Compressor one-dimensional flow channel layout acquisition method and one-dimensional flow channel size calculation method

Abstract

The invention aims to provide a gas compressor one-dimensional flow channel layout obtaining method and a one-dimensional flow channel size calculating method.The gas compressor one-dimensional flow channel layout obtaining method comprises the following steps that S1, aerodynamic thermodynamic cycle parameters of the inlet section and the outlet section of a gas compressor are obtained; s2, structure parameters of the inlet section and the outlet section of the gas compressor are calculated; s3, the axial length of the one-dimensional flow channel of the gas compressor is obtained through a one-dimensional flow channel size calculation method; and S4, the one-dimensional flow channel layout of the gas compressor is generated. By means of the compressor one-dimensional flow channel layout obtaining method and the compressor one-dimensional flow channel size calculation method, the compressor one-dimensional flow channel size and the compressor one-dimensional flow channel layout can be rapidly obtained.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine engines, and in particular to a method for obtaining a one-dimensional flow passage layout of a compressor and a method for calculating the size of the one-dimensional flow passage. Background Art

[0002] Engine flow path size estimation is an important part of the overall design. It is based on the application of the engine aerodynamic and thermodynamic cycle parameter analysis results to determine the preliminary structure and layout of engine components, and provide reasonable and quantifiable data support for the selection of component parameters in the overall scheme design.

[0003] At the current stage, the one-dimensional flow channel size of the compressor is a detailed aerodynamic design process based on the overall performance scheme design results, which comprehensively considers parameters such as airflow angle, reaction force, flow loss, etc. Although the calculation accuracy is high, the number of iterations is large and the design cycle is long, which greatly affects the design efficiency in the overall scheme demonstration stage.

[0004] How to provide a method to quickly obtain the one-dimensional flow path size of the compressor is an urgent problem that needs to be solved. Summary of the invention

[0005] The object of the present invention is to provide a one-dimensional flow channel size calculation method, which can quickly obtain the one-dimensional flow channel size of a compressor.

[0006] A one-dimensional flow channel size calculation method for achieving the above-mentioned purpose comprises the following steps:

[0007] a. Get the number of compressor stages;

[0008] b. Set the initial axial length of the compressor;

[0009] c. Establish a coordinate system and obtain multiple inner flow channel coordinate points and multiple outer flow channel coordinate points of the compressor;

[0010] d. fitting an inner flow channel function curve according to the plurality of inner flow channel coordinate points, and fitting an outer flow channel function curve according to the plurality of outer flow channel coordinate points;

[0011] e. Calculate the theoretical axial length of the compressor;

[0012] f. Determine whether the error between the theoretical axial length and the initial axial length meets the requirement, if not, repeat steps b to e, if yes, proceed to the next step;

[0013] g. Determine whether the error between the theoretical axial length and the actual axial length meets the requirements. If not, repeat steps b to f. If so, proceed to the next step;

[0014] h. One-dimensional flow path dimensions of the output compressor.

[0015] In one or more embodiments, in step a, the number of compressor stages is determined by the following formula (1):

[0016]

[0017] Where z is the number of compressor stages; π c is the compressor total pressure ratio; is the average stage pressure ratio.

[0018] In one or more embodiments, the average stage pressure ratio ranges from 1.3 to 1.6.

[0019] In one or more embodiments, in step c, a coordinate system is established with the intersection of the compressor inlet section and the compressor rotation axis as the coordinate origin, the compressor rotation axis as the x-axis, and the line passing through the coordinate origin and perpendicular to the horizontal plane as the y-axis.

[0020] In one or more embodiments, the inner flow channel coordinate points include:

[0021] The coordinate point of the inner flow channel inlet located at the compressor inlet section;

[0022] The inner flow passage outlet coordinate point located at the compressor outlet section; and

[0023] The middle coordinate point of the inner flow passage located at the middle section between the compressor inlet and the compressor outlet

[0024] The outer flow channel coordinate points include:

[0025] The coordinate point of the outer flow passage inlet located at the compressor inlet section;

[0026] The coordinate point of the outer flow passage outlet located at the compressor outlet section; and

[0027] The middle coordinate point of the outer flow passage located at the middle section between the compressor inlet and the compressor outlet.

[0028] In one or more embodiments, in step e, the theoretical axial length of the compressor is calculated by the following formula (2):

[0029] L n =(f out (x n )-f in (x n )) / AR out +x n (2);

[0030] Among them, L n is the theoretical axial length of the compressor, f out is the outer flow channel function curve, fin is the inner flow channel function curve, x n is the coordinate of the compressor outlet section along the x-axis, AR out is the aspect ratio at the compressor outlet section.

[0031] In one or more embodiments, in step f, the error between the theoretical axial length and the initial axial length is calculated by the following formula (3):

[0032]

[0033] In step g, the error between the theoretical axial length and the actual axial length is calculated by the following formula (4):

[0034]

[0035] Among them, Delta1 is the error between the theoretical axial length and the initial axial length, Delta2 is the error between the theoretical axial length and the actual axial length, L0 is the initial axial length, L c is the actual axial length.

[0036] On the other hand, according to some embodiments of the present application, a method for obtaining a one-dimensional flow path layout of a compressor is provided, which comprises the following steps:

[0037] S1. Obtain the aerodynamic and thermodynamic cycle parameters of the compressor inlet section and outlet section;

[0038] S2. Calculate the structural parameters of the compressor inlet and outlet sections;

[0039] S3. Obtain the axial length of the one-dimensional flow channel of the compressor by the one-dimensional flow channel size calculation method according to any one of claims 1 to 7;

[0040] S4. Generate a one-dimensional flow path layout of the compressor.

[0041] In one or more embodiments, the aerodynamic thermodynamic cycle parameters include total temperature, total pressure, average axial Mach number, and physical flow rate.

[0042] In one or more embodiments, the average axial Mach number of the inlet cross section is 0.4 to 0.6, and the average axial Mach number of the outlet cross section is 0.1 to 0.3.

[0043] In one or more embodiments, in step S2, the cross-sectional areas of the inlet cross section and the outlet cross section are calculated respectively by the following formula (5):

[0044]

[0045] Among them, A i is the cross-sectional area (m2 ), W is the cross-sectional flow rate (kg / s), Ma is the average axial Mach number of the cross-sectional area, T is the total temperature of the cross-sectional area (K), γ is the specific heat ratio, R is the gas constant (J / (kg·K)); and P is the total pressure of the cross-sectional area (Pa).

[0046] In one or more embodiments, in step S2, the outer diameters of the inlet cross section and the outlet cross section are calculated by the following formula (6), and the inner diameters of the inlet cross section and the outlet cross section are calculated by the following formula (7):

[0047]

[0048] D h =D t ·HTR (7);

[0049] Among them, D t is the outer diameter (m), D h is the inner diameter (m), and HTR is the blade root hub ratio.

[0050] In one or more embodiments, the hub ratio of the inlet cross section is 0.5 to 0.7, and the hub ratio of the outlet cross section is 0.9 to 0.94.

[0051] In one or more embodiments, the one-dimensional flow path layout of the compressor is generated based on the structural parameters of the compressor inlet section and the outlet section, the axial length of the one-dimensional flow path of the compressor, the aspect ratio of the rotor and stator of each stage of the compressor, and the axial clearance of each stage of the compressor.

[0052] In one or more embodiments, for each compressor stage, the rotor inlet aspect ratio is 1 to 2, the rotor outlet aspect ratio is 0.9 to 1.2, the stator inlet aspect ratio is 2.5 to 4, and the stator outlet aspect ratio is 0.9 to 1.1.

[0053] In one or more embodiments, for each compressor stage, the axial clearance between the compressor stage before and after is 0.11 to 0.13 times the axial chord length, and the axial clearance between the compressor stage after and after is 0.1 to 1.1 times the axial chord length.

[0054] On the other hand, according to some embodiments of the present application, a readable storage medium is provided, on which computer instructions are stored. When the computer instructions are executed by a processor, the steps of the method for acquiring the one-dimensional flow path layout of the compressor as described above are implemented.

[0055] The beneficial effects of the present invention are:

[0056] Through the method for obtaining the one-dimensional flow path layout of the compressor recorded in one or more embodiments of the present invention, based on the engine aerodynamic and thermodynamic cycle parameter analysis results and component design criteria, the compressor flow path size under the overall performance requirements can be quickly evaluated, and further provide input for component weight estimation. At the same time, in the overall plan demonstration stage, the component size can be more comprehensively grasped to determine whether the overall plan can meet the requirements of the overall machine size, shorten the R&D cycle, and reduce R&D costs.

[0057] The above description is only an overview of the technical solution of the present application. In order to more clearly understand the technical means of the present application, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0058] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Moreover, the same reference numerals are used throughout the drawings to represent the same components. In the drawings:

[0059] Figure 1 A schematic diagram of the process flow of some embodiments of the one-dimensional flow channel size calculation method is shown;

[0060] Figure 2 A schematic diagram of the flow chart of some embodiments of the method for acquiring the one-dimensional flow passage layout of a compressor is shown;

[0061] Figure 3 A schematic diagram of the one-dimensional flow path layout of the compressor obtained according to the method is shown. DETAILED DESCRIPTION

[0062] The following embodiments of the technical solution of the present application are described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present application, and are therefore only used as examples, and cannot be used to limit the scope of protection of the present application.

[0063] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0064] In order to solve the problem that the existing methods cannot meet the rapid evaluation requirements of the overall scheme demonstration, on the one hand, according to some embodiments of the present application, a one-dimensional flow channel size calculation method is provided, such as Figure 1 The flowchart of some embodiments of the one-dimensional flow channel size calculation method is shown. The one-dimensional flow channel size calculation method comprises the following steps:

[0065] Step a: Obtain the compressor stage number Z.

[0066] Step b: Set the initial axial length L0 of the compressor.

[0067] Step c: Establish a coordinate system and obtain multiple inner flow channel coordinate points and multiple outer flow channel coordinate points of the compressor.

[0068] Step d: fitting the inner flow channel function curve according to the multiple inner flow channel coordinate points, and fitting the outer flow channel function curve according to the multiple outer flow channel coordinate points.

[0069] Step e: Calculate the theoretical axial length L of the compressor n .

[0070] Step f: Determine the theoretical axial length L n Does the error with the initial axial length L0 meet the requirements? If not, repeat steps b to e. If yes, proceed to the next step: step g.

[0071] Step g: Determine the theoretical axial length L n The actual axial length L c Does the error meet the requirements? If not, repeat steps b to f. If yes, proceed to the next step: step h.

[0072] In a specific embodiment, the initial axial length L0 of the compressor is selected from small to large based on empirical values.

[0073] Step h: Output the one-dimensional flow channel size of the compressor, which is the calculated theoretical axial length L n .

[0074] In some specific embodiments of the one-dimensional flow channel size calculation method,

[0075] In step a, the number of compressor stages is determined by the following formula (1):

[0076]

[0077] Where z is the number of compressor stages; π c is the compressor total pressure ratio; is the average stage pressure ratio.

[0078] In some specific embodiments of the one-dimensional flow channel size calculation method, the average stage pressure ratio The value range is 1.3 to 1.6.

[0079] In some embodiments of the one-dimensional flow channel size calculation method, in step c, a coordinate system is established with the intersection of the compressor inlet cross section and the compressor rotation axis as the coordinate origin, the compressor rotation axis as the x-axis, and the line passing through the coordinate origin and perpendicular to the horizontal plane as the y-axis. It can be understood that in the coordinate system established in this way, the direction of the compressor axis is the x-axis.

[0080] In some embodiments of the one-dimensional flow channel size calculation method, the inner flow channel coordinate points include: the inner flow channel inlet coordinate point A located at the compressor inlet section in , the inner flow channel outlet coordinate point C located at the compressor outlet section in and the middle coordinate point B of the inner flow passage located in the middle section between the compressor inlet and the compressor outlet in The external flow channel coordinate points include: the external flow channel inlet coordinate point A located at the compressor inlet section out , the coordinate point C of the outer flow channel outlet located at the compressor outlet section out and the middle coordinate point B of the outer flow passage located in the middle section between the compressor inlet and the compressor outlet out .

[0081] In a specific embodiment, A in The coordinate point is (0, D h,in / 2), A out The coordinate point is (0, D t,in / 2); B in The coordinate point is (x m , D h,m / 2), B out The coordinate point is (x m , D t,m / 2); C in The coordinate point is (L0, D h，,out / 2), C out The coordinate point is (L0, D t,out / 2). Among them, D t D is the tip diameter (i.e. outer diameter), unit: m; h D is the blade root hub diameter (i.e. inner diameter). h,i That is the blade root hub diameter at the section at position i, D t,i That is the blade tip diameter at the section at position i.

[0082] In a specific embodiment, the first-stage rotor outlet cross section is selected as the middle cross section between the compressor inlet and the compressor outlet.

[0083] In some embodiments of the one-dimensional flow channel size calculation method, the axial length from the outlet of a compressor blade of a certain stage to the compressor inlet can be calculated by the following formula:

[0084] L i =(f out (x i )-f in (x i )) / AR i +x i ;

[0085] The axial coordinate of the inlet of a certain compressor blade can be calculated by the following formula:

[0086] x i+1 =(f out (x i )-f in (x i )) / AR i +x i +c i ;

[0087] In the formula, x i is the axial coordinate of the inlet of a certain compressor blade; c i is the axial clearance between the rotor and stator.

[0088] Therefore, in step e, the theoretical axial length of the compressor is calculated by the following formula (2):

[0089] L n =(f out (x n )-f in (x n )) / AR out +x n (2);

[0090] Among them, L n is the theoretical axial length of the compressor, f out is the external flow channel function curve, f in is the internal flow channel function curve, x n is the coordinate of the compressor outlet section along the x-axis, AR out is the stator aspect ratio at the compressor outlet section.

[0091] In some embodiments of the one-dimensional flow channel size calculation method, the inner flow channel function curve obtained by fitting is a trigonometric function: f in (x) = a in sin(b in *x+c in ). The fitting outer flow channel function curve is a trigonometric function: f out (x) = a out sin(b out *x+c out ). In the formula, a in 、bin 、c in 、a out 、b out 、c out is the fitting coefficient.

[0092] In some embodiments of the one-dimensional flow channel size calculation method, in step f, the error between the theoretical axial length and the initial axial length is calculated by the following formula (3):

[0093]

[0094] In step g, the error between the theoretical axial length and the actual axial length is calculated by the following formula (4):

[0095]

[0096] Among them, Delta1 is the error between the theoretical axial length and the initial axial length, Delta2 is the error between the theoretical axial length and the actual axial length, L0 is the initial axial length, L c is the actual axial length.

[0097] On the other hand, according to some embodiments of the present application, a method for obtaining a one-dimensional flow path layout of a compressor is also provided, such as Figure 2 The flowchart of some embodiments of the method for obtaining the one-dimensional flow path layout of a compressor is shown. The method for obtaining the one-dimensional flow path layout of a compressor comprises the following steps:

[0098] Step S1: obtaining aerodynamic and thermodynamic cycle parameters of the compressor inlet section and outlet section;

[0099] Step S2: Calculate the structural parameters of the compressor inlet section and outlet section;

[0100] Step S3: obtaining the axial length of the one-dimensional flow channel of the compressor by the one-dimensional flow channel size calculation method described in one or more embodiments described above;

[0101] Step S4: Generate a one-dimensional flow path layout of the compressor.

[0102] In some embodiments of the method for obtaining the one-dimensional flow path layout of a compressor, the aerodynamic thermodynamic cycle parameters include: total temperature, total pressure, average axial Mach number and physical flow rate. Specifically, it includes the inlet cross-section total temperature T in , outlet section total temperature T out , Total pressure of inlet section P in , outlet section total pressure P out , Average axial Mach number of the inlet section Ma in , average axial Mach number of the exit section Ma out Physical flow rate W of inlet section inAnd the physical flow rate W of the outlet section out .

[0103] In some embodiments of the method for obtaining the one-dimensional flow path layout of the compressor, the average axial Mach number Ma of the inlet cross section in The average axial Mach number of the exit section is 0.4 to 0.6. out It is 0.1 to 0.3.

[0104] In some embodiments of the method for obtaining the one-dimensional flow path layout of a compressor, in step S2, the cross-sectional areas of the inlet cross section and the outlet cross section are respectively calculated by the following formula (5):

[0105]

[0106] Among them, A i is the cross-sectional area (m 2 ), W is the cross-sectional flow rate (kg / s), Ma is the average axial Mach number of the cross-sectional area, T is the total temperature of the cross-sectional area (K), γ is the specific heat ratio, R is the gas constant (J / (kg·K)); and P is the total pressure of the cross-sectional area (Pa).

[0107] The total temperature of the aerodynamic thermodynamic cycle parameters [T in , T out ], total pressure [P in , P out ], average axial Mach number [Ma in ,Ma out ], physical flow [W in , W out ] are respectively substituted into formula (5) to obtain the inlet / outlet cross-sectional area [A in , A out ].

[0108] In some embodiments of the method for acquiring the one-dimensional flow path layout of a compressor, in step S2, the outer diameters of the inlet section and the outlet section are calculated by the following formula (6), and the inner diameters of the inlet section and the outlet section are calculated by the following formula (7):

[0109]

[0110] D h =D t ·HTR (7);

[0111] Among them, D t is the outer diameter (m), D h is the inner diameter (m), and HTR is the blade root hub ratio.

[0112] Correspondingly, the inlet / outlet cross-sectional area [A in , Aout ] are respectively substituted into formula (6) and (7) to calculate the inner diameter and outer diameter of the inlet and outlet sections.

[0113] In some embodiments of the method for acquiring a one-dimensional flow path layout of a compressor, the hub ratio of the inlet cross section is 0.5 to 0.7, and the hub ratio of the outlet cross section is 0.9 to 0.94.

[0114] In some embodiments of the method for acquiring a one-dimensional flow path layout of a compressor, the one-dimensional flow path layout of the compressor is generated according to the structural parameters of the compressor inlet cross section and the outlet cross section, the axial length of the one-dimensional flow path of the compressor, the aspect ratio of the rotor and stator of each stage of the compressor, and the axial clearance of each stage of the compressor. The one-dimensional flow path layout of the compressor is finally obtained as follows: Figure 3 shown.

[0115] In some embodiments of the method for obtaining a one-dimensional flow path layout of a compressor, for each stage of the compressor, the rotor inlet aspect ratio is 1 to 2, the rotor outlet aspect ratio is 0.9 to 1.2, the stator inlet aspect ratio is 2.5 to 4, and the stator outlet aspect ratio is 0.9 to 1.1.

[0116] In some embodiments of the method for acquiring the one-dimensional flow path layout of a compressor, for the front stages of the compressor, the rotor-stator axial clearance is 0.11 to 0.13 times the axial chord length, and for the rear stages of the compressor, the rotor-stator axial clearance is 0.1 to 1.1 times the axial chord length. For example, if the compressor has 10 stages, the first 5 stages along the air intake direction are called the front stages, and the rear 5 stages are called the rear stages.

[0117] The computer-readable storage medium provided by the present disclosure stores computer instructions thereon. When the computer instructions are executed by a processor, the method for obtaining the one-dimensional flow path layout of a compressor provided by any of the above embodiments can be implemented, thereby obtaining the one-dimensional flow path layout of the compressor.

[0118] The steps of the method or algorithm described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. The software module may reside in a RAM memory, a flash memory, a ROM memory, an EPROM memory, an EEPROM memory, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor so that the processor can read and write information from / to the storage medium. In an alternative, a storage medium may be integrated into a processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and the storage medium may reside in a user terminal as discrete components.

[0119] In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented as a computer program product in software, each function may be stored on or transmitted by a computer-readable medium as one or more instructions or codes. Computer-readable media include both computer storage media and communication media, including any medium that facilitates the transfer of a computer program from one place to another. Storage media may be any available medium that can be accessed by a computer. As an example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disk storage, disk storage or other magnetic storage device, or any other medium that can be used to carry or store the desired program code in the form of an instruction or data structure and can be accessed by a computer. Any connection is also properly referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using a coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwaves, the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwaves are included in the definition of the medium. Disk and disc as used herein include compact disc (CD), laser disc, optical disc, digital versatile disc (DVD), floppy disk and Blu-ray disc, wherein disk often reproduces data magnetically, while disc reproduces data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.

[0120] Through the method for obtaining the one-dimensional flow path layout of the compressor recorded in one or more embodiments of the present invention, based on the engine aerodynamic and thermodynamic cycle parameter analysis results and component design criteria, the compressor flow path size under the overall performance requirements can be quickly evaluated, and further provide input for component weight estimation. At the same time, in the overall plan demonstration stage, the component size can be more comprehensively grasped to determine whether the overall plan can meet the requirements of the overall machine size, shorten the R&D cycle, and reduce R&D costs.

[0121] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0122] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them; although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application, and they should all be included in the scope of the claims and specification of the present application. In particular, as long as there is no structural conflict, the various technical features mentioned in the various embodiments can be combined in any way. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions that fall within the scope of the claims.

Claims

1. A one-dimensional flow channel size calculation method, characterized in that: The steps include: a. Get the number of compressor stages; b. Set the initial axial length of the compressor; c. Establish a coordinate system and obtain multiple inner flow channel coordinate points and multiple outer flow channel coordinate points of the compressor; d. fitting an inner flow channel function curve according to the plurality of inner flow channel coordinate points, and fitting an outer flow channel function curve according to the plurality of outer flow channel coordinate points; e. Calculate the theoretical axial length of the compressor; f. Determine whether the error between the theoretical axial length and the initial axial length meets the requirement, if not, repeat steps b to e, if yes, proceed to the next step; g. Determine whether the error between the theoretical axial length and the actual axial length meets the requirements. If not, repeat steps b to f. If so, proceed to the next step; h. One-dimensional flow path dimensions of the output compressor.

2. The one-dimensional flow channel size calculation method according to claim 1, characterized in that: In step a, the number of compressor stages is determined by the following formula (1): Where z is the number of compressor stages; π c is the compressor total pressure ratio; is the average stage pressure ratio.

3. The one-dimensional flow channel size calculation method according to claim 2, characterized in that: The average stage pressure ratio ranges from 1.3 to 1.

6.

4. The one-dimensional flow channel size calculation method according to claim 1, characterized in that: In step c, a coordinate system is established with the intersection of the compressor inlet section and the compressor rotation axis as the coordinate origin, the compressor rotation axis as the x-axis, and the line passing through the coordinate origin and perpendicular to the horizontal plane as the y-axis.

5. The one-dimensional flow channel size calculation method according to claim 4, characterized in that: The inner flow channel coordinate points include: The coordinate point of the inner flow channel inlet located at the compressor inlet section; The inner flow passage outlet coordinate point located at the compressor outlet section; and The middle coordinate point of the inner flow passage located at the middle section between the compressor inlet and the compressor outlet The outer flow channel coordinate points include: The coordinate point of the outer flow passage inlet located at the compressor inlet section; The coordinate point of the outer flow passage outlet located at the compressor outlet section; and The middle coordinate point of the outer flow passage located at the middle section between the compressor inlet and the compressor outlet.

6. The one-dimensional flow channel size calculation method according to claim 4, characterized in that: In step e, the theoretical axial length of the compressor is calculated by the following formula (2): L n =(f out (x n )-f in (x n )) / AR out +x n (2); Among them, L n is the theoretical axial length of the compressor, f out is the outer flow channel function curve, f in is the inner flow channel function curve, x n is the coordinate of the compressor outlet section along the x-axis, AR out is the aspect ratio at the compressor outlet section.

7. The one-dimensional flow channel size calculation method according to claim 6, characterized in that: In step f, the error between the theoretical axial length and the initial axial length is calculated by the following formula (3): In step g, the error between the theoretical axial length and the actual axial length is calculated by the following formula (4): Among them, Delta1 is the error between the theoretical axial length and the initial axial length, Delta2 is the error between the theoretical axial length and the actual axial length, L0 is the initial axial length, L c is the actual axial length.

8. A method for obtaining a one-dimensional flow path layout of a compressor, characterized in that: The steps include: S1. Obtain the aerodynamic and thermodynamic cycle parameters of the compressor inlet section and outlet section; S2. Calculate the structural parameters of the compressor inlet and outlet sections; S3. Obtain the axial length of the one-dimensional flow channel of the compressor by the one-dimensional flow channel size calculation method according to any one of claims 1 to 7; S4. Generate a one-dimensional flow path layout of the compressor.

9. The method for acquiring the one-dimensional flow path layout of a compressor according to claim 8, characterized in that: The aerodynamic thermodynamic cycle parameters include total temperature, total pressure, average axial Mach number and physical flow rate.

10. The method for acquiring the one-dimensional flow path layout of a compressor according to claim 9, characterized in that: The average axial Mach number of the inlet section is 0.4 to 0.6, and the average axial Mach number of the outlet section is 0.1 to 0.

3.

11. The method for acquiring the one-dimensional flow path layout of a compressor according to claim 8, characterized in that: In step S2, the cross-sectional areas of the inlet cross section and the outlet cross section are calculated respectively by the following formula (5): Among them, A i is the cross-sectional area (m 2 ), W is the cross-sectional flow rate (kg / s), Ma is the average axial Mach number of the cross-sectional area, T is the total temperature of the cross-sectional area (K), γ is the specific heat ratio, R is the gas constant (J / (kg·K)); and P is the total pressure of the cross-sectional area (Pa).

12. The method for acquiring the one-dimensional flow path layout of a compressor according to claim 11, characterized in that: In step S2, the outer diameters of the inlet section and the outlet section are calculated by the following formula (6), and the inner diameters of the inlet section and the outlet section are calculated by the following formula (7): D h =D t ·HTR (7); Among them, D t is the outer diameter (m), D h is the inner diameter (m), and HTR is the blade root hub ratio.

13. The method for acquiring the one-dimensional flow path layout of a compressor according to claim 12, characterized in that: The hub ratio of the inlet section is 0.5 to 0.7, and the hub ratio of the outlet section is 0.9 to 0.

94.

14. The method for acquiring the one-dimensional flow path layout of a compressor according to claim 8, characterized in that: The one-dimensional flow channel layout of the compressor is generated according to the structural parameters of the inlet section and the outlet section of the compressor, the axial length of the one-dimensional flow channel of the compressor, the aspect ratio of the rotor and stator of each stage of the compressor, and the axial clearance of each stage of the compressor.

15. The method for acquiring the one-dimensional flow path layout of a compressor according to claim 14, characterized in that: For each compressor stage, the rotor inlet aspect ratio is 1 to 2, the rotor outlet aspect ratio is 0.9 to 1.2, the stator inlet aspect ratio is 2.5 to 4, and the stator outlet aspect ratio is 0.9 to 1.

1.

16. The method for acquiring the one-dimensional flow path layout of a compressor according to claim 14, characterized in that: For the front stages of the compressor, the axial clearance of the rotor and stator is 0.11 to 0.13 times the axial chord length, and for the rear stages of the compressor, the axial clearance of the rotor and stator is 0.1 to 1.1 times the axial chord length.

17. A readable storage medium, characterized in that: Computer instructions are stored thereon, and when the computer instructions are executed by a processor, the steps of the method for acquiring the one-dimensional flow path layout of a compressor as described in any one of claims 8 to 16 are implemented.

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