Method, device, equipment and medium for calculating aerodynamic axial force of semi-open centrifugal impeller

Abstract

The application discloses a semi-open centrifugal impeller aerodynamic axial force calculation method, device, equipment and medium. The method comprises the following steps: obtaining impeller geometric information and aerodynamic working condition information. Based on a first front end force calculation algorithm and a second front end force calculation algorithm, the first front end axial force and the second front end axial force are calculated according to the impeller geometric information and the aerodynamic working condition information. The target front end axial force is determined based on the inlet type and the main flow passage pressure distribution correction. Based on the first rear end force calculation algorithm, the target rear end axial force is determined according to the impeller geometric information and the aerodynamic working condition information. The comprehensive aerodynamic axial force of the semi-open centrifugal impeller is determined according to the target front end axial force and the target rear end axial force. The application can realize high-precision calculation results, shorten the aerodynamic axial force calculation time, balance accuracy and timeliness, and significantly reduce the research and development cost.

Description

Technical Field

[0001] This invention relates to the field of aerodynamics, and in particular to a method, apparatus, equipment and medium for calculating the aerodynamic axial force of a semi-open centrifugal impeller. Background Technology

[0002] Semi-open centrifugal impellers are widely used in centrifugal compressors and turbopumps due to their high single-stage pressure ratio and simple structure. However, because they lack a cover plate on the back, the pressure distribution in the front and rear chambers of the impeller is extremely uneven, resulting in significant aerodynamic axial forces during operation. If these axial forces are not accurately predicted or properly controlled, they will not only increase the load and wear on the thrust bearing, but in severe cases, they can also cause rotor system instability, directly hindering the efficient and safe operation of the equipment. Therefore, accurate prediction of these forces is crucial.

[0003] Currently, the industry mainly uses three methods to obtain aerodynamic axial forces: classical theoretical calculations, three-dimensional numerical simulations, and experimental measurements. Classical theoretical calculation formulas are mostly based on one-dimensional flow assumptions, making it difficult to accurately characterize the complex turbulent flow and vortex structure of the impeller back cavity, resulting in poor calculation accuracy and even failing to correctly reflect the changing trend of axial forces. Furthermore, some empirical formulas are too simplistic, lack universality, and have low reliability. While three-dimensional numerical calculations can reproduce flow field details, the workload of geometric modeling and mesh generation increases exponentially after adding sealing structures, and CFD calculations have high hardware resource consumption and long iteration cycles. Experimental measurements, while providing intuitive data, suffer from long cycles, high costs, and limitations in sensor installation. All of these shortcomings fail to meet the demands of modern engineering design for rapid and high-precision prediction of axial forces. Summary of the Invention

[0004] This invention provides a method, apparatus, equipment, and medium for calculating the aerodynamic axial force of a semi-open centrifugal impeller, which achieves high-precision calculation results, shortens the calculation time of aerodynamic axial force, balances accuracy and timeliness, and significantly reduces research and development costs.

[0005] According to one aspect of the present invention, a method for calculating the aerodynamic axial force of a semi-open centrifugal impeller is provided. The method includes:

[0006] Obtain the impeller geometry information corresponding to the semi-open centrifugal impeller to be calculated, as well as the aerodynamic operating condition information related to the semi-open centrifugal impeller. The impeller geometry information includes, but is not limited to, the impeller inlet hub radius and blade tip radius, and the sealing tooth tip radius. The aerodynamic operating condition information includes, but is not limited to, the impeller outlet static pressure, inlet static pressure, inlet mass flow rate, impeller angular velocity, and gas density.

[0007] Based on the first front-end force algorithm, the first front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the second front-end force algorithm, the second front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information.

[0008] Based on the intake type corresponding to the semi-open centrifugal impeller, the pressure distribution of the main channel is corrected according to the first front-end axial force and the second front-end axial force to determine the target front-end axial force on the main channel side of the semi-open centrifugal impeller.

[0009] Based on the first rear-end force algorithm, the target rear-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information.

[0010] The combined aerodynamic axial force of the semi-open centrifugal impeller is determined based on the axial force at the front end of the target and the axial force at the rear end of the target.

[0011] According to another aspect of the present invention, a device for calculating the aerodynamic axial force of a semi-open centrifugal impeller is provided. The device includes:

[0012] The impeller-related data acquisition module is used to acquire the impeller geometry information corresponding to the semi-open centrifugal impeller to be calculated, as well as the aerodynamic operating condition information related to the semi-open centrifugal impeller. The impeller geometry information includes, but is not limited to, the impeller inlet hub radius and blade tip radius, and the sealing tooth tip radius. The aerodynamic operating condition information includes, but is not limited to, the impeller outlet static pressure, inlet static pressure, inlet mass flow rate, impeller angular velocity, and gas density.

[0013] The front-end axial force determination module is used to determine the first front-end axial force on the main flow side of the semi-open centrifugal impeller based on the first front-end force algorithm, according to the impeller geometry information and the aerodynamic operating condition information, and to determine the second front-end axial force on the main flow side of the semi-open centrifugal impeller based on the second front-end force algorithm, according to the impeller geometry information and the aerodynamic operating condition information.

[0014] The front-end axial force correction module is used to correct the main flow pressure distribution based on the first front-end axial force and the second front-end axial force according to the intake type corresponding to the semi-open centrifugal impeller, and to determine the target front-end axial force on the main flow side of the front end of the semi-open centrifugal impeller.

[0015] The rear axial force determination module is used to determine the target rear axial force on the front main flow side of the semi-open centrifugal impeller based on the first rear force algorithm, according to the impeller geometry information and the aerodynamic operating condition information.

[0016] The integrated axial force determination module is used to determine the integrated aerodynamic axial force of the semi-open centrifugal impeller based on the target front-end axial force and the target rear-end axial force.

[0017] According to another aspect of the present invention, an electronic device is provided, the electronic device comprising:

[0018] At least one processor; and

[0019] A memory communicatively connected to the at least one processor; wherein,

[0020] The memory stores a computer program that can be executed by the at least one processor, which enables the at least one processor to perform the aerodynamic axial force calculation method for a semi-open centrifugal impeller according to any embodiment of the present invention.

[0021] According to another aspect of the present invention, a computer-readable storage medium is provided, the computer-readable storage medium storing computer instructions for causing a processor to execute and implement the method for calculating the aerodynamic axial force of a semi-open centrifugal impeller as described in any embodiment of the present invention.

[0022] The technical solution of this invention involves acquiring the impeller geometry information and aerodynamic operating condition information related to the semi-open centrifugal impeller to be calculated. Based on a first front-end force algorithm, a first front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on a second front-end force algorithm, a second front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the intake type corresponding to the semi-open centrifugal impeller, the main flow pressure distribution is corrected according to the first and second front-end axial forces to determine the target front-end axial force on the main flow side of the semi-open centrifugal impeller. Based on a first rear-end force algorithm, the target rear-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the axial force at the front end and the axial force at the rear end of the target, the comprehensive aerodynamic axial force of the semi-open centrifugal impeller is determined. This solves the problem of large trend deviation and low reliability of classical theoretical formulas, overcomes the pain points of large resource consumption and long cycle of three-dimensional numerical simulation and experimental measurement numerical calculation, achieves high-precision prediction results, shortens the calculation time, takes into account the accuracy and timeliness of engineering design, and significantly reduces R&D costs.

[0023] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of the present invention, nor is it intended to limit the scope of the invention. Other features of the invention will become readily apparent from the following description. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a flowchart of a method for calculating the aerodynamic axial force of a semi-open centrifugal impeller according to an embodiment of the present invention;

[0026] Figure 2 This is a schematic diagram of the aerodynamic axial force of a semi-open centrifugal impeller according to an embodiment of the present invention;

[0027] Figure 3 This is a schematic diagram comparing the comprehensive aerodynamic axial forces provided in an embodiment of the present invention;

[0028] Figure 4 This is a structural diagram of a semi-open centrifugal impeller aerodynamic axial force calculation device according to an embodiment of the present invention;

[0029] Figure 5 This is a schematic diagram of the structure of an electronic device that implements the aerodynamic axial force calculation method for a semi-open centrifugal impeller according to an embodiment of the present invention. Detailed Implementation

[0030] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0031] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0032] Figure 1 This is a flowchart illustrating a method for calculating the aerodynamic axial force of a semi-open centrifugal impeller according to an embodiment of the present invention. This embodiment is applicable to calculating the aerodynamic axial force of a semi-open centrifugal impeller. The method can be executed by a semi-open centrifugal impeller aerodynamic axial force calculation device, which can be implemented in hardware and / or software and can be configured in an electronic device. For example... Figure 1 As shown, the method includes:

[0033] S101. Obtain the impeller geometry information corresponding to the semi-open centrifugal impeller to be calculated, as well as the aerodynamic operating condition information related to the semi-open centrifugal impeller.

[0034] Semi-open centrifugal impellers are a common core rotating component in fluid machinery such as centrifugal pumps, fans, and compressors. Semi-open centrifugal impellers fall between open and closed types, characterized by retaining only a rear cover plate and lacking a front cover plate. The aerodynamic axial force of a semi-open centrifugal impeller mainly consists of two parts: the front main flow side and the rear cover plate sealing side.

[0035] Figure 2 This is a schematic diagram of the aerodynamic axial force of a semi-open centrifugal impeller according to an embodiment of the present invention. Figure 2 As shown, the axial force on the front main flow side is divided into two parts: the force F0 on the inlet cylindrical surface and the force F1 on the blade projection surface. The axial force on the rear cover sealing side is mainly the impeller back cavity pressure F2. The difference between the axial force on the front main flow side and the axial force on the rear cover sealing side is the aerodynamic axial force of the semi-open centrifugal impeller.

[0036] The impeller geometry information includes, but is not limited to, the impeller inlet hub radius and blade tip radius, and the sealing tooth tip radius. The aerodynamic operating condition information includes, but is not limited to, the impeller outlet static pressure, inlet static pressure, inlet mass flow rate, impeller angular velocity, and gas density.

[0037] Specifically, design drawings or 3D model parameters of the semi-open centrifugal impeller are collected, including impeller geometry information such as the dimensions of the inlet hub and blade tip, and the radius of the rear chamber seal. Based on the actual operating or design condition data of the semi-open centrifugal impeller, aerodynamic condition information including inlet and outlet static pressure, inlet mass flow rate, rotor speed, and gas density is collected. This data can come from geometric modeling files and aerodynamic performance parameter tables, providing basic data input for subsequent force analysis calculations.

[0038] S102. Based on the first front-end force algorithm, determine the first front-end axial force on the main flow side of the semi-open centrifugal impeller according to the impeller geometry information and the aerodynamic operating condition information, and based on the second front-end force algorithm, determine the second front-end axial force on the main flow side of the semi-open centrifugal impeller according to the impeller geometry information and the aerodynamic operating condition information.

[0039] Specifically, the relevant parameters from the impeller geometry and aerodynamic operating conditions are input into the first and second front-end force algorithms, respectively, for force calculation. This allows for the determination of the first and second front-end axial forces on the main flow side of the semi-open centrifugal impeller. It should be noted that the first front-end axial force can refer to the force F0 on the inlet cylindrical surface, and the second front-end axial force can refer to the force F1 on the blade projection surface.

[0040] For example, the algorithm based on the first front-end force is as follows:

[0041] ;

[0042] in, This refers to the axial force at the first front end. This refers to the impeller inlet tip radius, This refers to the impeller inlet blade root radius, It refers to the imported static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. This refers to the import quality flow rate, This refers to the inlet axial velocity.

[0043] Regarding the second front-end axial force, assuming the blade projection surface has an arbitrary radius... Pressure at the location If the distribution follows a linear function along the flow direction, then:

[0044] ;

[0045] ;

[0046] in, This refers to the impeller inlet tip radius, This refers to the impeller outlet radius, This refers to the impeller inlet static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. It refers to any radius of the blade's projected surface. Pressure at the place, This refers to the static pressure at the impeller outlet.

[0047] like Figure 2 As shown, the radial range of the main channel is After integration, the second front-end force algorithm is as follows:

[0048] ;

[0049] in, This refers to the axial force at the second front end. This refers to the impeller inlet tip radius, This refers to the impeller outlet radius, This refers to the impeller inlet static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. This refers to the static pressure at the impeller outlet.

[0050] S103. Based on the intake type corresponding to the semi-open centrifugal impeller, the pressure distribution of the main channel is corrected according to the first front-end axial force and the second front-end axial force, and the target front-end axial force on the main channel side of the semi-open centrifugal impeller is determined.

[0051] It needs to be explained that in determining the first and second front-end axial forces, the pressure of the blades is assumed to be an ideal value. However, in reality, when the gas flows in the curved flow channel, eddies and friction are generated, resulting in a smaller pressure distribution in the main flow channel compared to the assumption. Therefore, it is necessary to make corrections based on the above assumptions, so that the target front-end axial force on the main flow side of the semi-open centrifugal impeller can be calculated and determined after correction.

[0052] For example, the air intake types of semi-open centrifugal impellers mainly include atmospheric pressure air intake type and non-pressure air intake type.

[0053] When the intake type is atmospheric pressure intake, the axial force at the target front end is as follows:

[0054] ;

[0055] In special cases, when the semi-open centrifugal impeller is cantilevered... , ;

[0056] When the intake type is non-pressure intake, the axial force at the target front end is as follows:

[0057] ;

[0058] In special cases, when the semi-open centrifugal impeller is cantilevered... , ;

[0059] in, This refers to the axial force at the first front end. This refers to the impeller inlet tip radius, This refers to the impeller inlet blade root radius, It refers to the imported static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. This refers to the import quality flow rate, This refers to the inlet axial speed, This refers to the axial force at the second front end. This refers to the impeller outlet radius, This refers to the impeller inlet static pressure, This refers to the static pressure at the impeller outlet.

[0060] S104. Based on the first rear-end force algorithm, determine the target rear-end axial force on the main flow side of the semi-open centrifugal impeller according to the impeller geometry information and the aerodynamic operating condition information.

[0061] Specifically, the relevant parameters in the impeller geometry information and aerodynamic operating condition information are input into the first rear-end force algorithm for force calculation, and after correction processing, the target rear-end axial force is obtained.

[0062] For example, determining the target rear-end axial force on the main flow side of the semi-open centrifugal impeller includes:

[0063] Based on the first rear-end force algorithm, the initial rear-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information; the initial rear-end axial force is corrected according to the intake type corresponding to the semi-open centrifugal impeller to obtain the target rear-end axial force.

[0064] Specifically, the relevant parameters in the impeller geometry information and aerodynamic operating condition information are input into the first rear-end force algorithm to obtain the initial rear-end axial force. Then, according to the intake type, the initial rear-end axial force is corrected to obtain the target rear-end axial force.

[0065] For example, the first back-end force algorithm is derived from a simple radial equilibrium equation:

[0066] ;

[0067] in, This refers to the candidate rotational angular velocity of the gas in the back cavity, which is determined specifically according to the intake type. This refers to the rate of change of pressure with respect to radius. This refers to the gas density at the impeller outlet. It refers to the distance from a point on the circular ring on the back of the impeller to the axis of rotation.

[0068] Integrating the above equation, we have... ,get:

[0069] ;

[0070] Integrating both sides simultaneously yields the algorithm for the first rear-end force, as shown below:

[0071] ;

[0072] in, This refers to the axial force at the rear end of the target. It refers to the distance from a point on the circular ring on the back of the impeller to the axis of rotation. This refers to the impeller back radius being static pressure at the point This refers to the impeller outlet radius, This refers to the radius of the sealing tooth tip, This refers to the impeller outlet static pressure, This refers to the gas density at the impeller outlet. It refers to the candidate rotational angular velocity of the gas in the back cavity.

[0073] Based on the intake type corresponding to the semi-open centrifugal impeller, the initial rear-end axial force is corrected to obtain the target rear-end axial force, including:

[0074] When the intake type is atmospheric pressure intake, The axial force at the rear end of the target is as follows:

[0075] ;

[0076] When the intake type is atmospheric pressure intake, The axial force at the rear end of the target is as follows:

[0077] ;

[0078] in, This refers to the axial force at the rear end of the target. This refers to the impeller outlet radius, This refers to the radius of the sealing tooth tip, This refers to the impeller outlet static pressure, This refers to the gas density at the impeller outlet. This refers to the candidate rotational angular velocity of the gas in the back cavity. This refers to the actual angular velocity of the gas in the back cavity.

[0079] S105. Determine the combined aerodynamic axial force of the semi-open centrifugal impeller based on the axial force at the front end of the target and the axial force at the rear end of the target.

[0080] Specifically, the difference between the axial force at the front end of the target and the axial force at the rear end of the target is determined as the comprehensive aerodynamic axial force of the semi-open centrifugal impeller.

[0081] For example, when the intake type is atmospheric pressure intake, the combined aerodynamic axial force is as follows:

[0082] ;

[0083] For example, when the intake type is atmospheric pressure intake, the combined aerodynamic axial force is as follows:

[0084] ;

[0085] in, This refers to the combined aerodynamic axial force, This refers to the axial force at the rear end of the target. This refers to the axial force at the front end of the target. This refers to the impeller outlet radius, This refers to the radius of the sealing tooth tip, This refers to the impeller outlet static pressure, This refers to the gas density at the impeller outlet. This refers to the actual angular velocity of the gas in the back cavity. This refers to the impeller inlet static pressure, This refers to the impeller inlet blade root radius, This refers to the impeller inlet tip radius, This refers to the import quality flow rate, This refers to the inlet axial velocity.

[0086] Figure 3 This is a schematic diagram comparing the comprehensive aerodynamic axial forces provided in an embodiment of the present invention. Figure 3 As shown, the black dotted lines represent the calculation results of the classical theoretical formula, the black solid lines represent the calculation results of the three-dimensional simulation, and the red dashed lines represent the comprehensive aerodynamic axial force calculation results provided by the embodiment of the present invention. The comprehensive aerodynamic axial force calculation results provided by the embodiment of the present invention achieve a high degree of consistency with the high-precision three-dimensional simulation data across the entire flow range. It accurately captures the real physical trend of axial force changes with operating conditions, avoids non-physical abrupt changes in high-operating-condition regions by traditional algorithms, and simplifies complex flow field analysis into analytical formulas usable in engineering, significantly improving the reliability of axial force prediction for semi-open impellers and the efficiency of design iteration.

[0087] The technical solution of this invention involves acquiring the impeller geometry information and aerodynamic operating condition information related to the semi-open centrifugal impeller to be calculated. Based on a first front-end force algorithm, a first front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on a second front-end force algorithm, a second front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the intake type corresponding to the semi-open centrifugal impeller, the main flow pressure distribution is corrected according to the first and second front-end axial forces to determine the target front-end axial force on the main flow side of the semi-open centrifugal impeller. Based on a first rear-end force algorithm, the target rear-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the axial force at the front end and the axial force at the rear end of the target, the comprehensive aerodynamic axial force of the semi-open centrifugal impeller is determined. This solves the problem of large trend deviation and low reliability of classical theoretical formulas, overcomes the pain points of large resource consumption and long cycle of three-dimensional numerical simulation and experimental measurement numerical calculation, achieves high-precision prediction results, shortens the calculation time, takes into account the accuracy and timeliness of engineering design, and significantly reduces R&D costs.

[0088] Figure 4 This is a schematic diagram of a semi-open centrifugal impeller aerodynamic axial force calculation device provided in an embodiment of the present invention. Figure 4 As shown, the device includes:

[0089] The impeller-related data acquisition module 301 is used to acquire the impeller geometry information corresponding to the semi-open centrifugal impeller to be calculated and the aerodynamic condition information related to the semi-open centrifugal impeller. The impeller geometry information includes, but is not limited to, the impeller inlet hub radius and blade tip radius, and the sealing tooth tip radius. The aerodynamic condition information includes, but is not limited to, the impeller outlet static pressure, inlet static pressure, inlet mass flow rate, impeller angular velocity, and gas density.

[0090] The front-end axial force determination module 302 is used to determine the first front-end axial force on the main flow side of the semi-open centrifugal impeller based on the first front-end force algorithm, according to the impeller geometry information and the aerodynamic operating condition information, and to determine the second front-end axial force on the main flow side of the semi-open centrifugal impeller based on the second front-end force algorithm, according to the impeller geometry information and the aerodynamic operating condition information.

[0091] The front-end axial force correction module 303 is used to correct the main channel pressure distribution based on the first front-end axial force and the second front-end axial force according to the air intake type corresponding to the semi-open centrifugal impeller, and to determine the target front-end axial force on the front-end main channel side of the semi-open centrifugal impeller.

[0092] The rear axial force determination module 304 is used to determine the target rear axial force on the front main flow side of the semi-open centrifugal impeller based on the first rear force algorithm, according to the impeller geometry information and the aerodynamic operating condition information.

[0093] The integrated axial force determination module 305 is used to determine the integrated aerodynamic axial force of the semi-open centrifugal impeller based on the target front-end axial force and the target rear-end axial force.

[0094] The technical solution of this invention involves acquiring the impeller geometry information and aerodynamic operating condition information related to the semi-open centrifugal impeller to be calculated. Based on a first front-end force algorithm, a first front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on a second front-end force algorithm, a second front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the intake type corresponding to the semi-open centrifugal impeller, the main flow pressure distribution is corrected according to the first and second front-end axial forces to determine the target front-end axial force on the main flow side of the semi-open centrifugal impeller. Based on a first rear-end force algorithm, the target rear-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the axial force at the front end and the axial force at the rear end of the target, the comprehensive aerodynamic axial force of the semi-open centrifugal impeller is determined. This solves the problem of large trend deviation and low reliability of classical theoretical formulas, overcomes the pain points of large resource consumption and long cycle of three-dimensional numerical simulation and experimental measurement numerical calculation, achieves high-precision prediction results, shortens the calculation time, takes into account the accuracy and timeliness of engineering design, and significantly reduces R&D costs.

[0095] Optionally, the first front-end force-based algorithm is as follows:

[0096] ;

[0097] in, This refers to the axial force at the first front end. This refers to the impeller inlet tip radius, This refers to the impeller inlet blade root radius, It refers to the imported static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. This refers to the import quality flow rate, This refers to the inlet axial velocity.

[0098] Optionally, the second front-end force algorithm is as follows:

[0099] ;

[0100] in, This refers to the axial force at the second front end. This refers to the impeller inlet tip radius, This refers to the impeller outlet radius, This refers to the impeller inlet static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. This refers to the static pressure at the impeller outlet.

[0101] Optional, the front-end axial force correction module 303 is used for:

[0102] When the intake type is atmospheric pressure intake, the target front-end axial force is determined as follows:

[0103] ;

[0104] When the intake type is non-pressure intake, the target front-end axial force is determined as follows:

[0105] ;

[0106] in, This refers to the axial force at the front end of the target. This refers to the axial force at the first front end. This refers to the impeller inlet tip radius, This refers to the impeller inlet blade root radius, It refers to the imported static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. This refers to the import quality flow rate, This refers to the inlet axial speed, This refers to the axial force at the second front end. This refers to the impeller outlet radius, This refers to the impeller inlet static pressure, This refers to the static pressure at the impeller outlet.

[0107] Optionally, the rear axial force determination module 304 includes:

[0108] The initial rear-end axial force determination unit is used to determine the initial rear-end axial force on the main flow side of the semi-open centrifugal impeller based on the first rear-end force algorithm, according to the impeller geometry information and the aerodynamic operating condition information.

[0109] The target rear-end axial force determination unit is used to correct the initial rear-end axial force according to the air intake type corresponding to the semi-open centrifugal impeller, so as to obtain the target rear-end axial force.

[0110] Optionally, the first back-end force algorithm is as follows:

[0111] ;

[0112] in, This refers to the axial force at the rear end of the target. It refers to the distance from a point on the circular ring on the back of the impeller to the axis of rotation. This refers to the impeller back radius being static pressure at the point This refers to the impeller outlet radius, This refers to the radius of the sealing tooth tip, This refers to the impeller outlet static pressure, This refers to the gas density at the impeller outlet. It refers to the candidate rotational angular velocity of the gas in the back cavity.

[0113] Optionally, the target rear-end axial force determining element is used for:

[0114] When the intake type is atmospheric pressure intake, according to Determine the axial force at the target rear end:

[0115] ;

[0116] When the intake type is atmospheric pressure intake, according to Determine the axial force at the target rear end:

[0117] ;

[0118] in, This refers to the axial force at the rear end of the target. This refers to the impeller outlet radius, This refers to the radius of the sealing tooth tip, This refers to the impeller outlet static pressure, This refers to the gas density at the impeller outlet. This refers to the candidate rotational angular velocity of the gas in the back cavity. This refers to the actual angular velocity of the gas in the back cavity.

[0119] The aerodynamic axial force calculation device for a semi-open centrifugal impeller provided in this embodiment of the invention can execute the aerodynamic axial force calculation method for a semi-open centrifugal impeller provided in any embodiment of the invention, and has the corresponding functional modules and beneficial effects of the method.

[0120] Figure 5 A schematic diagram of an electronic device 10, which can be used to implement embodiments of the present invention, is shown. The electronic device is intended to represent various forms of digital computers, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device can also represent various forms of mobile devices, such as personal digital processors, cellular phones, smartphones, wearable devices (e.g., helmets, glasses, watches, etc.), and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely illustrative and are not intended to limit the implementation of the invention described and / or claimed herein.

[0121] like Figure 5 As shown, the electronic device 10 includes at least one processor 11 and a memory, such as a read-only memory (ROM) 12 or a random access memory (RAM) 13, communicatively connected to the at least one processor 11. The memory stores computer programs executable by the at least one processor. The processor 11 can perform various appropriate actions and processes based on the computer program stored in the ROM 12 or loaded from storage unit 18 into the RAM 13. The RAM 13 can also store various programs and data required for the operation of the electronic device 10. The processor 11, ROM 12, and RAM 13 are interconnected via a bus 14. An input / output (I / O) interface 15 is also connected to the bus 14.

[0122] Multiple components in electronic device 10 are connected to I / O interface 15, including: input unit 16, such as keyboard, mouse, etc.; output unit 17, such as various types of displays, speakers, etc.; storage unit 18, such as disk, optical disk, etc.; and communication unit 19, such as network card, modem, wireless transceiver, etc. Communication unit 19 allows electronic device 10 to exchange information / data with other devices through computer networks such as the Internet and / or various telecommunications networks.

[0123] Processor 11 can be a variety of general-purpose and / or special-purpose processing components with processing and computing capabilities. Some examples of processor 11 include, but are not limited to, central processing unit (CPU), graphics processing unit (GPU), various special-purpose artificial intelligence (AI) computing chips, various processors running machine learning model algorithms, digital signal processors (DSPs), and any suitable processor, controller, microcontroller, etc. Processor 11 performs the various methods and processes described above, such as the method for calculating the aerodynamic axial force of a semi-open centrifugal impeller.

[0124] In some embodiments, the method for calculating the aerodynamic axial force of a semi-open centrifugal impeller can be implemented as a computer program tangibly contained in a computer-readable storage medium, such as storage unit 18. In some embodiments, part or all of the computer program can be loaded and / or installed on electronic device 10 via ROM 12 and / or communication unit 19. When the computer program is loaded into RAM 13 and executed by processor 11, one or more steps of the method for calculating the aerodynamic axial force of a semi-open centrifugal impeller described above can be performed. Alternatively, in other embodiments, processor 11 can be configured to perform the method for calculating the aerodynamic axial force of a semi-open centrifugal impeller by any other suitable means (e.g., by means of firmware).

[0125] Various embodiments of the systems and techniques described above herein can be implemented in digital electronic circuit systems, integrated circuit systems, field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), application-specific standard products (ASSPs), system-on-a-chip (SoCs), complex programmable logic devices (CPLDs), computer hardware, firmware, software, and / or combinations thereof. These various embodiments may include implementations in one or more computer programs that can be executed and / or interpreted on a programmable system including at least one programmable processor, which may be a dedicated or general-purpose programmable processor, capable of receiving data and instructions from a storage system, at least one input device, and at least one output device, and transmitting data and instructions to the storage system, the at least one input device, and the at least one output device.

[0126] Computer programs used to implement the methods of the present invention may be written in any combination of one or more programming languages. These computer programs may be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing device, such that when executed by the processor, the computer programs cause the functions / operations specified in the flowcharts and / or block diagrams to be performed. The computer programs may be executed entirely on a machine, partially on a machine, or as a standalone software package, partially on a machine and partially on a remote machine, or entirely on a remote machine or server.

[0127] In the context of this invention, a computer-readable storage medium can be a tangible medium that may contain or store a computer program for use by or in conjunction with an instruction execution system, apparatus, or device. A computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatus, or devices, or any suitable combination thereof. Alternatively, a computer-readable storage medium may be a machine-readable signal medium. More specific examples of machine-readable storage media include electrical connections based on one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fibers, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof.

[0128] To provide interaction with a user, the systems and techniques described herein can be implemented on an electronic device having: a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user; and a keyboard and pointing device (e.g., a mouse or trackball) through which the user provides input to the electronic device. Other types of devices can also be used to provide interaction with the user; for example, feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form (including sound input, voice input, or tactile input).

[0129] The systems and technologies described herein can be implemented in computing systems that include backend components (e.g., as data servers), or middleware components (e.g., application servers), or frontend components (e.g., user computers with graphical user interfaces or web browsers through which users can interact with implementations of the systems and technologies described herein), or any combination of such backend, middleware, or frontend components. The components of the system can be interconnected via digital data communication of any form or medium (e.g., communication networks). Examples of communication networks include local area networks (LANs), wide area networks (WANs), blockchain networks, and the Internet.

[0130] A computing system can include clients and servers. Clients and servers are generally located far apart and typically interact through communication networks. The client-server relationship is created by computer programs running on the respective computers and having a client-server relationship with each other. The server can be a cloud server, also known as a cloud computing server or cloud host, which is a hosting product within the cloud computing service system to address the shortcomings of traditional physical hosts and VPS services, such as high management difficulty and weak business scalability.

[0131] It should be understood that the various forms of processes shown above can be used, with steps reordered, added, or deleted. For example, the steps described in this invention can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution of this invention can be achieved, and this is not limited herein.

[0132] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A method for calculating the aerodynamic axial force of a semi-open centrifugal impeller, characterized in that, include: Obtain the impeller geometry information corresponding to the semi-open centrifugal impeller to be calculated, as well as the aerodynamic operating condition information related to the semi-open centrifugal impeller. The impeller geometry information includes, but is not limited to, the impeller inlet hub radius and blade tip radius, and the sealing tooth tip radius. The aerodynamic operating condition information includes, but is not limited to, the impeller outlet static pressure, inlet static pressure, inlet mass flow rate, impeller angular velocity, and gas density. Based on the first front-end force algorithm, the first front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the second front-end force algorithm, the second front-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the intake type corresponding to the semi-open centrifugal impeller, the pressure distribution of the main channel is corrected according to the first front-end axial force and the second front-end axial force to determine the target front-end axial force on the main channel side of the semi-open centrifugal impeller. Based on the first rear-end force algorithm, the target rear-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. The combined aerodynamic axial force of the semi-open centrifugal impeller is determined based on the axial force at the front end of the target and the axial force at the rear end of the target.

2. The method according to claim 1, characterized in that, The algorithm based on the first front-end force is as follows: ； in, This refers to the axial force at the first front end. This refers to the impeller inlet tip radius, This refers to the impeller inlet blade root radius, It refers to the imported static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. This refers to the import quality flow rate, This refers to the inlet axial velocity.

3. The method according to claim 1, characterized in that, The second front-end force algorithm is as follows: ； in, This refers to the axial force at the second front end. This refers to the impeller inlet tip radius, This refers to the impeller outlet radius, This refers to the impeller inlet static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. This refers to the static pressure at the impeller outlet.

4. The method according to claim 1, characterized in that, The step of determining the target front-end axial force on the main flow side of the semi-open centrifugal impeller by correcting the main flow pressure distribution based on the first and second front-end axial forces according to the intake type corresponding to the semi-open centrifugal impeller includes: When the intake type is atmospheric pressure intake, the axial force at the target front end is as follows: ； When the intake type is non-pressure intake, the axial force at the target front end is as follows: ； in, This refers to the axial force at the front end of the target. This refers to the axial force at the first front end. This refers to the impeller inlet tip radius, This refers to the impeller inlet blade root radius, It refers to the imported static pressure, It refers to the distance from a point on the impeller inlet ring to the axis of rotation. This refers to the import quality flow rate, This refers to the inlet axial speed, This refers to the axial force at the second front end. This refers to the impeller outlet radius, This refers to the impeller inlet static pressure, This refers to the static pressure at the impeller outlet.

5. The method according to claim 1, characterized in that, The method based on the first rear-end force algorithm, which determines the target rear-end axial force on the main flow side of the semi-open centrifugal impeller according to the impeller geometry and aerodynamic operating conditions, includes: Based on the first rear-end force algorithm, the initial rear-end axial force on the main flow side of the semi-open centrifugal impeller is determined according to the impeller geometry information and the aerodynamic operating condition information. Based on the intake type corresponding to the semi-open centrifugal impeller, the initial rear axial force is corrected to obtain the target rear axial force.

6. The method according to claim 1 or 5, characterized in that, The first back-end force algorithm is as follows: ； in, This refers to the axial force at the rear end of the target. It refers to the distance from a point on the circular ring on the back of the impeller to the axis of rotation. This refers to the impeller back radius being static pressure at the point This refers to the impeller outlet radius, This refers to the radius of the sealing tooth tip, This refers to the impeller outlet static pressure, This refers to the gas density at the impeller outlet. It refers to the candidate rotational angular velocity of the gas in the back cavity.

7. The method according to claim 6, characterized in that, Based on the intake type corresponding to the semi-open centrifugal impeller, the initial rear-end axial force is corrected to obtain the target rear-end axial force, including: When the intake type is atmospheric pressure intake, The axial force at the rear end of the target is as follows: ； When the intake type is atmospheric pressure intake, The axial force at the rear end of the target is as follows: ； in, This refers to the axial force at the rear end of the target. This refers to the impeller outlet radius, This refers to the radius of the sealing tooth tip, This refers to the impeller outlet static pressure, This refers to the gas density at the impeller outlet. This refers to the candidate rotational angular velocity of the gas in the back cavity. This refers to the actual angular velocity of the gas in the back cavity.

8. A device for calculating the aerodynamic axial force of a semi-open centrifugal impeller, characterized in that, include: The impeller-related data acquisition module is used to acquire the impeller geometry information corresponding to the semi-open centrifugal impeller to be calculated, as well as the aerodynamic operating condition information related to the semi-open centrifugal impeller. The impeller geometry information includes, but is not limited to, the impeller inlet hub radius and blade tip radius, and the sealing tooth tip radius. The aerodynamic operating condition information includes, but is not limited to, the impeller outlet static pressure, inlet static pressure, inlet mass flow rate, impeller angular velocity, and gas density. The front-end axial force determination module is used to determine the first front-end axial force on the main flow side of the semi-open centrifugal impeller based on the first front-end force algorithm, according to the impeller geometry information and the aerodynamic operating condition information, and to determine the second front-end axial force on the main flow side of the semi-open centrifugal impeller based on the second front-end force algorithm, according to the impeller geometry information and the aerodynamic operating condition information. The front-end axial force correction module is used to correct the main flow pressure distribution based on the first front-end axial force and the second front-end axial force according to the intake type corresponding to the semi-open centrifugal impeller, and to determine the target front-end axial force on the main flow side of the front end of the semi-open centrifugal impeller. The rear axial force determination module is used to determine the target rear axial force on the front main flow side of the semi-open centrifugal impeller based on the first rear force algorithm, according to the impeller geometry information and the aerodynamic operating condition information. The integrated axial force determination module is used to determine the integrated aerodynamic axial force of the semi-open centrifugal impeller based on the target front-end axial force and the target rear-end axial force.

9. An electronic device, characterized in that, The electronic device includes: At least one processor; and A memory communicatively connected to the at least one processor; wherein, The memory stores a computer program that can be executed by the at least one processor, the computer program being executed by the at least one processor to enable the at least one processor to perform the method for calculating the aerodynamic axial force of a semi-open centrifugal impeller as described in any one of claims 1-7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions that, when executed by a processor, implement the method for calculating the aerodynamic axial force of a semi-open centrifugal impeller as described in any one of claims 1-7.

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