Design method of compressor bleed air system and aero engine

Abstract

This invention discloses a compressor bleed air system design method and an aero-engine. The compressor includes a casing, a stator, a rotor, a bleed air chamber disposed in the casing, and a bleed air passage connecting the bleed air chamber between the stator and the rotor. The design method includes: S1. Determining the bleed air axial position and bleed air parameters; S2. Matching the bleed air stage positions, selecting the stage positions based on pressure, stability effects, and engine efficiency; S3. Designing the bleed air passage structure, analyzing the bleed air volume and venting volume based on the static pressure and total pressure at the bleed air port position and matching the bleed air port area, calculating the bleed air passage size based on the bleed air port area, and designing the bleed air passage structure based on the bleed air passage size and structural design points; S4. Designing the bleed air chamber structure, including heat insulation design, flow guidance design, and pressure distribution design; S5. Calculating and analyzing bleed air performance to determine whether it meets the design requirements. If it does, engineering design is performed; if not, the bleed air port area is rematched and the process returns to S3.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular, to a design method for a compressor bleed air system. Furthermore, this invention also relates to an aero-engine incorporating the aforementioned compressor bleed air system design method. Background Technology

[0002] With the continuous advancement of aero-engine technology, the operating environment temperature and pressure of high-temperature components are also increasing. To ensure component reliability and extend component lifespan, it is necessary not only to increase the flow rate of cooling air but also to employ efficient cooling technologies. Improving the efficiency of cooling bleed air can effectively enhance engine thermal efficiency, reduce engine fuel consumption, and achieve long-term, reliable turbine operation.

[0003] In existing technologies, the cooling air required by the turbine is typically drawn from between the compressor rotor and stator stages; a common structure is shown below. Figure 1 It mainly consists of a rotor, stator, bleed air chamber, bolts, bleed air passage, casing, and heat shield. High-pressure gas from the compressor's main flow path enters the bleed air chamber through holes or slots in the compressor casing, and then the gas in the bleed air chamber is guided to the turbine blades through the bleed air passage. For example... Figure 1 As shown, conventional cooling air enters the gas collecting chamber through openings or slots in the compressor casing between the stator and rotor. Its advantages are simple structure and ease of manufacturing; however, its disadvantage is significant pressure loss when the main compressor gas enters the gas collecting chamber through the casing slots. Currently, there are no corresponding standards for the design of compressor bleed air channels and bleed air chambers. The lack of methods for designing bleed air channels and bleed air chambers makes it difficult to meet increasingly stringent bleed air efficiency requirements. Designers need to spend a lot of time adjusting the structure, resulting in a lack of guaranteed design quality. Summary of the Invention

[0004] This invention provides a design method for a compressor bleed air system and an aero-engine, to solve the technical problems in the prior art where there are no corresponding standards for the design of compressor bleed air channels and bleed air chambers, no methodological guidance for the design of bleed air channels and bleed air chambers, which cannot meet increasingly stringent bleed air efficiency requirements, require designers to spend a lot of time adjusting the structure, and the design quality cannot be guaranteed.

[0005] According to one aspect of the present invention, a method for designing a compressor bleed air system is provided. The compressor includes a casing, a stator mounted on the casing, a rotor mounted on the casing, a bleed air chamber disposed on the casing, and a bleed air passage disposed on the casing and located between the stator and the rotor, communicating with the bleed air chamber. The method for designing the compressor bleed air system includes the following:

[0006] S1. Determination of induced draft axial position and induced draft parameters;

[0007] S2. Bleed air stage position matching: select the stage position based on pressure, stability effects, and engine efficiency;

[0008] S3. Design of the air intake channel structure: Based on the static pressure and total pressure at the location of the air intake hole, analyze the air intake volume and the air release volume and match the area of ​​the air intake hole. Calculate the size of the air intake channel based on the area of ​​the air intake hole. Design the air intake channel structure based on the size of the air intake channel and the key points of the structural design.

[0009] S4. Air venting chamber structure design, including heat insulation design, airflow guidance design and pressure distribution design;

[0010] S5. Calculate and analyze the air intake performance to determine whether it meets the design requirements. If it meets the requirements, proceed to step S6. If it does not meet the requirements, rematch the air intake hole area and proceed to step S3.

[0011] S6. Engineering Design.

[0012] As a further improvement to the above technical solution, step S1 includes:

[0013] After completing the three-dimensional numerical simulation of the engine compressor, the parameters of the associated locations are extracted as input parameters for the air system calculation, and the parameters are calculated according to the air flow path of the entire engine; the air pressure and flow range required by downstream users in different flight stages are determined.

[0014] As a further improvement to the above technical solution, step S2 includes:

[0015] The selection of the matching stage is based on the fact that the outlet pressure is higher than the highest demand pressure of all downstream users under all operating conditions; the selection stage is based on calculation and test to ensure that bleed air does not induce rotational stall or surge; and the selection stage is based on a comprehensive assessment of the engine power loss and fuel consumption rate caused by bleed air.

[0016] As a further improvement to the above technical solution, step S3 includes:

[0017] S31. The static pressure P1 and total temperature T1 at the air intake are obtained through three-dimensional calculation;

[0018] S32. According to the formula Determine the area of ​​the air intake hole, where lam1 is taken empirically and m is the total amount of air intake and exhaust;

[0019] S33. Calculate the size of the air intake channel based on the area S;

[0020] S34. Design the air venting channel structure based on the air venting channel dimensions.

[0021] As a further improvement to the above technical solution, when designing the air intake channel structure, step S3 also includes:

[0022] The design includes the center and inflow angle of the air intake channel, the design of the front wall of the air intake channel, the design of the rear wall of the air intake channel, the design of the inlet width of the air intake channel, the design of the outlet width of the air intake channel, the design of the height difference between the front and rear steps, the design of the length of the air intake channel, the design of the shape of the air intake channel, and the design of the location distribution of the air intake channel.

[0023] As a further improvement to the above technical solution, step S3 includes:

[0024] The air intake channel is designed to be inclined at 15° to 75° along the flow direction; the front wall of the air intake channel is designed to be either a straight line or an arc; the rear wall of the air intake channel is designed to match the angle α of the incoming flow. If α ≤ 45°, it is designed to be a straight line; if α ≥ 45°, it is designed to be an arc.

[0025] As a further improvement to the above technical solution, step S4 includes:

[0026] Thermal insulation design is implemented at the casing connection points and / or locations where thermal stress is concentrated, and flow guidance design is implemented in areas where backflow occurs.

[0027] As a further improvement to the above technical solution, step S4 also includes:

[0028] Design the distribution of air intake holes.

[0029] As a further improvement to the above technical solution, step S5 includes:

[0030] Perform three-dimensional calculations on the air-entraining model to assess whether it meets the air-entraining requirements. If it does, the design is completed; otherwise, adjust the lam1 parameters and proceed to step S3 for iterative optimization.

[0031] According to another aspect of the present invention, an aero-engine is also provided, which includes the above-described compressor bleed air system design method.

[0032] The present invention has the following beneficial effects:

[0033] This bleed air system design method determines bleed air parameters based on relevant parameters calculated after three-dimensional numerical simulation of the compressor. It selects the stage location based on pressure, stability, and engine efficiency. The bleed air volume and discharge volume are analyzed based on the static and total pressure at the bleed air port location, and the bleed air port area is matched. The bleed air channel size is calculated based on the bleed air port area. The bleed air channel structure is designed based on the bleed air channel size and identifying key structural design points. Then, the bleed air chamber structure is designed to obtain a preliminary bleed air model. Bleed air performance calculations are performed to determine if it meets design requirements. If it meets the requirements, the design is completed and subsequent engineering design is carried out. If it does not meet the requirements, the bleed air port area is rematched and iteratively optimized. This bleed air system design method summarizes the design and usage experience of bleed air channels and bleed air chambers of various compressors, streamlining the design process of compressor bleed air channels and bleed air chambers. Furthermore, it significantly improves design efficiency and product quality by identifying key structural design points and using single-parameter iterative optimization.

[0034] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0035] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0036] Figure 1 This is a schematic diagram of the compressor bleed air system according to a preferred embodiment of the present invention;

[0037] Figure 2 This is a simplified design flow diagram of a preferred embodiment of the present invention;

[0038] Figure 3 This is a schematic diagram of the center of the air intake channel and the angle of the incoming flow in a preferred embodiment of the present invention;

[0039] Figure 4 This is a schematic diagram of the arc structure of the front wall of the air intake channel according to a preferred embodiment of the present invention;

[0040] Figure 5 This is a schematic diagram of the arc structure of the rear wall of the air intake channel according to a preferred embodiment of the present invention;

[0041] Figure 6 This is a schematic diagram of the design of the inlet and outlet width of the air intake channel according to a preferred embodiment of the present invention;

[0042] Figure 7 This is a schematic diagram of the height difference between the front and rear steps of the air intake channel according to a preferred embodiment of the present invention;

[0043] Figure 8This is a schematic diagram of the air intake channel length design of a preferred embodiment of the present invention;

[0044] Figure 9 This is a schematic diagram of the heat insulation design of the air intake channel according to a preferred embodiment of the present invention.

[0045] Legend:

[0046] 100, Rotor; 200, Stator; 300, Air Intake Chamber; 400, Bolt; 500, Air Intake Channel; 600, Casing; 700, Heat Insulation Cover. Detailed Implementation

[0047] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0048] Figure 1 This is a schematic diagram of the compressor bleed air system according to a preferred embodiment of the present invention; Figure 2 This is a simplified design flow diagram of a preferred embodiment of the present invention; Figure 3 This is a schematic diagram of the center of the air intake channel and the angle of the incoming flow in a preferred embodiment of the present invention; Figure 4 This is a schematic diagram of the arc structure of the front wall of the air intake channel according to a preferred embodiment of the present invention; Figure 5 This is a schematic diagram of the arc structure of the rear wall of the air intake channel according to a preferred embodiment of the present invention; Figure 6 This is a schematic diagram of the design of the inlet and outlet width of the air intake channel according to a preferred embodiment of the present invention; Figure 7 This is a schematic diagram of the height difference between the front and rear steps of the air intake channel according to a preferred embodiment of the present invention; Figure 8 This is a schematic diagram of the air intake channel length design according to a preferred embodiment of the present invention; Figure 9 This is a schematic diagram of the heat insulation design of the air intake channel according to a preferred embodiment of the present invention.

[0049] like Figures 1 to 9 As shown, the compressor bleed air system design method of this embodiment includes a compressor comprising a casing 600, a stator 200 mounted on the casing 600, a rotor 100 mounted on the casing 600, a bleed air chamber 300 disposed on the casing 600, and a bleed air passage 500 disposed on the casing 600 and located between the stator 200 and the rotor 100, communicating with the bleed air chamber 300. The casing 600 is fastened to the other casings by bolts 400. The compressor bleed air system design method includes the following:

[0050] S1. Determination of induced draft axial position and induced draft parameters;

[0051] S2. Bleed air stage position matching: select the stage position based on pressure, stability effects, and engine efficiency;

[0052] S3. Structural design of the air intake channel 500: Based on the static pressure and total pressure analysis of the air intake hole location, the air intake volume and the air release volume are analyzed and the air intake hole area is matched. The size of the air intake channel 500 is calculated based on the air intake hole area. The structure of the air intake channel 500 is designed based on the size of the air intake channel 500 and the key points of structural design.

[0053] S4. The 300-degree air venting chamber has a structural design, including heat insulation design, airflow guidance design, and pressure distribution design.

[0054] S5. Calculate and analyze the air intake performance to determine whether it meets the design requirements. If it meets the requirements, proceed to step S6. If it does not meet the requirements, rematch the air intake hole area and proceed to step S3.

[0055] S6. Engineering Design.

[0056] Understandably, this bleed air system design method determines bleed air parameters based on relevant parameters calculated after three-dimensional numerical simulation of the compressor. It selects the stage position based on pressure, stability, and engine efficiency. Based on the static and total pressure at the bleed air inlet location, it analyzes the bleed air volume and discharge volume and matches the bleed air inlet area. Based on the bleed air inlet area, it calculates the dimensions of the bleed air channel 500. Based on the dimensions of the bleed air channel 500 and identifying key structural design points, it designs the structure of the bleed air channel 500. Then, it designs the structure of the bleed air chamber 300, obtaining a preliminary bleed air model. Its bleed air performance is calculated and analyzed to determine if it meets design requirements. If it meets the requirements, the design is completed and subsequent engineering design is carried out. If it does not meet the requirements, the bleed air inlet area is re-matched and iteratively optimized. This bleed air system design method, by summarizing the design and usage experience of various compressor bleed air channels and bleed air chambers 300, streamlines the design process of the compressor bleed air channel 500 and bleed air chamber 300. Furthermore, it significantly improves design efficiency and product quality by identifying key structural design points and using single-parameter iterative optimization.

[0057] In particular, the engineering design in step S6 adopts conventional engineering design methods of existing technology. For example, in a specific embodiment, step S6 includes engineering design, process review, engineering design approval and other steps. After completing the above steps, it is determined whether the requirements are met. If the requirements are met, the data is archived. If the requirements are not met, the above steps are repeated until the requirements are met.

[0058] In some preferred embodiments, step S1 includes:

[0059] After completing the three-dimensional numerical simulation of the engine compressor, parameters from relevant locations are extracted as input parameters for air system calculations. Parameter calculations are performed according to the overall airflow path of the engine. The required air pressure and flow ranges for downstream users in different flight phases are clarified. Specifically, after completing the three-dimensional numerical simulation of the engine compressor, parameters from relevant locations are extracted as input parameters for air system calculations. Parameter calculations are performed for the total temperature, total pressure, etc., of relevant chambers according to the overall airflow path of the engine. This provides boundary conditions or input parameters for calculating the axial force, temperature field, strength vibration, and deformation of the engine rotor 100 to meet design requirements. Downstream users include systems such as air conditioning / environmental control systems, turbine blade cooling, wing anti-icing, and cabin pressure maintenance. Flight phases include takeoff, climb, cruise, and descent. Furthermore, when clarifying the required air pressure and flow ranges for downstream users in different flight phases, air cleanliness and temperature should be considered to avoid inhaling low-energy air from the boundary layer of the engine walls.

[0060] In some preferred embodiments, step S2 includes:

[0061] The selection of the bleed air stage is based on the following considerations: The bleed air outlet pressure must be higher than the maximum demand pressure of downstream users under all operating conditions. Calculations and experiments are used to ensure that bleed air does not induce rotating stall or surge. A comprehensive assessment of the engine power loss and fuel consumption caused by bleed air is conducted to select the appropriate stage. Specifically, the bleed air passage 500 is typically located in the intermediate stage of the compressor. When selecting this stage, pressure matching must be considered; the outlet pressure of this stage must be higher than the maximum demand pressure of downstream users under any operating condition. The impact on stability must also be considered, as bleed air alters the flow characteristics downstream of the compressor, essentially acting as unloading. The further forward the bleed air inlet, the greater its impact on the compressor operating line and surge boundary. Based on this, calculations and experiments are conducted to ensure that bleed air does not induce rotating stall or surge. The impact on efficiency must also be considered, as bleed air reduces the overall engine efficiency. A trade-off must be made. Based on the above, and through a comprehensive assessment of the engine power loss and fuel consumption caused by bleed air, the optimal solution is obtained by selecting the appropriate stage.

[0062] In some preferred embodiments, step S3 includes:

[0063] S31. The static pressure P1 and total temperature T1 at the air intake are obtained through three-dimensional calculation; where the static pressure is in Pa and the temperature is in K.

[0064] S32. According to the formula Determine the area of ​​the air intake hole, where lam1 is taken based on experience, and m is the total amount of air intake and exhaust;

[0065] S33. Calculate the dimensions of the air intake channel 500 based on the area S;

[0066] S34. Design the structure of the air venting channel 500 based on the dimensions and structural design considerations of the air venting channel 500.

[0067] In some preferred embodiments, when designing the air intake channel 500 structure, step S3 further includes:

[0068] The design method for the air intake channel 500 includes the design of its center and incoming flow angle, front wall, rear wall, inlet width, outlet width, front and rear step height difference, length, shape, and location distribution. Based on the calculated dimensions of the air intake channel 500 and the structural design of the above design points, this method effectively guides the design of the air intake channel 500 and air intake chamber 300, adapting to increasingly stringent air intake efficiency requirements without requiring a significant amount of time to adjust the structure, thus ensuring design and product quality.

[0069] In some preferred embodiments, step S3 includes:

[0070] The air intake channel 500 is designed to be inclined at 15° to 75° along the flow direction. The front wall of the air intake channel 500 is designed as a straight line or an arc. The rear wall of the air intake channel 500 is designed to match the incoming flow angle α. If α ≤ 45°, it is designed as a straight line; if α ≥ 45°, it is designed as an arc. The 15° to 75° inclination of the air intake channel 500 along the flow direction is beneficial for improving surge margin and reducing separation loss. The front wall of the air intake channel 500 is designed as a straight line or an arc, and the preferred design is the front wall. The curved structure facilitates smooth airflow and improves the static pressure rise coefficient. The rear wall is designed with either a curved or straight structure to match the center of the induced draft channel 500 with the angle of the incoming flow, ensuring stable induced draft. The inlet width L2 and outlet width L1 of the induced draft channel 500 are designed such that the outlet width L1 is greater than or equal to the inlet width L2. If the orifice is too large, it will cause excessive gas loss and affect the compressor performance. If the orifice is too small, it may cause blockage or poor flow. The front step structure and the rear step structure formed on both sides of the induced draft channel 500 are designed with different heights from the opposite side.

[0071] In some preferred embodiments, step S4 includes:

[0072] Thermal insulation design is implemented at the connection points of the casing 600 and / or locations where thermal stress is concentrated, and flow guidance design is implemented in areas where backflow occurs. Specifically, a heat shield 700 can be installed at the connection points of the casing 600 and / or locations where thermal stress is concentrated. It is generally installed at the connection points of the casing 600, where thermal stress and creep deformation at high temperatures occur due to inconsistent thermal expansion of the casing 600. The heat shield 700 is used to reduce thermal stress at this location to ensure the reliability of the structure during its service life. Flow guides are installed in areas where backflow occurs to optimize the airflow path in the air duct 300. On the other hand, opening locations such as the air duct inlet of the air duct channel 500 are key areas of stress concentration. Detailed finite element analysis can be performed on these openings, and designs such as smooth transitions and reinforcing ribs can be adopted to avoid the generation and propagation of fatigue cracks.

[0073] It should be noted that when designing the air intake channel 500 structure in step S3, the length of the air intake channel can be appropriately extended through structures such as the casing 600, heat shield 700, and flow guide, thereby achieving the design of the air intake channel length, which is beneficial to reduce turbulence;

[0074] In some preferred embodiments, step S4 further includes:

[0075] The design of the air vent locations is crucial. Specifically, to ensure uniform pressure distribution within the air vent chamber 300 and avoid localized high or low pressure areas, the reasonable arrangement of the air vent locations and sizes can effectively balance the pressure within the chamber and prevent airflow backflow or eddy currents. Furthermore, it is essential to avoid opening the air vent channel 500 along its entire circumference, as this would result in the casing 600 becoming a cantilever structure. Simultaneously, a fully open circumference would lead to a significant increase in venting and air loss. Therefore, the number, diameter, and distribution of the air vents need to be precisely designed according to actual requirements, with a preferred multi-hole uniform distribution design, further optimized through simulation analysis.

[0076] In some preferred embodiments, step S5 further includes:

[0077] Perform three-dimensional calculations on the air-entraining model to assess whether it meets the air-entraining requirements. If it does, the design is completed; otherwise, adjust the lam1 parameters and proceed to step S3 for iterative optimization.

[0078] On the other hand, a preferred embodiment of the present invention also provides an aero-engine that applies the above-mentioned compressor bleed air system design method. The bleed air system of this aero-engine determines the bleed air parameters by calculating relevant parameters based on the three-dimensional numerical simulation of the compressor. The stage position is selected according to the influence of pressure, stability and engine efficiency. The bleed air volume and exhaust volume are analyzed based on the static pressure and total pressure of the bleed air port position, and the bleed air port area is matched. The bleed air channel size is calculated based on the bleed air port area. The bleed air channel structure is designed based on the bleed air channel size and the identification of structural design points. Then the bleed air chamber structure is designed to obtain a preliminary bleed air model. The bleed air performance is calculated and analyzed to determine whether it meets the design requirements. If it meets the requirements, the design is completed and subsequent engineering design is carried out. If it does not meet the requirements, the bleed air port area is rematched and iteratively optimized. This bleed air system design method summarizes the design and use experience of bleed air channels and bleed air chambers of various types of compressors, making the design process of compressor bleed air channels and bleed air chambers more streamlined. It also greatly improves design efficiency and product quality by identifying structural design points and iteratively optimizing single parameters.

[0079] In the description of this invention, it should be noted that the terms "upper", "lower", "front", "rear", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0080] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0081] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A design method for a compressor bleed air system, the compressor comprising a casing (600), a stator (200) mounted in the casing (600), a rotor (100) mounted in the casing (600), a bleed air chamber (300) disposed in the casing (600), and a bleed air passage (500) disposed on the casing (600) and located between the stator (200) and the rotor (100) communicating with the bleed air chamber (300), characterized in that, The design method for the compressor bleed air system includes the following: S1. Determination of induced draft axial position and induced draft parameters; S2. Bleed air stage position matching: select the stage position based on pressure, stability effects, and engine efficiency; S3. Design of the air intake channel (500) structure: Based on the static pressure and total pressure of the air intake hole position, analyze the air intake volume and air release volume and match the air intake hole area. Calculate the size of the air intake channel (500) based on the air intake hole area. Design the structure of the air intake channel (500) based on the size and structural design points of the air intake channel (500). S4. Structural design of the air venting chamber (300), including heat insulation design, flow guiding design and pressure distribution design; S5. Calculate and analyze the air intake performance to determine whether it meets the design requirements. If it meets the requirements, proceed to step S6. If it does not meet the requirements, rematch the air intake hole area and proceed to step S3. S6. Engineering Design.

2. The compressor bleed air system design method according to claim 1, characterized in that, Step S1 includes: After completing the three-dimensional numerical simulation of the engine compressor, the parameters of the associated locations are extracted as input parameters for the air system calculation, and the parameters are calculated according to the air flow path of the entire engine; the air pressure and flow range required by downstream users in different flight stages are determined.

3. The compressor bleed air system design method according to claim 1, characterized in that, Step S2 includes: The selection of the matching stage is based on the fact that the outlet pressure is higher than the highest demand pressure of all downstream users under all operating conditions; the selection stage is based on calculation and test to ensure that bleed air does not induce rotational stall or surge; and the selection stage is based on a comprehensive assessment of the engine power loss and fuel consumption rate caused by bleed air.

4. The compressor bleed air system design method according to claim 1, characterized in that, Step S3 includes: S31. The static pressure P1 and total temperature T1 at the air intake are obtained through three-dimensional calculation; S32. According to the formula Determine the area of ​​the air intake hole, where lam1 is taken empirically and m is the total amount of air intake and exhaust; S33. Calculate the dimensions of the air intake channel (500) based on the area S; S34. Design the structure of the air intake channel (500) based on the size of the air intake channel (500).

5. The compressor bleed air system design method according to claim 1, characterized in that, When designing the air intake channel (500) structure, step S3 also includes: The design of the center and incoming flow angle of the air intake channel (500), the design of the front wall of the air intake channel (500), the design of the rear wall of the air intake channel (500), the design of the inlet width of the air intake channel (500), the design of the outlet width of the air intake channel (500), the design of the height difference between the front and rear steps, the design of the length of the air intake channel (500), the design of the shape of the air intake channel (500), and the design of the location distribution of the air intake channel (500).

6. The compressor bleed air system design method according to claim 5, characterized in that, Step S3 includes: The air intake channel (500) is designed to be inclined at 15°~75° along the flow direction; the front wall of the air intake channel (500) is designed to be a straight line or an arc; the rear wall of the air intake channel (500) is designed to match the angle α of the incoming flow. If α≤45°, it is designed to be a straight line; if α≥45°, it is designed to be an arc.

7. The compressor bleed air system design method according to claim 1, characterized in that, Step S4 includes: Thermal insulation is provided at the connection points of the casing (600) and / or at locations where thermal stress is concentrated, and flow guidance is provided in areas where backflow occurs.

8. The compressor bleed air system design method according to claim 7, characterized in that, Step S4 also includes: Design the distribution of air intake holes.

9. The compressor bleed air system design method according to claim 4, characterized in that, Step S5 includes: Perform three-dimensional calculations on the air-entraining model to assess whether it meets the air-entraining requirements. If it does, the design is completed; otherwise, adjust the lam1 parameters and proceed to step S3 for iterative optimization.

10. An aircraft engine, characterized in that, The application uses the compressor bleed air system design method according to any one of claims 1-9.

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