Methods for obtaining one-dimensional flow channel layout and calculating one-dimensional flow channel dimensions of compressor

Abstract

The purpose of this invention is to provide a method for obtaining the one-dimensional flow channel layout of a compressor and a method for calculating the one-dimensional flow channel dimensions. The method for obtaining the one-dimensional flow channel layout includes the following steps: S1. Obtaining the aerodynamic and thermodynamic cycle parameters of the compressor inlet and outlet sections; S2. Calculating the structural parameters of the compressor inlet and outlet sections; S3. Obtaining the axial length of the one-dimensional flow channel using the one-dimensional flow channel dimension calculation method; S4. Generating the one-dimensional flow channel layout of the compressor. This method for obtaining the one-dimensional flow channel layout and calculating the one-dimensional flow channel dimensions of a compressor can be obtained quickly.

Description

Technical Field

[0001] This invention relates to the field of gas turbine engine technology, and in particular to a method for obtaining the one-dimensional flow channel layout of a compressor and a method for calculating the one-dimensional flow channel size. Background Technology

[0002] Engine flow channel size estimation is a crucial step in the overall design. It is based on the analysis results of engine aerodynamic and thermodynamic cycle parameters and is used to determine the preliminary structure and layout of engine components, providing reasonable and quantifiable data support for the selection of component parameters in the overall scheme design.

[0003] At present, the one-dimensional flow channel size of the compressor is based on the overall performance scheme design results and a detailed aerodynamic design process that comprehensively considers parameters such as airflow angle, reaction force, and flow loss. 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 for quickly obtaining the one-dimensional flow channel dimensions of a compressor is a problem that urgently needs to be solved. Summary of the Invention

[0005] The purpose of this invention is to provide a method for calculating one-dimensional flow channel dimensions, which can quickly obtain the one-dimensional flow channel dimensions of a compressor.

[0006] The method for calculating the dimensions of a one-dimensional flow channel to achieve the aforementioned objective includes the following steps:

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

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

[0009] c. Establish a coordinate system and obtain the coordinates of multiple internal flow channels and multiple external flow channels of the compressor;

[0010] d. Fit the inner flow channel function curve based on the coordinate points of the multiple inner flow channels, and fit the outer flow channel function curve based on the coordinate points of the multiple outer flow channels;

[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 requirements. 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 yes, proceed to the next step.

[0014] h. Output compressor one-dimensional flow channel dimensions.

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

[0016]

[0017] Where z is the compressor stage number; π c The total pressure ratio of the compressor; 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 origin, the compressor rotation axis as the x-axis, and a line passing through the origin and perpendicular to the horizontal plane as the y-axis.

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

[0021] The coordinates of the inlet point of the internal flow channel located at the compressor inlet section;

[0022] The coordinates of the outlet point of the internal flow channel located at the compressor outlet section; and

[0023] The coordinate point of the inner flow channel located at the midpoint of the cross section between the compressor inlet and the compressor outlet.

[0024] The coordinate points of the external flow channel include:

[0025] The coordinates of the inlet point of the outer flow channel at the compressor inlet section;

[0026] The coordinates of the outlet point of the external flow channel located at the compressor outlet section; and

[0027] The coordinate point of the outer flow channel located at the mid-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 using 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 f is the theoretical axial length of the compressor. out For the external flow channel function curve, fin Let x be the internal flow channel function curve. n AR is the coordinate of the compressor outlet section along the x-axis. out The aspect ratio is the 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 using the following formula (3):

[0032]

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

[0034]

[0035] Where 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, and L c This is the actual axial length.

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

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

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

[0039] S3. The axial length of the compressor's one-dimensional flow channel is obtained by the one-dimensional flow channel size calculation method as described in any one of claims 1 to 7;

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

[0041] In one or more embodiments, the aerothermal 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 section is 0.4 to 0.6, and the average axial Mach number of the outlet section is 0.1 to 0.3.

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

[0044]

[0045] Among them, A i The cross-sectional area (m²)2 W is the cross-sectional flow rate (kg / s), Ma is the average axial Mach number of the cross-section, T is the total temperature of the cross-section (K), γ is the specific heat ratio, R is the gas constant (J / (kg·K)), and P is the total pressure of the cross-section (Pa).

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

[0047]

[0048] D h =D t HTR (7);

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

[0050] In one or more embodiments, 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.

[0051] In one or more embodiments, the one-dimensional flow channel layout of the compressor is generated based on the structural parameters of the compressor inlet and outlet sections, 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.

[0052] In one or more embodiments, 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.

[0053] In one or more embodiments, for each stage of the compressor, the axial clearance with the previous stage is 0.11 to 0.13 times the axial chord length, and the axial clearance with the subsequent stage is 0.1 to 1.1 times the axial chord length.

[0054] In another aspect, according to some embodiments of this application, a readable storage medium is also provided, on which computer instructions are stored, which, when executed by a processor, implement the steps of the compressor one-dimensional flow channel layout acquisition method as described above.

[0055] The beneficial effects of this invention are as follows:

[0056] The compressor one-dimensional flow channel layout acquisition method described in one or more embodiments of the present invention can quickly evaluate the compressor flow channel size under the overall performance requirements based on the analysis results of engine aerodynamic and thermodynamic cycle parameters and component design criteria, and further provide input for component weight estimation. At the same time, the component size can be comprehensively grasped in the overall scheme demonstration stage, and it can be determined whether the overall scheme can meet the requirements of the whole machine size, shorten the R&D cycle and reduce the R&D cost.

[0057] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0058] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

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

[0060] Figure 2 A flowchart illustrating some embodiments of the compressor one-dimensional flow channel layout acquisition method is shown;

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

[0062] The embodiments of the technical solution of this application will now be described in detail with reference to the accompanying drawings. These embodiments are only used to more clearly illustrate the technical solution of this application and are therefore merely examples, and should not be used to limit the scope of protection of this application.

[0063] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.

[0064] To address the issue that existing methods cannot meet the rapid evaluation requirements for overall scheme demonstration, on the one hand, according to some embodiments of this application, a one-dimensional flow channel size calculation method is provided, such as... Figure 1 A flowchart illustrating some embodiments of the present one-dimensional flow channel size calculation method is shown. The present one-dimensional flow channel size calculation method includes the following steps:

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

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

[0067] Step c: Establish a coordinate system and obtain the coordinates of multiple internal flow channels and multiple external flow channels of the compressor.

[0068] Step d: Fit the internal flow channel function curve based on multiple internal flow channel coordinate points, and fit the external flow channel function curve based on multiple external 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 Compared with the actual axial length L c If the error meets the requirements, repeat steps b to f; if it does, proceed to the next step: step h.

[0072] In one specific embodiment, the initial axial length L0 of the compressor is selected based on empirical values, from smallest to largest.

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

[0074] In some specific embodiments of this 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 compressor stage number; π c The total pressure ratio of the compressor; The average stage pressure ratio.

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

[0079] In some embodiments of this one-dimensional flow channel size calculation method, in step c, a coordinate system is established with the intersection of the compressor inlet section and the compressor rotation axis as the origin, the compressor rotation axis as the x-axis, and a line passing through the 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's axis is the x-axis.

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

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

[0082] In one specific embodiment, the first-stage rotor outlet section is selected as the intermediate section located between the compressor inlet and the compressor outlet.

[0083] In some embodiments of this one-dimensional flow channel size calculation method, the axial length from the compressor blade outlet to the compressor inlet of a certain stage can be calculated using 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 stage compressor blade can be calculated using 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 c represents the axial coordinate of the inlet blade of a certain stage compressor; i This refers to the axial clearance of the rotor-stator.

[0088] Therefore, in step e, the theoretical axial length of the compressor is calculated using 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 f is the theoretical axial length of the compressor. out For the external flow channel function curve, f in For the internal flow channel function curve, x n AR represents the coordinate of the compressor outlet section along the x-axis. out The aspect ratio of the stator at the compressor outlet section is denoted as .

[0091] In some embodiments of this one-dimensional flow channel size calculation method, the fitted internal flow channel function curve is a trigonometric function: f in (x)=a in sin(b in *x+c in The fitted external 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 represents the fitting coefficient.

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

[0093]

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

[0095]

[0096] Where 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, and L c This is the actual axial length.

[0097] On the other hand, some embodiments of this application also provide a method for obtaining a one-dimensional compressor flow channel layout, such as... Figure 2 The following is a flowchart illustrating some embodiments of the method for obtaining a one-dimensional compressor flow path layout. The method for obtaining a one-dimensional compressor flow path layout includes the following steps:

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

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

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

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

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

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

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

[0105]

[0106] Among them, A i The cross-sectional area (m²) 2 W is the cross-sectional flow rate (kg / s), Ma is the average axial Mach number of the cross-section, T is the total temperature of the cross-section (K), γ is the specific heat ratio, R is the gas constant (J / (kg·K)), and P is the total pressure of the cross-section (Pa).

[0107] The total temperature [T] of the known inlet / outlet cross-section aerothermal cycle parameters is now known. in T out Total pressure [P] in P out Mean axial Mach number [Ma] in Ma out Physical flow [W] in W out Substituting these values ​​into formula (5) yields the inlet / outlet cross-sectional area [A]. in A out ].

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

[0109]

[0110] D h =D t HTR (7);

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

[0112] Correspondingly, the inlet / outlet cross-sectional area [A] in Aout Substitute these values ​​into formulas (6) and (7) respectively to calculate the inner and outer diameters of the inlet and outlet sections.

[0113] In some embodiments of the method for obtaining the one-dimensional flow channel layout of a compressor, 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.

[0114] In some embodiments of the method for obtaining the one-dimensional flow channel layout of a compressor, the one-dimensional flow channel layout of the compressor is generated based on the structural parameters of the compressor inlet and outlet sections, the axial length of the one-dimensional flow channel, 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 final obtained one-dimensional flow channel layout of the compressor is as follows: Figure 3 As shown.

[0115] In some embodiments of the method for obtaining the one-dimensional flow channel 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 obtaining the one-dimensional flow path layout of a compressor, the axial clearance between the rotor and stator is 0.11 to 0.13 times the axial chord length for the first few stages of the compressor, and 0.1 to 1.1 times the axial chord length for the last few stages of the compressor. For example, if the compressor has 10 stages, the first 5 stages along the intake direction are called the first few stages, and the last 5 stages are called the last few stages.

[0117] The computer-readable storage medium provided in this disclosure stores computer instructions thereon. When executed by a processor, these computer instructions can implement the compressor one-dimensional flow channel layout acquisition method provided in any of the above embodiments, thereby enabling the acquisition of the compressor's one-dimensional flow channel layout.

[0118] The steps of the methods or algorithms 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 both. The software module may reside in RAM memory, flash memory, ROM memory, EPROM memory, EEPROM memory, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor such that the processor can read and write information to / from the storage medium. In an alternative, the storage medium may be integrated into the processor. The processor and storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and storage medium may reside as discrete components in the user terminal.

[0119] In one or more exemplary embodiments, the described functionality may be implemented in hardware, software, firmware, or any combination thereof. If implemented in software as a computer program product, the functionality may be stored or transmitted as one or more instructions or code on or through a computer-readable medium. A computer-readable medium includes both computer storage media and communication media, encompassing any medium that facilitates the transfer of a computer program from one location to another. A storage medium may be any available medium accessible to a computer. By way of example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disc storage, disk storage or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and is accessible to a computer. Any connection is also legitimately referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwave, then the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwave are included in the definition of a medium. As used in this article, disk and disc include compact discs (CDs), laser discs, optical discs, digital multi-purpose discs (DVDs), floppy disks, and Blu-ray discs. Disks typically reproduce data magnetically, while discs reproduce data optically using lasers. Combinations of these should also be included within the scope of computer-readable media.

[0120] The compressor one-dimensional flow channel layout acquisition method described in one or more embodiments of the present invention can quickly evaluate the compressor flow channel size under the overall performance requirements based on the analysis results of engine aerodynamic and thermodynamic cycle parameters and component design criteria, and further provide input for component weight estimation. At the same time, the component size can be comprehensively grasped in the overall scheme demonstration stage, and it can be determined whether the overall scheme can meet the requirements of the whole machine size, shorten the R&D cycle and reduce the R&D cost.

[0121] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0122] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and not to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application, and they should all be covered within the scope of the claims and specification of this application. In particular, as long as there is no structural conflict, the various technical features mentioned in the embodiments can be combined in any way. This application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A method for calculating the dimensions of a one-dimensional flow channel, characterized in that, Includes the following steps: a. Obtain the number of compressor stages; b. Set the initial axial length of the compressor; c. Establish a coordinate system and obtain the coordinates of multiple internal flow channels and multiple external flow channels of the compressor; d. Fit the inner flow channel function curve based on the coordinate points of the multiple inner flow channels, and fit the outer flow channel function curve based on the coordinate points of the multiple outer flow channels; 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 requirements. 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 yes, proceed to the next step. h. Output compressor one-dimensional flow channel dimensions.

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

3. The method for calculating the dimensions of a one-dimensional flow channel as described in claim 2, characterized in that, The average stage pressure ratio ranges from 1.3 to 1.

6.

4. The method for calculating the dimensions of a one-dimensional flow channel as described in 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 origin, the compressor rotation axis as the x-axis, and a line passing through the origin and perpendicular to the horizontal plane as the y-axis.

5. The method for calculating the dimensions of a one-dimensional flow channel as described in claim 4, characterized in that, The coordinate points of the internal flow channel include: The coordinates of the inlet point of the internal flow channel located at the compressor inlet section; The coordinates of the outlet point of the internal flow channel located at the compressor outlet section; and The coordinate point of the inner flow channel located at the midpoint of the cross section between the compressor inlet and the compressor outlet. The coordinate points of the external flow channel include: The coordinates of the inlet point of the outer flow channel at the compressor inlet section; The coordinates of the outlet point of the external flow channel located at the compressor outlet section; and The coordinate point of the outer flow channel located at the mid-section between the compressor inlet and the compressor outlet.

6. The method for calculating the dimensions of a one-dimensional flow channel as described in claim 4, characterized in that, In step e, the theoretical axial length of the compressor is calculated using the following formula (2): L n =(f out (x n )-f in (x n )) / AR out +x n (2); Among them, L n f is the theoretical axial length of the compressor. out For the external flow channel function curve, f in Let x be the internal flow channel function curve. n AR is the coordinate of the compressor outlet section along the x-axis. out The aspect ratio is the ratio at the compressor outlet section.

7. The method for calculating the dimensions of a one-dimensional flow channel as described in claim 6, characterized in that, In step f, the error between the theoretical axial length and the initial axial length is calculated using the following formula (3): In step g, the error between the theoretical axial length and the actual axial length is calculated using the following formula (4): Where 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, and L c This is the actual axial length.

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

9. The method for obtaining the one-dimensional flow channel layout of a compressor as described in claim 8, characterized in that, The aerothermal cycle parameters include total temperature, total pressure, average axial Mach number, and physical flow rate.

10. The method for obtaining the one-dimensional flow channel layout of a compressor as described in 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 obtaining the one-dimensional flow channel layout of a compressor as described in claim 8, characterized in that, In step S2, the cross-sectional areas of the inlet and outlet sections are calculated using the following formula (5): Among them, A i The cross-sectional area (m²) 2 W is the cross-sectional flow rate (kg / s), Ma is the average axial Mach number of the cross-section, T is the total temperature of the cross-section (K), γ is the specific heat ratio, R is the gas constant (J / (kg·K)), and P is the total pressure of the cross-section (Pa).

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

13. The method for obtaining the one-dimensional flow channel layout of a compressor as described in 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 obtaining the one-dimensional flow channel layout of a compressor as described in claim 8, characterized in that, The one-dimensional flow channel layout of the compressor is generated based on the structural parameters of the compressor inlet and outlet sections, the axial length of the compressor's one-dimensional flow channel, 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 obtaining the one-dimensional flow channel layout of a compressor as described in claim 14, characterized in that, 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.

16. The method for obtaining the one-dimensional flow channel layout of a compressor as described in claim 14, characterized in that, For the first stage of the compressor, the rotor-stator axial clearance is 0.11 to 0.13 times the axial chord length; for the later stage of the compressor, the rotor-stator axial clearance is 0.1 to 1.1 times the axial chord length.

17. A readable storage medium, characterized in that, It stores computer instructions that, when executed by a processor, implement the steps of the compressor one-dimensional flow channel layout acquisition method as described in any one of claims 8 to 16.

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