A small wind area compressor stator multi-parameter aerodynamic construction method and system

Abstract

The application relates to the technical field of aero-engines, and discloses a small-wind-area compressor stator multi-parameter aerodynamic construction method and system, wherein the tip point of a leading edge line of a meridian projection of a small-wind-area compressor stator is moved forward, and the tip point of a trailing edge line is moved backward, so that the solidity of the tip of the stator is increased, the flow separation of the tip of the stator is reduced, the efficiency and the stability margin of the small-wind-area compressor are improved, and in the condition of the same hub ratio, the number of stator blades is further reduced, the solidity of the root of the small-wind-area compressor stator is reduced, the flow capacity of the root of the stator is increased, the efficiency and the stability margin of the small-wind-area compressor are further improved, the design efficiency is improved, the design period is shortened, the working envelope of the engine is improved, the small-wind-area compressor stator design can be directly used, the engine inlet wind area can be effectively reduced, and the weight reduction purpose is achieved.

Description

Technical Field

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

[0002] Aircraft engines require highly efficient and lightweight compressor components. To adapt to this trend, compressors are developing towards smaller inlet sizes, meaning smaller inlet frontal areas. Generally, to maintain the same inlet axial velocity, the smaller the inlet frontal area, the smaller the inlet hub ratio.

[0003] Currently, 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 present invention aims to provide a multi-parameter aerodynamic design method and system for a small frontal area compressor stator. This method can reduce flow separation at the stator tip of a small frontal area compressor, increase the flow capacity at the stator root under the same hub-wheel ratio, and further improve the efficiency and stability margin of the small frontal area compressor. This method has high design efficiency, a short design cycle, and can improve the engine's operating envelope. In particular, it can be directly applied to the design of small frontal area compressor stators, effectively reducing the engine inlet frontal area, thereby achieving the goal 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 frontal area compressor, a flow coefficient distribution law of the inlet stage of the small frontal area compressor is constructed, so that the flow coefficient of the small frontal area compressor decreases step by step from the first stage to the outlet stage. The first stage flow coefficient of the small frontal area compressor is 1.27 to 1.6 times that of the first stage flow coefficient of a conventional compressor, and the first stage flow coefficient of the small frontal area compressor is 0.7 to 0.8; wherein, the unit inlet annular flow of the small frontal area compressor is 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 ), compressor with stator import hub ratio of 0.6-0.7;

[0008] According to a 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 maintaining the positions of the leading edge point and the trailing edge point of the blade root of the small frontal area compressor and 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 is moved 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 is moved 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, trailing 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 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 smoothly transitions from the blade root to the blade tip.

[0012] Furthermore, 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 a conventional compressor is 20% to 100% of the angle of attack of the root section of the stator blade of a 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 value, and the angle of attack of the stator blade of the small frontal area compressor transitions smoothly from the blade root to the section of 50% of the blade height.

[0013] Furthermore, the camber camber ratio of the blade root section of the small frontal area compressor stator is 1.1 to 1.25 times the camber camber ratio of the blade root section of the conventional compressor stator, the relative deviation between the camber camber ratio of the section at 50% of the blade height and above of the small frontal area compressor stator and the camber camber 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 camber camber 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.

[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 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 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] 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 a flow coefficient distribution rule for the inlet stage of the small frontal area compressor according to the design index requirements of the small frontal area compressor, so that the flow coefficient of the small frontal area compressor decreases step by step from the first stage to the outlet stage. The first stage flow coefficient of the small frontal 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 frontal area compressor is 0.7 to 0.8; wherein, the unit inlet annular flow of the small frontal area compressor is 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 ), compressor with stator import hub ratio of 0.6-0.7;

[0017] a first adjustment module, configured to adjust, based on a ratio H of the flow coefficients of the first stage of the small frontal area compressor to the first stage of the conventional compressor, a meridian projection distribution law of the stator of the small frontal area compressor, while maintaining the positions of 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 profile construction module is used to determine the attack angle, trailing 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 distribution 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 shifts the leading edge line blade tip point of the meridional projection of the stator of a small frontal area compressor forward and the trailing edge line blade tip apex backward, thereby increasing the density of the stator tip and reducing 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-to-wheel ratio, the density at 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 at 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 for a small frontal area compressor stator of the present invention can not only improve design efficiency and shorten design cycle, but also improve the operating 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 positional relationship between the leading edge line and 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 setback 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 construction module; 6. Area division module; 7. Data acquisition module; 8. Optimization module; 9. Output module. DETAILED DESCRIPTION

[0030] The present invention will be described in further detail below with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the present invention to the following embodiments, as all technologies implemented based on the present invention fall within 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 frontal area compressor, a flow coefficient distribution law of the inlet stage of the small frontal area compressor is constructed, so that the flow coefficient of the small frontal area compressor decreases step by step from the first stage to the outlet stage. The first stage flow coefficient of the small frontal area compressor is 1.27 to 1.6 times that of the first stage flow coefficient of a conventional compressor, and the first stage flow coefficient of the small frontal area compressor is 0.7 to 0.8; wherein, the unit inlet annular flow of the small frontal area compressor is 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 ), compressor with stator import hub ratio of 0.6-0.7;

[0034] According to a 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 maintaining the positions of the leading edge point and the trailing edge point of the blade root of the small frontal area compressor and 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 is moved 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 is moved 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, trailing 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 conditions, the consistency of the small frontal area compressor stator root 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 operating 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 a flow coefficient distribution rule for the inlet stage of the small frontal area compressor according to the design index requirements of the small frontal area compressor, so that the flow coefficient of the small frontal area compressor decreases step by step from the first stage to the outlet stage. The first stage flow coefficient of the small frontal 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 frontal area compressor is 0.7 to 0.8; wherein, the unit inlet annular flow of the small frontal area compressor is 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 ), compressor with stator import hub ratio of 0.6-0.7;

[0039] a first adjustment module, configured to adjust, based on a ratio H of the flow coefficients of the first stage of the small frontal area compressor to the first stage of the conventional compressor, a meridian projection distribution law of the stator of the small frontal area compressor, while maintaining the positions of 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 profile construction module is used to determine the attack angle, trailing 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 Figures 1-6 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 describe the process of the multi-parameter aerodynamic construction method of the small frontal area compressor stator of the present invention in detail; wherein, the small frontal area compressor has a unit inlet annular flow rate 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 ), 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: Based on the design index requirements of the small frontal area compressor, a flow coefficient distribution rule for the inlet stage of the small frontal area compressor is constructed, so that the flow coefficient of the small frontal area compressor decreases step by step from the first stage to the outlet stage, the first stage flow coefficient of the small frontal area compressor is 1.27 to 1.6 times the first stage flow coefficient of a conventional compressor, and the first stage flow coefficient of the small frontal 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 flow coefficient of the first stage of the small frontal area compressor is selected to be 1.46 times the flow coefficient of the first stage 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 within 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 the 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 maintaining the positions of the leading edge point and the trailing edge point of the blade root of the small frontal area compressor and 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 coefficients 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 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 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, trailing angle, density and mid-camber 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 small frontal area compressor stator blade root section is 1.1 to 1.4 times the consistency of the conventional compressor stator blade root section, the consistency of the small frontal area compressor stator blade tip section is 0.85 to 0.98 times the consistency of the conventional compressor stator blade tip section, and the consistency distribution of the small frontal area compressor stator smoothly transitions from the blade root to the blade tip.

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

[0051] like Figure 5 As shown, the camber line camber ratio of the small frontal area compressor stator blade root section is 1.1 to 1.25 times the camber line camber ratio of the conventional compressor stator blade root section, the relative deviation between the camber line camber ratio of the section at 50% of the blade height and above of the small frontal area compressor stator and the camber line camber 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 camber line camber 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 blade root section of the small frontal area compressor stator is 1.1 to 1.25 times the trailing angle of the blade root section of the conventional compressor stator, 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 a 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 camber 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 problems caused by high root density due to small frontal area and flow separation problems caused by low tip density by designing the attack angle, trailing angle, density and mid-arc curvature ratio of the compressor stator with small frontal area, thereby achieving the purpose of improving 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 scope of protection 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 frontal area compressor, a flow coefficient distribution law of the inlet stage of the small frontal area compressor is constructed, so that the flow coefficient of the small frontal area compressor decreases step by step from the first stage to the outlet stage. The first stage flow coefficient of the small frontal area compressor is 1.27 to 1.6 times that of the first stage flow coefficient of a conventional compressor, and the first stage flow coefficient of the small frontal area compressor is 0.7 to 0.8; wherein, the unit inlet annular flow of the small frontal area compressor is 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 ), compressor with stator import hub ratio of 0.6-0.7; According to a 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 maintaining the positions of the leading edge point and the trailing edge point of the blade root of the small frontal area compressor and 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 is moved 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 is moved 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, trailing 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 is reduced 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 the 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 smoothly transitions 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 at 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 at 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 transitions smoothly from the blade root to the section at 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 camber camber ratio of the blade root section of the small frontal area compressor stator is 1.1 to 1.25 times the camber camber ratio of the blade root section of the conventional compressor stator. The relative deviation between the camber camber ratio of the section at 50% of the blade height and above of the small frontal area compressor stator and the camber camber 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 camber camber 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 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.

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 a flow coefficient distribution rule for the inlet stage of the small frontal area compressor according to the design index requirements of the small frontal area compressor, so that the flow coefficient of the small frontal area compressor decreases step by step from the first stage to the outlet stage. The first stage flow coefficient of the small frontal 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 frontal area compressor is 0.7 to 0.8; wherein, the unit inlet annular flow of the small frontal area compressor is 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 ), compressor with stator import hub ratio of 0.6-0.7; a first adjustment module, configured to adjust, based on a ratio H of the flow coefficients of the first stage of the small frontal area compressor to the first stage of the conventional compressor, a meridian projection distribution law of the stator of the small frontal area compressor, while maintaining the positions of 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 profile construction module is used to determine the attack angle, trailing 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 the rounding function.

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