arc curvature ratio of the conventional compressor stator blade root section, the relative deviation between the mid-arc curvature ratio of the section at 50% of the blade height and above of the small frontal area compressor stator and the mid-arc curvature ratio of the section at 50% of the blade height and above of the conventional compressor stator is less than a second preset threshold value, and the mid-arc curvature ratio of the small frontal area compressor stator from the blade root to the section at 50% of the blade height has a smooth transition.

[0052] like Figure 6 As shown, the trailing angle of the small frontal area compressor stator blade root section is 1.1 to 1.25 times the trailing angle of the conventional compressor stator blade root section, the relative deviation between the trailing angle of the section at 50% of the blade height and above of the small frontal area compressor stator and the trailing angle of the section at 50% of the blade height and above of the conventional compressor stator is less than the third preset threshold, and the trailing angle of the small frontal area compressor stator from the blade root to the section at 50% of the blade height transitions smoothly.

[0053] In this embodiment, the value ranges of the first preset threshold, the second preset threshold and the third preset threshold are all less than 1%, so as to ensure that the angle of attack, the trailing angle and the mid-arc curvature ratio of the section of 50% of the blade height and above of the stator of the small frontal area compressor are equivalent to those of a conventional compressor.

[0054] Compared with conventional compressor stator blades, this embodiment can solve the circulation problem caused by high root consistency due to small frontal area and flow separation problem caused by low tip consistency by designing the attack angle, backward angle, consistency and mid-arc curvature ratio of the compressor stator with small frontal area, thereby achieving the purpose of improving the compressor efficiency and stability margin.

[0055] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A multi-parameter aerodynamic construction method for a small frontal area compressor stator, characterized in that: include: According to the design index requirements of the small windward area compressor, the flow coefficient distribution law of the inlet stage of the small windward area compressor is constructed, so that the flow coefficient of the small windward area compressor is gradually reduced from the first stage to the outlet stage, and the first stage flow coefficient of the small windward area compressor is 1.27 to 1.6 times that of the first stage flow coefficient of the conventional compressor, and the first stage flow coefficient of the small windward area compressor is 0.7 to 0.8; wherein, the small windward area compressor has a unit inlet annular flow of 200 to 220 kg / (sm 2 ), a compressor with a stator inlet hub ratio of 0.4 to 0.5; the conventional compressor has a unit inlet annular flow rate of 160 to 180 kg / (sm 2 ), compressors with a stator inlet hub ratio of 0.6-0.7; According to the ratio H of the flow coefficients of the first stage of the small frontal area compressor and the first stage of the conventional compressor, under the condition that the leading edge point and the trailing edge point of the blade root of the small frontal area compressor are kept consistent with the leading edge point and the trailing edge point of the blade root of the conventional compressor, the meridian projection distribution law of the stator of the small frontal area compressor is adjusted so that the tip apex of the leading edge line of the stator of the small frontal area compressor moves forward relative to the tip apex of the leading edge line of the stator of the conventional compressor, and the forward movement distance is 0.16H times the axial chord length of the stator tip of the conventional compressor; and the tip apex of the trailing edge line of the stator of the small frontal area compressor moves backward relative to the tip apex of the trailing edge line of the stator of the conventional compressor, and the backward movement distance is 0.075H times the axial chord length of the stator tip of the conventional compressor; According to the design index requirements of the small frontal area compressor, the attack angle, backward angle, density and mid-arc curvature ratio of the small frontal area compressor stator are determined, and the blade shape of the small frontal area compressor stator is constructed.

2. The multi-parameter aerodynamic construction method for a small frontal area compressor stator according to claim 1, characterized in that: The flow coefficient of the small frontal area compressor drops to less than 0.55 from the middle stage. U mid is the number of intermediate stages of the small frontal area compressor, N is the total number of compressor stages, and Round(*) is a rounding function.

3. The multi-parameter aerodynamic construction method for a small frontal area compressor stator according to claim 1, characterized in that: The consistency of the root section of the stator blade of the small frontal area compressor is 1.1 to 1.4 times that of the root section of the stator blade of the conventional compressor, the consistency of the tip section of the stator blade of the small frontal area compressor is 0.85 to 0.98 times that of the tip section of the stator blade of the conventional compressor, and the consistency distribution of the stator of the small frontal area compressor has a smooth transition from the blade root to the blade tip.

4. The multi-parameter aerodynamic construction method for a small frontal area compressor stator according to claim 1, characterized in that: The increase in the angle of attack of the root section of the stator blade of the small frontal area compressor relative to the angle of attack of the root section of the stator blade of the conventional compressor is 20% to 100% of the angle of attack of the root section of the stator blade of the conventional compressor, the relative deviation between the angle of attack of the section of 50% of the blade height and above of the stator blade of the small frontal area compressor and the angle of attack of the section of 50% of the blade height and above of the stator blade of the conventional compressor is less than a first preset threshold, and the angle of attack of the stator blade of the small frontal area compressor has a smooth transition from the blade root to the section of 50% of the blade height.

5. The multi-parameter aerodynamic construction method for a small frontal area compressor stator according to claim 1, characterized in that: The mid-arc curvature ratio of the blade root section of the small frontal area compressor stator is 1.1 to 1.25 times the mid-arc curvature ratio of the blade root section of the conventional compressor stator, the relative deviation between the mid-arc curvature ratio of the section at 50% of the blade height and above of the small frontal area compressor stator and the mid-arc curvature ratio of the section at 50% of the blade height and above of the conventional compressor stator is less than a second preset threshold, and the mid-arc curvature ratio of the small frontal area compressor stator from the blade root to the section at 50% of the blade height has a smooth transition.

6. The multi-parameter aerodynamic construction method for a small frontal area compressor stator according to claim 1, characterized in that: The trailing angle of the root section of the stator blade of the small frontal area compressor is 1.1 to 1.25 times the trailing angle of the root section of the stator blade of the conventional compressor, the relative deviation between the trailing angle of the section at 50% of the blade height and above of the stator blade of the small frontal area compressor and the trailing angle of the section at 50% of the blade height and above of the stator blade of the conventional compressor is less than the third preset threshold value, and the trailing angle of the stator blade of the small frontal area compressor has a smooth transition from the blade root to the section at 50% of the blade height.

7. A multi-parameter aerodynamic construction system for a small frontal area compressor stator, characterized in that: include: The flow coefficient distribution module is used to construct the flow coefficient distribution law of the inlet stage of the small windward area compressor according to the design index requirements of the small windward area compressor, so that the flow coefficient of the small windward area compressor is gradually reduced from the first stage to the outlet stage, and the first stage flow coefficient of the small windward area compressor is 1.27 to 1.6 times the first stage flow coefficient of the conventional compressor, and the first stage flow coefficient of the small windward area compressor is 0.7 to 0.8; wherein, the small windward area compressor has a unit inlet annular flow of 200 to 220 kg / (sm 2 ), a compressor with a stator inlet hub ratio of 0.4 to 0.5; the conventional compressor has a unit inlet annular flow rate of 160 to 180 kg / (sm 2 ), compressors with a stator inlet hub ratio of 0.6-0.7; A first adjustment module is used to adjust the meridian projection distribution law of the stator of the small frontal area compressor according to the ratio H of the flow coefficient of the first stage of the small frontal area compressor and the first stage of the conventional compressor, while keeping the leading edge point and the trailing edge point of the blade root of the small frontal area compressor consistent with the leading edge point and the trailing edge point of the blade root of the conventional compressor, so that the tip apex of the leading edge line of the stator of the small frontal area compressor moves forward relative to the tip apex of the leading edge line of the stator of the conventional compressor, and the forward movement distance is 0.16H times the axial chord length of the stator tip of the conventional compressor; and the tip apex of the trailing edge line of the stator of the small frontal area compressor moves backward relative to the tip apex of the trailing edge line of the stator of the conventional compressor, and the backward movement distance is 0.075H times the axial chord length of the stator tip of the conventional compressor; The blade shape construction module is used to determine the attack angle, backward angle, density and mid-arc curvature ratio of the stator of the small frontal area compressor according to the design index requirements of the small frontal area compressor, and construct the blade shape of the stator of the small frontal area compressor.

8. The multi-parameter aerodynamic construction system for a small frontal area compressor stator according to claim 7, characterized in that: In the flow coefficient distribution module, the flow coefficient of the small frontal area compressor is controlled to be reduced to within 0.55 from the middle stage. U mid is the number of intermediate stages of the small frontal area compressor, N is the total number of compressor stages, and Round(*) is a rounding function.

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