CN117634100B - Meridian flow passage acquisition method, device, equipment and medium of multistage axial-flow compressor - Google Patents

Meridian flow passage acquisition method, device, equipment and medium of multistage axial-flow compressor Download PDF

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CN117634100B
CN117634100B CN202410106032.3A CN202410106032A CN117634100B CN 117634100 B CN117634100 B CN 117634100B CN 202410106032 A CN202410106032 A CN 202410106032A CN 117634100 B CN117634100 B CN 117634100B
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target point
axial flow
flow compressor
stage axial
compressor
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CN117634100A (en
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魏征
刘驰
李强
刘涛
郝帅
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Shaanxi Aerospace Information Technology Co ltd
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Abstract

The embodiment of the disclosure discloses a method, a device, equipment and a medium for acquiring a meridian flow passage of a multistage axial flow compressor, wherein the method for acquiring the meridian flow passage comprises the following steps: for each single-stage axial flow compressor of the multi-stage axial flow compressors, determining a first target point location, a second target point location and a third target point location based on the inlet of the rotor blade and the outlet of the stator blade; obtaining flow coefficients, radial component speeds of absolute speeds and densities respectively corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor; and determining the geometric shape of a meridian flow passage in the multistage axial flow compressor based on the flow coefficients, the absolute speed meridian split speeds and the densities respectively corresponding to the first target point position, the second target point position and the third target point position in all the single-stage axial flow compressors.

Description

Meridian flow passage acquisition method, device, equipment and medium of multistage axial-flow compressor
Technical Field
The embodiment of the disclosure relates to the technical field of axial flow compressor design, in particular to a method, a device, equipment and a medium for acquiring meridian flow passages of a multistage axial flow compressor.
Background
The multistage axial-flow compressor is a power machine widely applied to the fields of aviation, ships, electric power, metallurgy, energy, chemical industry, medicine and the like, and is one of core equipment of many large-scale industrial production enterprises. The multistage axial compressor is generally composed of a plurality of single-stage axial compressors, and each single-stage axial compressor of the plurality of single-stage axial compressors includes a row of rotor blades and a subsequent row of stator blades.
At present, the structural design of a neutron noon runner is a crucial design part in the structural design of a multistage axial-flow compressor. The reasonable meridian flow passage structure can ensure that the high-efficiency airflow dynamics performance is realized in each single-stage axial-flow compressor, and the energy loss is reduced. The structural design of the meridian flow passage in the related art has long iteration period and low calculation precision, so that the design time of the multistage axial flow compressor is prolonged seriously, the design cost is increased, and the development and market popularization of the multistage axial flow compressor are restricted seriously finally.
Disclosure of Invention
In view of this, embodiments of the present disclosure desirably provide a method, apparatus, device, and medium for obtaining a meridian flow passage of a multistage axial flow compressor; the radial flow passage in the multistage axial flow compressor can be accurately designed, the design accuracy is high, and the design period is short.
The technical scheme of the embodiment of the disclosure is realized as follows:
In a first aspect, an embodiment of the present disclosure provides a method for obtaining a meridian flow passage of a multistage axial flow compressor, which is characterized in that the method includes:
for each single-stage axial flow compressor of the multi-stage axial flow compressors, determining a first target point location, a second target point location and a third target point location based on the inlet of the rotor blade and the outlet of the stator blade; wherein the first target point is located at an inlet of the rotor blade, the second target point is located at an outlet of the rotor blade or an inlet of the stator blade, and the third target point is located at an outlet of the stator blade;
Based on the flow coefficient corresponding to the inlet of the multistage axial flow compressor and the flow coefficient corresponding to the outlet of the multistage axial flow compressor, acquiring the flow coefficients corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor respectively;
Acquiring meridian component speeds of absolute speeds corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor based on set boundary conditions and pneumatic parameters at an inlet and an outlet in the multi-stage axial flow compressor;
acquiring densities corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor based on pneumatic parameters respectively set by the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor;
and determining the geometric shape of a meridian flow passage in the multistage axial flow compressor based on the flow coefficients, the absolute speed meridian split speeds and the densities respectively corresponding to the first target point position, the second target point position and the third target point position in all the single-stage axial flow compressors.
In a second aspect, an embodiment of the present disclosure provides a meridian passage acquiring device of a multistage axial compressor, including a first determining portion, a first acquiring portion, a second acquiring portion, a third acquiring portion, and a second determining portion; wherein,
The first determination section is configured to: for each single-stage axial flow compressor of the multi-stage axial flow compressors, determining a first target point location, a second target point location and a third target point location based on the inlet of the rotor blade and the outlet of the stator blade; wherein the first target point is located at an inlet of the rotor blade, the second target point is located at an outlet of the rotor blade or an inlet of the stator blade, and the third target point is located at an outlet of the stator blade;
The first acquisition section is configured to: based on the flow coefficient corresponding to the inlet of the multistage axial flow compressor and the flow coefficient corresponding to the outlet of the multistage axial flow compressor, acquiring the flow coefficients corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor respectively;
The second acquisition section is configured to: acquiring meridian component speeds of absolute speeds corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor based on set boundary conditions and pneumatic parameters at an inlet and an outlet in the multi-stage axial flow compressor;
The third acquisition section is configured to: acquiring densities corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor based on pneumatic parameters respectively set by the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor;
The second determination section is configured to: and determining the geometric shape of a meridian flow passage in the multistage axial flow compressor based on the flow coefficients, the absolute speed meridian split speeds and the densities respectively corresponding to the first target point position, the second target point position and the third target point position in all the single-stage axial flow compressors.
In a third aspect, the disclosed embodiments provide a computing device comprising: a communication interface, a memory and a processor; the components are coupled together by a bus system; wherein,
The communication interface is used for receiving and transmitting signals in the process of receiving and transmitting information with other external network elements;
The memory is used for storing a computer program capable of running on the processor;
the processor is configured to execute the steps of the radial flow channel acquisition method of the multistage axial flow compressor according to the first aspect when the computer program is executed.
In a fourth aspect, an embodiment of the present disclosure provides a computer storage medium storing a meridian passage acquisition procedure of a multistage axial compressor, where the meridian passage acquisition procedure of the multistage axial compressor is executed by at least one processor to implement the steps of the meridian passage acquisition method of the multistage axial compressor according to the first aspect.
The embodiment of the disclosure provides a method, a device, equipment and a medium for acquiring meridian flow passages of a multistage axial flow compressor; for each single stage axial flow compressor of the multi-stage axial flow compressors, a first target point location at the inlet of the rotor blade, a second target point location at the outlet of the rotor blade or the inlet of the stator blade, and a third target point location at the outlet of the stator blade are determined based on the inlet of the rotor blade and the outlet of the stator blade. And acquiring flow coefficients corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor based on the flow coefficients corresponding to the inlet of the multi-stage axial flow compressor and the flow coefficients corresponding to the outlet of the multi-stage axial flow compressor. And acquiring meridian component speeds of absolute speeds corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor respectively according to the set boundary conditions and the aerodynamic parameters at the inlet and the outlet of the multi-stage axial flow compressor. And acquiring densities corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor based on pneumatic parameters respectively set by the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor, and finally determining the geometric shape of a meridian flow passage in the multi-stage axial flow compressor based on flow coefficients, absolute velocity meridian split speeds and densities corresponding to the first target point position, the second target point position and the third target point position in all the single-stage axial flow compressors. Through the technical scheme provided by the embodiment of the disclosure, the structure of the meridian runner in the multistage axial flow compressor can be accurately designed, the design accuracy is high, and the design period is short.
Drawings
Fig. 1 is a meridional view of a 5-stage axial compressor provided by an embodiment of the present disclosure.
Fig. 2 is a geometric structure diagram of a meridian flow passage in a multistage axial compressor provided in an embodiment of the present disclosure.
Fig. 3 is a schematic annular cross-sectional view of a meridional flow channel provided by an embodiment of the present disclosure.
Fig. 4 is a meridional view of an equal-outer diameter multistage axial compressor provided by an embodiment of the present disclosure.
Fig. 5 is a meridian view of a multi-stage axial compressor with equal diameter provided by an embodiment of the present disclosure.
Fig. 6 is a meridional view of a multi-stage axial compressor of equal inner diameter provided by an embodiment of the present disclosure.
Fig. 7 is a schematic flow chart of a meridian flow path obtaining method of a multistage axial flow compressor according to an embodiment of the disclosure.
Fig. 8 is a schematic position diagram of each target point in the 2-stage axial compressor according to an embodiment of the present disclosure.
Fig. 9 is a schematic diagram of a velocity triangle of a first target point according to an embodiment of the disclosure.
Fig. 10 is a schematic diagram of a velocity component triangle of a first target point according to an embodiment of the disclosure.
Fig. 11 is a schematic diagram of a velocity triangle of a second target point according to an embodiment of the disclosure.
Fig. 12 is a schematic diagram of a velocity component triangle of a second target point provided in an embodiment of the present disclosure.
Fig. 13 is a schematic diagram of a speed triangle of a third target point according to an embodiment of the disclosure.
Fig. 14 is a schematic diagram of a velocity component triangle of a second target point provided in an embodiment of the present disclosure.
Fig. 15 is a flowchart of an iterative calculation method of a circumferential velocity corresponding to a first target point in a1 st single-stage axial flow compressor according to an embodiment of the present disclosure.
Fig. 16 is a schematic view of radial flow channel geometry of a single stage axial flow compressor provided in an embodiment of the present disclosure.
FIG. 17 is a schematic illustration of a geometry of a rotor blade provided by an embodiment of the present disclosure.
Fig. 18 is a schematic view of the geometry of a stator vane provided by an embodiment of the present disclosure.
Fig. 19 is a schematic diagram of a meridian flow path acquiring device of a multistage axial compressor according to an embodiment of the present disclosure.
Fig. 20 is a schematic structural diagram of a computing device according to an embodiment of the present disclosure.
Detailed Description
The technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure.
Referring to fig. 1, a meridional view of a 5-stage axial compressor is illustratively provided. As can be seen from fig. 1, in the 5-stage axial flow compressor, 1 rotor blade Rot and 1 stator blade Sta are contained in each single-stage axial flow compressor. The rotor blade and the stator blade may be collectively referred to as a blade. The solid line G in fig. 1 represents a casing-type line, the solid line H represents a hub-type line, and the region between the casing-type line G and the hub-type line H is a meridional flow path. In the specific implementation process, the rotor blades and the stator blades are distributed in the meridian flow passage and are used for jointly determining the aerodynamic performance of the multistage axial flow compressor. The dash-dot line Rs in fig. 1 indicates the rotation axis of the 5-stage axial flow compressor. In some examples, because the multistage axial compressor compresses air in stages, its air density increases continuously along the meridional flow path, and thus the area of the meridional flow path decreases continuously in stages. As shown in fig. 2, which shows the geometric parameters of the meridional flow channels in a multistage axial compressor. Wherein R t represents the corresponding case radius of each single-stage axial-flow compressor, and refers to the vertical distance between the corresponding case molded line of each single-stage axial-flow compressor and the rotating shaft. R m represents the average radius corresponding to each single-stage axial-flow compressor, and refers to the vertical distance between the average radius position corresponding to each single-stage axial-flow compressor and the rotating shaft. R h represents the hub radius corresponding to each single-stage axial flow compressor, and refers to the vertical distance between the hub molded line corresponding to each single-stage axial flow compressor and the rotating shaft.
It can be understood that the casing radius R t, the average radius R m and the hub radius R h corresponding to each single-stage axial flow compressor need to be obtained in the structural design of the meridian flow passage. When designing the meridian flow passage, the annular area corresponding to the meridian flow passage in each single-stage axial flow compressor is also required to be calculated, and the annular area of the meridian flow passage is shown as a diagonal filling area in fig. 3.
In the related art, the structural design of the meridian flow passage is solved based on the specific condition that the multistage axial flow compressor is equal in outer diameter, equal in average diameter or equal in inner diameter. Referring to fig. 4, a meridional view of an equal outer diameter multi-stage axial compressor is shown. As can be seen from fig. 4, the main characteristic of the equal-outer-diameter multistage axial flow compressor is that the corresponding casing radiuses of all the single-stage axial flow compressors are equal, so that the circumferential speeds of all the single-stage axial flow compressors in the equal-outer-diameter multistage axial flow compressor at the casing molded lines can be obtained to be equal. Referring to fig. 5, a meridional view of a multi-stage axial compressor of equal diameter is shown. As can be seen from fig. 5, the equal-diameter multistage axial flow compressor is mainly characterized in that the average radii corresponding to all the single-stage axial flow compressors are equal, so that the circumferential speeds of all the single-stage axial flow compressors in the equal-diameter multistage axial flow compressor at the equal-diameter positions can be obtained to be equal. Referring to fig. 6, a meridional view of a multi-stage axial compressor of equal inner diameter is shown. As can be seen from fig. 6, the main characteristic of the equal-inner-diameter multistage axial flow compressor is that the hub radius corresponding to all the single-stage axial flow compressors is equal, so that the circumferential speeds of all the single-stage axial flow compressors in the equal-inner-diameter multistage axial flow compressor at the hub molded line are equal. However, in the implementation process, the multistage axial flow compressor is not designed according to equal outer diameters, equal average diameters or equal inner diameters. Therefore, if the design mode of equal outer diameter, equal average diameter or equal inner diameter is adopted when designing the meridian flow passage in the multistage axial flow compressor, the design precision of the multistage axial flow compressor is low, and the design iteration period is further prolonged.
Based on the foregoing, it is desirable for the embodiments of the present disclosure to provide a technical solution capable of accurately obtaining geometric parameters of a meridian flow passage in a multistage axial flow compressor, so as to improve design accuracy and shorten a design iteration period of the meridian flow passage. Specifically, referring to fig. 7, a method for obtaining a meridian flow passage of a multistage axial flow compressor according to an embodiment of the present disclosure is shown, and the method specifically includes the following steps.
In step S701, for each single-stage axial flow compressor of the multi-stage axial flow compressors, determining a first target point location, a second target point location, and a third target point location based on the inlet of the rotor blade and the outlet of the stator blade; the first target point is located at the inlet of the rotor blade, the second target point is located at the outlet of the rotor blade or the inlet of the stator blade, and the third target point is located at the outlet of the stator blade.
To clearly show the positional relationship of the first, second, and third target points in each single stage axial flow compressor in the embodiments of the present disclosure, taking the 1 st single stage axial flow compressor and the 2 nd single stage axial flow compressor in fig. 1 as an example, three target points in the 1 st single stage axial flow compressor include a first target point Z 1,1 located at the inlet of the rotor blade Rot1, a second target point Z 1,2 located at the outlet of the rotor blade Rot1 or the inlet of the stator blade Sta1, and a third target point Z 1,3 located at the outlet of the stator blade Sta1 as shown in fig. 8. It will be appreciated that the outlet of the stator vane stat 1 in the 1 st single-stage axial compressor corresponds to the inlet of the rotor vane Rot2 in the 2 nd single-stage axial compressor, that is, the third target point Z 1,3 of the outlet of the stator vane stat 1 in the 1 st single-stage axial compressor is the first target point Z 2,1 of the inlet of the rotor vane Rot2 in the 2 nd single-stage axial compressor, so that in the implementation process, the outlet of the rotor vane Rot2 in the 2 nd single-stage axial compressor or the inlet of the stator vane stat 2 is provided with the second target point Z 2,2 and the outlet of the stator vane stat 2 is provided with the third target point Z 2,3.
In step S702, based on the flow coefficient corresponding to the inlet of the multi-stage axial flow compressor and the flow coefficient corresponding to the outlet of the multi-stage axial flow compressor, the flow coefficients corresponding to the first target point, the second target point and the third target point in each single-stage axial flow compressor are obtained.
In the embodiment of the disclosure, the flow coefficient corresponding to the inlet of the multistage axial flow compressor is the flow coefficient corresponding to the first target point in the 1 st single-stage axial flow compressor, and the flow coefficient corresponding to the outlet of the multistage axial flow compressor is the flow coefficient corresponding to the third target point in the nth single-stage axial flow compressor, where N represents the number of single-stage axial flow compressors included in the multistage axial flow compressor.
In step S703, based on the set boundary conditions and the aerodynamic parameters at the inlet and the outlet of the multi-stage axial flow compressor, the meridian component speeds of the absolute speeds corresponding to the first, second and third target points in each single-stage axial flow compressor are obtained.
The boundary condition is a state equation. In the embodiments of the present disclosure, other state parameters for any state point can be found from any 2 thermodynamic state parameters, given the gas type and state equation. As the total pressure P 1,t,1 and the total temperature T 1,t,1 at the inlet of the known multistage axial compressor, the method can be realized by a state equationCalculating to obtain total enthalpy H 1,t,1 at the inlet of the multistage axial flow compressor and using the state equationAnd calculating to obtain the entropy value s 1,1 at the inlet of the multistage axial flow compressor. It is understood that the total enthalpy H 1,t,1 at the inlet of the multistage axial compressor is the total enthalpy corresponding to the first target point in the 1 st single-stage axial compressor, and the entropy s 1,1 at the inlet of the multistage axial compressor is the entropy corresponding to the first target point in the 1 st single-stage axial compressor.
In some examples, according to the fluid state equationIsentropic enthalpy H N,is at the outlet of the multistage axial compressor is calculated, wherein P N,3 represents static pressure at the outlet of the multistage axial compressor,/>，/>Representing the total-to-static ratio.
For the nth single stage axial flow compressor, the velocity triangle of the first target point location is shown in fig. 9. As shown in fig. 9, the pneumatic parameters corresponding to the velocity triangle of the first target point in the nth single-stage axial flow compressor include an absolute velocity C n,1 of the first target point, a relative velocity W n,1 of the first target point, a circumferential velocity U n,1 of the first target point, an absolute airflow angle α n,1 of the first target point, and a relative airflow angle β n,1 of the first target point, so as to obtain a meridional component velocity C n,m,1 of the absolute velocity of the first target point based on a correspondence between the velocity triangle of the first target point and the velocity component triangle of the first target point shown in fig. 9.
For the nth single stage axial flow compressor, the velocity triangle of the second target point is shown in fig. 11. As shown in fig. 11, the pneumatic parameters corresponding to the speed triangle of the second target point in the nth single-stage axial flow compressor include an absolute speed C n,2 of the second target point, a relative speed W n,2 of the second target point, a circumferential speed U n,2 of the second target point, and an absolute airflow angle α n,2 of the second target point, so as to obtain a meridian split speed C n,m,2 of the absolute speed of the second target point based on the corresponding relationship between the speed triangle of the second target point shown in fig. 11 and the speed component triangle of the second target point shown in fig. 12.
For the nth single stage axial flow compressor, the speed triangle of the third target point is shown in fig. 13. As shown in fig. 13, the pneumatic parameters corresponding to the speed triangle of the third target point in the nth single-stage axial flow compressor include the absolute speed C n,3 of the third target point, the circumferential speed U n,3 of the third target point, and the absolute airflow angle α n,3 of the third target point, so as to obtain the meridian component speed C n,m,3 of the absolute speed of the third target point based on the corresponding relationship between the speed triangle of the third target point shown in fig. 13 and the speed component triangle of the third target point shown in fig. 14. It is understood that the aerodynamic parameters corresponding to the third target point in the nth single-stage axial-flow compressor, such as the absolute speed C n,3 of the third target point in the nth single-stage axial-flow compressor, the circumferential speed U n,3 of the third target point in the nth single-stage axial-flow compressor, the absolute airflow angle α n,3 of the third target point in the nth single-stage axial-flow compressor, and the like are aerodynamic parameters corresponding to the first target point in the n+1th single-stage axial-flow compressor, such as the absolute speed C n+1,1 of the first target point in the n+1th single-stage axial-flow compressor, the circumferential speed U n+1,1 of the first target point in the n+1th single-stage axial-flow compressor, and the absolute airflow angle α n+1,1 of the first target point in the n+1th single-stage axial-flow compressor.
In step S704, based on the pneumatic parameters respectively set in the first target point location, the second target point location, and the third target point location in each single-stage axial flow compressor, densities respectively corresponding to the first target point location, the second target point location, and the third target point location in each single-stage axial flow compressor are obtained.
In step S705, the geometry of the meridian flow path in the multi-stage axial flow compressor is determined based on the flow coefficients, the absolute speed meridian speeds and the densities respectively corresponding to the first, second and third target points in all the single-stage axial flow compressors.
For the solution shown in fig. 7, for each single-stage axial-flow compressor of the multi-stage axial-flow compressors, a first target point located at the inlet of the rotor blade, a second target point located at the outlet of the rotor blade or the inlet of the stator blade, and a third target point located at the outlet of the stator blade are determined based on the inlet of the rotor blade and the outlet of the stator blade. And acquiring flow coefficients corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor based on the flow coefficients corresponding to the inlet of the multi-stage axial flow compressor and the flow coefficients corresponding to the outlet of the multi-stage axial flow compressor. And acquiring radial component speeds of absolute speeds corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor respectively according to the set boundary conditions and the aerodynamic parameters at the inlet and the outlet of the multi-stage axial flow compressor. And acquiring densities corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor based on pneumatic parameters respectively set by the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor, and finally determining the geometric shape of a meridian flow passage in the multi-stage axial flow compressor based on flow coefficients, absolute velocity meridian split speeds and densities corresponding to the first target point position, the second target point position and the third target point position in all the single-stage axial flow compressors. Through the technical scheme provided by the embodiment of the disclosure, the structure of the meridian runner in the multistage axial flow compressor can be accurately designed, the design accuracy is high, and the period is short.
For the technical solution shown in fig. 7, in some possible embodiments, based on a flow coefficient corresponding to an inlet of the multi-stage axial flow compressor and a flow coefficient corresponding to an outlet of the multi-stage axial flow compressor, obtaining flow coefficients corresponding to a first target point location, a second target point location, and a third target point location in each single-stage axial flow compressor includes:
Calculating according to formula (1) to obtain a flow coefficient corresponding to a first target point position in the nth single-stage axial flow compressor ：
（1）
Wherein k 1 =2n-1, N is greater than or equal to 1 and less than or equal to N, and N represents the number of single-stage axial flow compressors contained in the multistage axial flow compressor; x 1=1;x2 = 2n+1; representing flow coefficients corresponding to inlets of the multistage axial flow compressor; /(I) Representing flow coefficients corresponding to the outlets of the multistage axial flow compressors;
Calculating according to formula (2) to obtain a flow coefficient corresponding to a second target point position in the nth single-stage axial flow compressor ：
（2）
Wherein k 2 =2n;
Calculating according to formula (3) to obtain a flow coefficient corresponding to a third target point position in the nth single-stage axial flow compressor ：
（3）
Where k 3 =2n+1.
In the implementation process, the flow coefficient corresponding to the inlet of the multistage axial flow compressorAnd flow coefficient/>, corresponding to the outlet of the multistage axial compressorThe flow coefficients corresponding to the first target point position, the second target point position and the third target point position in any single-stage axial flow compressor can be respectively obtained through the formulas (1), (2) and (3) because the flow coefficients are preset pneumatic parameters.
For the technical solution shown in fig. 7, in some possible embodiments, obtaining meridian component speeds of absolute speeds corresponding to the first target point location, the second target point location, and the third target point location in each single-stage axial flow compressor based on the set boundary conditions and aerodynamic parameters at the inlet and the outlet in the multi-stage axial flow compressor includes:
Determining a circumferential speed U 1,1 and an absolute speed C 1,1 corresponding to a first target point position in a 1 st single-stage axial flow compressor in the multi-stage axial flow compressor and an absolute speed C N,3 corresponding to a third target point position in an N th single-stage axial flow compressor in the multi-stage axial flow compressor based on set boundary conditions and aerodynamic parameters at an inlet and an outlet in the multi-stage axial flow compressor;
In the nth single stage axial flow compressor:
Determining the meridian split speed of the absolute speed corresponding to the first target point position in the nth single-stage axial flow compressor based on the absolute speed C n,1 corresponding to the first target point position in the nth single-stage axial flow compressor; wherein N is more than or equal to 1 and less than or equal to N, and N represents the number of single-stage axial flow compressors contained in the multistage axial flow compressors;
Determining the meridian split speed of the absolute speed corresponding to the third target point position in the nth single-stage axial flow compressor based on the absolute speed C n,3 corresponding to the third target point position in the nth single-stage axial flow compressor;
And determining the meridian split speed of the absolute speed corresponding to the second target point position in the nth single-stage axial flow compressor based on the circumferential speed corresponding to the first target point position in the nth single-stage axial flow compressor and the meridian split speed of the absolute speed or based on the circumferential speed corresponding to the first target point position in the nth single-stage axial flow compressor and the meridian split speed of the absolute speed corresponding to the third target point position.
In the embodiment of the disclosure, first, a circumferential speed U 1,1 and an absolute speed C 1,1 corresponding to a first target point in a1 st single-stage axial flow compressor and an absolute speed C N,3 corresponding to a third target point in an nth single-stage axial flow compressor are calculated, and then meridian component speeds of the absolute speeds corresponding to the first target point, the second target point and the third target point in each single-stage axial flow compressor are obtained step by step.
For the above-described embodiments, in some examples, determining the circumferential speed U 1,1 and the absolute speed C 1,1 corresponding to the first target point location in the 1 st single-stage axial compressor of the multi-stage axial compressors and the absolute speed C N,3 corresponding to the third target point location in the nth single-stage axial compressor of the multi-stage axial compressors based on the set boundary conditions and the aerodynamic parameters at the inlet and the outlet in the multi-stage axial compressors includes:
Based on the set total enthalpy H 1,t,1 at the inlet of the multistage axial flow compressor and isentropic enthalpy H N,is at the outlet of the multistage axial flow compressor, calculating according to formula (4) to obtain an initial difference value between isentropic enthalpy H N,is and total enthalpy H 1,t,1 at the inlet ：
（4）
In the first placeIn the iterative calculation:
stage load coefficient corresponding to 1 st stage axial flow compressor based on setting Stage load factor/>, corresponding to an nth single stage axial flow compressorFirst/>The difference delta H tt,1-N,i-1 obtained in the iterative calculation is calculated according to the formula (5) to obtain the circumferential speed U 1,1,i corresponding to the first target point position in the 1 st single-stage axial flow compressor:
（5）
Wherein when When (1)Difference value obtained in iterative calculation/>For the initial difference/>；
Based on the peripheral speed U 1,1,i corresponding to the first target point in the 1 st single-stage axial-flow compressor, calculating according to the formula (6) and the formula (7) respectively to obtain the absolute speed C 1,1,i corresponding to the first target point in the 1 st single-stage axial-flow compressor and the absolute speed C N,3,i corresponding to the third target point in the N-th single-stage axial-flow compressor:
（6）
（7）
Wherein, Representing flow coefficients corresponding to inlets of the multistage axial flow compressor; /(I)Representing an absolute airflow angle corresponding to a first target point position in the 1 st single-stage axial flow compressor; /(I)Representing flow coefficients corresponding to the outlets of the multistage axial flow compressors; r r,1-N represents the average diameter ratio between the outlet and the inlet of the multistage axial compressor, and/>R m,1 represents the average radius at the inlet of the multistage axial compressor; r m,N represents the average radius at the outlet of the multistage axial compressor; /(I)Representing an absolute airflow angle corresponding to a third target point in the Nth single-stage axial-flow compressor;
Based on the absolute speed C N,3,i corresponding to the third target point in the Nth single-stage axial-flow compressor, calculating according to the following formula (8) to obtain the total enthalpy H N,t,3,i at the outlet of the multi-stage axial-flow compressor:
（8）
Wherein, ；/>Representing isentropic efficiency;
According to Calculated as (I) >Difference/>, of total enthalpy H N,t,3,i at outlet and total enthalpy H 1,t,1 at inlet of multistage axial compressor in secondary iterative calculation；
For the firstDifference/>, obtained in the iterative calculation, of total enthalpy H N,t,3,i at the outlet and total enthalpy H 1,t,1 at the inlet of the multistage axial compressorAnd/>Difference/>, obtained in the iterative calculation, of total enthalpy H N,t,3,i-1 at the outlet and total enthalpy H 1,t,1 at the inlet of the multistage axial compressorComparing and calculating;
If it is According to/>Calculating to obtain the peripheral speed U 1,1 corresponding to the first target point position in the final 1 st single-stage axial flow compressor, calculating to obtain the absolute speed C 1,1 corresponding to the first target point position in the 1 st single-stage axial flow compressor according to the formula (6), calculating to obtain the absolute speed C N,3 corresponding to the third target point position in the N single-stage axial flow compressor according to the formula (7), and ending the iterative calculation;
If it is Based on/>Execute the/>And (5) carrying out iterative calculation.
Fig. 15 shows the steps of a method for obtaining the peripheral speed U 1,1 corresponding to the first target point in the 1 st single-stage axial flow compressor, the absolute speed C 1,1, and the absolute speed C N,3 corresponding to the third target point in the nth single-stage axial flow compressor, specifically as follows:
In step S1501, an initial difference between isentropic enthalpy H N,is at the outlet of the multistage axial compressor and total enthalpy H 1,t,1 at the inlet of the multistage axial compressor is obtained according to equation (4) 。
In the first placeIn the iterative calculation:
In step S1502, a circumferential speed U 1,1,i corresponding to a first target point in the 1 st single-stage axial flow compressor is calculated according to equation (5).
In some examples, the 1 st single stage axial flow compressor corresponds to a stage load factorStage load coefficients/>, corresponding to the nth single-stage axial flow compressorIs preset.
In step S1503, based on the circumferential velocity U 1,1,i corresponding to the first target point in the 1 st single-stage axial flow compressor calculated in step S1502, the absolute velocity C 1,1,i corresponding to the first target point in the 1 st single-stage axial flow compressor and the absolute velocity C N,3,i corresponding to the third target point in the nth single-stage axial flow compressor can be calculated according to the formula (6) and the formula (7).
In some examples, for the flow coefficients corresponding at the inlet of the multistage axial compressor in formulas (6) and (7)Flow coefficient/>, corresponding to outlet of multistage axial-flow compressorAbsolute airflow angle/>, corresponding to first target point location in 1 st single-stage axial flow compressorThe absolute airflow angle corresponding to the third target point in the nth single-stage axial flow compressor and the average diameter ratio R r,1-N between the outlet and the inlet of the multistage axial flow compressor are preset.
In step S1504, based on the absolute speed C N,3,i corresponding to the third target point in the nth single-stage axial-flow compressor calculated in step S1503, the total enthalpy H N,t,3,i of the outlet of the multistage axial-flow compressor is calculated according to formula (8).
In some examples, for isentropic efficiency in equation (8)Is preset.
In step S1505, the total enthalpy H N,t,3,i of the outlet of the multistage axial compressor calculated in step S1504 is calculated according toCan be calculated as the/>Difference/>, of total enthalpy H N,t,3,i at outlet and total enthalpy H 1,t,1 at inlet of multistage axial compressor in secondary iterative calculation。
In step S1506, the calculated first step of step S1505 is performedDifference/>, obtained in the iterative calculation, of total enthalpy H N,t,3,i at the outlet and total enthalpy H 1,t,1 at the inlet of the multistage axial compressorAnd/>Difference/>, obtained in the iterative calculation, of total enthalpy H N,t,3,i-1 at the outlet and total enthalpy H 1,t,1 at the inlet of the multistage axial compressorA comparison is made. If the comparison result is less than or equal to 0.1, step S1507 is executed to end the iterative computation. Otherwise, based on/>Step S1502 is continued to be executed.
It can be appreciated that in the embodiment of the disclosure, the influence of the uncertain factors on the total enthalpy H 1,t,1 at the inlet of the multistage axial flow compressor and the isentropic enthalpy H N,is at the outlet of the multistage axial flow compressor is eliminated through iterative calculation, so that the total enthalpy H 1,t,1 at the inlet of the multistage axial flow compressor and the isentropic enthalpy H N,is at the outlet of the multistage axial flow compressor can be as close as possible, so as to improve the calculation precision of the circumferential speed U 1,1 and the absolute speed C 1,1 corresponding to the first target point in the 1 st single stage axial flow compressor and the absolute speed C N,3 corresponding to the third target point in the nth single stage axial flow compressor in the multistage axial flow compressor, and reduce the calculation error.
For the above embodiments, in some examples, determining the meridian split velocity of the absolute velocity corresponding to the first target point in the nth single stage axial compressor based on the absolute velocity C n,1 corresponding to the first target point in the nth single stage axial compressor includes:
According to the absolute speed C n,1 corresponding to the first target point in the nth single-stage axial flow compressor, the meridian direction component speed C n,m,1 of the absolute speed corresponding to the first target point in the nth single-stage axial flow compressor is obtained according to the formula (9):
（9）
Wherein, And the absolute airflow angle corresponding to the first target point position in the nth single-stage axial flow compressor is represented.
Taking the 1 st single-stage axial flow compressor as an example, when the circumferential speed U 1,1 and the absolute speed C 1,1 corresponding to the first target point in the 1 st single-stage axial flow compressor are calculated, the absolute airflow angle corresponding to the first target point in the 1 st single-stage axial flow compressor is knownIn the case of (2), according to the geometric relationships shown in fig. 9 and 10, other aerodynamic parameters of the first target point in the 1 st single-stage axial flow compressor can be calculated, specifically as follows:
Wherein, C 1,m,1 represents the meridian direction component speed of the absolute speed corresponding to the first target point position in the 1 st single-stage axial flow compressor; c 1,u,1 represents the circumferential partial velocity of the absolute velocity corresponding to the first target point in the 1 st single-stage axial flow compressor; w 1,1 represents the relative speed corresponding to the first target point in the 1 st single-stage axial flow compressor; w 1,u,1 represents the circumferential partial velocity of the relative velocity corresponding to the first target point in the 1 st single-stage axial flow compressor; w 1,m,1 represents the meridian direction component speed of the relative speed corresponding to the first target point position in the 1 st single-stage axial flow compressor; and the relative air flow angle corresponding to the first target point position in the 1 st single-stage axial flow compressor is shown. Based on the calculation result, according to the speed triangle corresponding to the first target point location, the rest pneumatic parameters corresponding to the first target point location can be calculated.
For the above embodiments, in some examples, determining the meridian split velocity of the absolute velocity corresponding to the third target point in the nth single stage axial flow compressor based on the absolute velocity C n,3 corresponding to the third target point in the nth single stage axial flow compressor includes:
according to the absolute speed C n,3 corresponding to the third target point in the nth single-stage axial flow compressor, the meridian direction component speed C n,m,3 of the absolute speed corresponding to the third target point in the nth single-stage axial flow compressor is obtained according to the formula (10):
（10）
wherein, C n,3 represents the absolute speed corresponding to the third target point in the nth single-stage axial flow compressor; and the absolute airflow angle corresponding to the third target point position in the nth single-stage axial flow compressor is represented.
It will be appreciated that in calculating the meridian split velocity C n,m,3 of the absolute velocity corresponding to the third target point in the nth single stage axial flow compressor, the following relationship may be set in some examples: c n,3=CN,3 . When the absolute speed C n,3 corresponding to the third target point position and the absolute airflow angle/>, corresponding to the third target point position, in the nth single-stage axial-flow compressor are knownUnder the condition of (3), the meridian direction component speed C n,m,3 of the absolute speed corresponding to the third target point position in the nth single-stage axial flow compressor can be calculated according to the formula (10). Of course, in the implementation process, the absolute speed C n,3 corresponding to the third target point in each single-stage axial-flow compressor and the absolute airflow angle corresponding to the third target pointThe setting can be performed according to actual conditions.
Taking the 1 st single-stage axial flow compressor as an example, when C 1,3=CN,3 andIn the case of (2), according to the geometric relationships shown in fig. 13 and 14, other aerodynamic parameters of the third target point in the 1 st single-stage axial flow compressor can be calculated, specifically as follows:
Wherein, C 1,m,3 represents the meridian direction component speed of the absolute speed corresponding to the third target point in the 1 st single-stage axial flow compressor; c 1,u,3 represents the circumferential component speed of the absolute speed corresponding to the third target point in the 1 st single stage axial flow compressor.
In a specific implementation process, the absolute speed C n,3 corresponding to the third target point in the nth single-stage axial-flow compressor is the absolute speed C n+1,1 corresponding to the first target point in the n+1th single-stage axial-flow compressor, and when the absolute speed C n+1,1 corresponding to the first target point in the n+1th single-stage axial-flow compressor is known, the meridian component speed C n+1,m,1 of the absolute speed corresponding to the first target point in the n+1th single-stage axial-flow compressor is calculated according to the above formula (9). Based on the calculation result, according to the speed triangle corresponding to the third target point, the rest pneumatic parameters corresponding to the third target point can be calculated.
For the above embodiments, in some examples, determining the meridian split velocity of the absolute velocity corresponding to the second target point in the nth single-stage axial compressor based on the circumferential velocity corresponding to the first target point in the nth single-stage axial compressor and the meridian split velocity of the absolute velocity or based on the circumferential velocity corresponding to the first target point in the nth single-stage axial compressor and the meridian split velocity of the absolute velocity corresponding to the third target point includes:
based on the circumferential speed U n,1 corresponding to the first target point position in the nth single-stage axial flow compressor and the meridian split speed C n,m,1 of the absolute speed, or the circumferential speed U n,1 corresponding to the first target point position in the nth single-stage axial flow compressor and the meridian split speed C n,m,3 of the absolute speed corresponding to the third target point position, calculating according to the formula (11) or the formula (12) to obtain the meridian split speed C n,m,2 of the absolute speed corresponding to the second target point position in the nth single-stage axial flow compressor:
（11）
（12）
Wherein R r,1-n,2 represents the average diameter ratio of the second target point position in the nth single-stage axial flow compressor to the first target point position in the 1 st single-stage axial flow compressor, and ，k2=2n,x1=1,x2=2n+1；/>Representing a flow coefficient corresponding to a second target point position in the nth single-stage axial flow compressor; /(I)Representing a flow coefficient corresponding to a first target point position in the nth single-stage axial flow compressor; /(I)Representing a flow coefficient corresponding to a third target point position in the nth single-stage axial flow compressor; r r,1-n,3 represents the average diameter ratio of the third target point in the nth single-stage axial-flow compressor to the first target point in the 1 st single-stage axial-flow compressor, and，k3=2n+1。
In an embodiment of the present disclosure, the location of the second target point location in each single stage axial flow compressor is not determined. In the implementation process, a relation between the aerodynamic parameters of the second target point and the aerodynamic parameters of the first target point and the aerodynamic parameters of the third target point needs to be established in each single-stage axial-flow compressor, and the relation is shown in the above formula (11) and formula (12).
In addition, in the average diameter ratio R r,1-N of the outlet and the inlet of the known multistage axial flow compressor, the average diameter ratio R r,1-n,1 of the first target point position in the nth single-stage axial flow compressor and the first target point position in the 1 st single-stage axial flow compressor is obtained through linear interpolation calculation, and the specific relation is as follows:
。
And calculating to obtain the average diameter ratio R r,1-n,2 of the second target point position in the nth single-stage axial flow compressor and the first target point position in the 1 st single-stage axial flow compressor according to the following formula:
。
And calculating according to the following formula to obtain the average diameter ratio R r,1-n,3 of the third target point position in the nth single-stage axial flow compressor and the first target point position in the 1 st single-stage axial flow compressor:
。
In some examples, for the 1 st single-stage axial compressor, after obtaining the meridian split velocity C 1,m,2 of the absolute velocity corresponding to the second target point in the 1 st single-stage axial compressor, the absolute airflow angle corresponding to the second target point in the 1 st single-stage axial compressor can be obtained according to the following formula ：
Wherein H 1,2 represents the static enthalpy value corresponding to the second target point position in the 1 st single-stage axial flow compressor,，/>Representing the level rotor strength corresponding to the 1 st single-level axial flow compressor; h 1,t,3 represents the total enthalpy corresponding to the third target point in the 1 st single-stage axial flow compressor, and，/>Representing the total-total enthalpy difference corresponding to the 1 st single-stage axial flow compressor,/>Representing the total-total enthalpy difference and/>, corresponding to the Nth single-stage axial flow compressorIs preset.
The absolute air flow angle corresponding to the second target point position in the 1 st single-stage axial flow compressor is obtainedIn the case of (2), according to the geometric relationships shown in fig. 11 and 12, other aerodynamic parameters of the second target point in the 1 st single-stage axial flow compressor can be calculated, specifically as follows:
Wherein, C 1,m,2 represents the meridian direction component speed of the absolute speed corresponding to the second target point position in the 1 st single-stage axial flow compressor; Representing a relative air flow angle corresponding to a second target point position in the 1 st single-stage axial flow compressor; c 1,2 represents the absolute speed corresponding to the second target point in the 1 st single-stage axial flow compressor; w 1,2 represents the relative speed corresponding to the second target point in the 1 st single-stage axial flow compressor; r r,1-1,2 represents the average diameter ratio of the second target point position in the 1 st single-stage axial flow compressor to the first target point position in the 1 st single-stage axial flow compressor.
For the technical solution shown in fig. 7, in some possible embodiments, based on pneumatic parameters respectively set by the first target point location, the second target point location, and the third target point location in each single-stage axial flow compressor, obtaining densities respectively corresponding to the first target point location, the second target point location, and the third target point location in each single-stage axial flow compressor includes:
Based on the total enthalpy H n,t,1 corresponding to the first target point in the set nth single-stage axial flow compressor, obtaining a static enthalpy value H n,1 corresponding to the first target point in the nth single-stage axial flow compressor according to the formula (13):
（13）
wherein, C n,1 represents the absolute speed corresponding to the first target point in the nth single-stage axial flow compressor;
Based on the static enthalpy value H n,1 and the entropy value s n,1 corresponding to the first target point in the nth single-stage axial flow compressor, obtaining the density corresponding to the first target point in the nth single-stage axial flow compressor according to the formula (14) ：
（14）
Based on isentropic static enthalpy H N,3,is and absolute speed C N,3 corresponding to a third target point in the set Nth single-stage axial flow compressor, isentropic total enthalpy H N,3t,is corresponding to the third target point of the Nth single-stage axial flow compressor is obtained according to formula (15):
（15）
Obtaining an isentropic total enthalpy difference delta H tt,1-N,is corresponding to the N single-stage axial flow compressor according to the difference value between the isentropic total enthalpy H N,3t,is corresponding to the third target point in the N single-stage axial flow compressor and the total enthalpy H 1,t,1 corresponding to the first target point in the 1 st single-stage axial flow compressor;
Based on the isentropic total enthalpy difference delta H tt,1-N,is corresponding to the nth single-stage axial flow compressor and the isentropic total enthalpy difference delta H tt,1-n,is corresponding to the nth single-stage axial flow compressor, calculating according to formula (16) to obtain isentropic total enthalpy H n,3t,is corresponding to a third target point in the nth single-stage axial flow compressor:
（16）
Wherein, Representing a stage load coefficient corresponding to the nth single-stage axial flow compressor; /(I)Representing the stage load coefficient corresponding to the 1 st single-stage axial flow compressor; /(I)Representing a stage load coefficient corresponding to the 2 nd single-stage axial flow compressor; /(I)Representing a stage load coefficient corresponding to the Nth single-stage axial flow compressor;
Based on isentropic total enthalpy H n,3t,is corresponding to a third target point in the nth single-stage axial flow compressor, isentropic static enthalpy H n,3,is corresponding to the third target point in the nth single-stage axial flow compressor is calculated according to formula (17):
（17）
wherein, C n,3 represents the absolute speed corresponding to the third target point in the nth single-stage axial flow compressor;
Based on isentropic static enthalpy H n,3,is corresponding to a third target point in the nth single-stage axial flow compressor and entropy value s n,1 corresponding to the first target point, calculating according to formula (18) to obtain a static pressure value P n,3 corresponding to the third target point in the nth single-stage axial flow compressor:
（18）
based on the static pressure P n,3 and the static enthalpy H n,3 corresponding to the third target point in the nth single-stage axial-flow compressor, calculating according to the formula (19) to obtain the density corresponding to the third target point in the nth single-stage axial-flow compressor ：
（19）
Based on the strength of the stage rotor corresponding to the nth single-stage axial flow compressorAnd calculating according to the formula (20) to obtain isentropic static enthalpy H n,2,is corresponding to a second target point position in the nth single-stage axial flow compressor:
（20）
Based on isentropic static enthalpy H n,2,is corresponding to a second target point position in the nth single-stage axial flow compressor and entropy value s n,1 corresponding to the first target point position, calculating according to formula (21) to obtain a static pressure value P n,2 corresponding to the second target point position in the nth single-stage axial flow compressor:
（21）
Based on the static pressure P n,2 and the static enthalpy H n,2 corresponding to the second target point in the nth single-stage axial-flow compressor, calculating according to the formula (22) to obtain the density corresponding to the second target point in the nth single-stage axial-flow compressor ：
（22）。
It should be noted that, in the embodiment of the present disclosure, the total enthalpy H 1,t,1 corresponding to the first target point in the 1 st single-stage axial flow compressor is calculated according to the state equationAnd besides the calculated total enthalpy H n,t,1 corresponding to the first target point position in the other single-stage axial flow compressors is the total enthalpy corresponding to the third target point position in the adjacent last single-stage axial flow compressor.
In addition, it can be appreciated that the static enthalpy H n,3 corresponding to the third target point in the nth single stage axial flow compressor can be based onCalculating to obtain total enthalpy H n,t,3 corresponding to a third target point position in the nth single-stage axial flow compressor, and further according to/>And (5) calculating to obtain the product.
On the other hand, the static enthalpy H n,2 corresponding to the second target point in the nth single-stage axial-flow compressor can be according toAnd (5) calculating to obtain the product.
In yet another aspect, in embodiments of the present disclosure, the static pressure at the jth target point in the nth single stage axial flow compressor may be based onCalculated, where/>Represents isentropic static enthalpy corresponding to the j-th target point in the nth single-stage axial flow compressor,/>And the entropy value corresponding to the first target point position in the nth single-stage axial flow compressor is represented. In some examples, when according to/>When the static pressure corresponding to the third target point in the N single-stage axial flow compressor is calculated, the total enthalpy/>, corresponding to the third target point in the N single-stage axial flow compressor, is knownUnder the condition of (3), the entropy value s N,1 corresponding to the first target point position in the Nth single-stage axial flow compressor can be obtained through calculation. Based on the above, the entropy value s N,1 corresponding to the first target point in the nth single-stage axial-flow compressor is set to be equal to the entropy value s N-1,3 corresponding to the third target point in the (N-1) -th single-stage axial-flow compressor, and the entropy value s N-1,3 corresponding to the third target point in the (N-1) -th single-stage axial-flow compressor is set to be equal to the entropy value s N-1,1 corresponding to the first target point in the (N-1) -th single-stage axial-flow compressor, so that the total enthalpy/>, corresponding to the third target point in the (N-1) -th single-stage axial-flow compressor, is calculated based on the entropy value s N-1,1 corresponding to the first target point in the (N-1) -th single-stage axial-flow compressorUnder the condition of (1), the static pressure corresponding to the third target point position in the N-1 single-stage axial flow compressor can be calculated, and the static pressure of each target point position in each single-stage axial flow compressor can be obtained through step-by-step repeated calculation. In other examples, it may also be provided that the static pressure at each target point in all single stage axial flow compressors is the same, thus when according to/>When the static pressure at the outlet of the multistage axial flow compressor is calculated, the static pressure of each target point position in each single-stage axial flow compressor can be obtained.
It is understood that the solution of the density corresponding to each target point in each single stage axial flow compressor in embodiments of the present disclosure is dependent on the static pressure and static enthalpy corresponding thereto. Thus, when static pressure and static enthalpy are obtained, the density of the corresponding target point position can be obtained.
For the technical solution shown in fig. 7, in some possible embodiments, determining the geometry of the meridian passage in the multi-stage axial flow compressor based on the flow coefficients, the absolute velocity meridian speeds and the densities respectively corresponding to the first target point, the second target point and the third target point in all the single-stage axial flow compressors includes:
Based on the density and absolute radial velocity of the jth target point in the nth single-stage axial flow compressor, calculating according to formula (23) to obtain an annular area A n,j corresponding to the jth target point in the nth single-stage axial flow compressor:
（23）
Wherein M represents mass flow; representing the density corresponding to the jth target point in the nth single-stage axial flow compressor; c n,m,j represents the meridian direction component speed of the absolute speed corresponding to the j-th target point in the n-th single-stage axial flow compressor;
based on the peripheral speed U n,m,j corresponding to the j-th target point in the set n-th single-stage axial-flow compressor at the uniform diameter position, calculating according to formula (24) to obtain an average radius R n,m,j corresponding to the j-th target point in the n-th single-stage axial-flow compressor:
（24）
Wherein, Indicating the rotation speed; /(I)，/>Representing the circumferential speed corresponding to a first target point position in the nth single-stage axial flow compressor; /(I)Representing the average diameter ratio of a j-th target point position in the nth single-stage axial flow compressor to a first target point position in the 1 st single-stage axial flow compressor;
Based on the annular area A n,j and the average radius R n,m,j corresponding to the jth target point in the nth single-stage axial flow compressor, acquiring the casing radius R n,j,t and the hub radius R n,j,h corresponding to the jth target point in the nth single-stage axial flow compressor according to the formula (25) and the formula (26):
（25）/>
（26）
And determining the geometric shape of a meridian flow passage in the multistage axial flow compressor based on the case radius R n,j,t and the hub radius R n,j,h corresponding to the j-th target point in all the single-stage axial flow compressors.
After the flow coefficient, the radial component speed of the absolute speed and the density corresponding to each target point position in each single-stage axial flow compressor are obtained according to the technical scheme, the hub radius and the casing radius of each target point position in each single-stage axial flow compressor are obtained according to the formulas (23) to (26). And the geometric structure of the meridian flow passage in each single-stage axial flow compressor can be determined based on the hub radius and the casing radius of each target point in each single-stage axial flow compressor and the set axial chord length of the blade row in each single-stage axial flow compressor. As shown in fig. 16, which illustrates radial flow path geometry parameters in a single stage axial flow compressor, chord m represents the blade row axial chord length in each single stage axial flow compressor.
In the implementation process, the rotation speed w and the mass flow rate M are preset.
In some examples, as shown in fig. 17 and 18, the blade row axial chord length is generally determined by the chord length chord and the mounting angle θ, with the specific relationships shown below:
At the chord and the angle of incidence of the blade The geometric shape of the meridian flow passage in each single-stage axial flow compressor can be obtained under the set condition, and the geometric shape of the meridian flow passage in the multi-stage axial flow compressor is further determined.
Based on the same inventive concept as the previous technical solution, referring to fig. 19, there is shown a meridian passage acquiring device 190 of a multistage axial compressor provided in an embodiment of the present disclosure, where the meridian passage acquiring device 190 includes a first determining portion 1901, a first acquiring portion 1902, a second acquiring portion 1903, a third acquiring portion 1904, and a second determining portion 1905; wherein,
The first determination section 1901 is configured to: for each single-stage axial flow compressor of the multi-stage axial flow compressors, determining a first target point location, a second target point location and a third target point location based on the inlet of the rotor blade and the outlet of the stator blade; the first target point is positioned at the inlet of the rotor blade, the second target point is positioned at the outlet of the rotor blade or the inlet of the stator blade, and the third target point is positioned at the outlet of the stator blade;
The first acquisition section 1902 is configured to: based on the flow coefficient corresponding to the inlet of the multistage axial flow compressor and the flow coefficient corresponding to the outlet of the multistage axial flow compressor, acquiring the flow coefficients corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor respectively;
the second acquisition section 1903 is configured to: acquiring meridian component speeds of absolute speeds corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor based on set boundary conditions and pneumatic parameters at an inlet and an outlet in the multi-stage axial flow compressor;
The third acquisition section 1904 is configured to: acquiring densities corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial-flow compressor based on pneumatic parameters respectively set by the first target point position, the second target point position and the third target point position in each single-stage axial-flow compressor;
The second determination section 1905 is configured to: and determining the geometric shape of a meridian flow passage in the multistage axial flow compressor based on the flow coefficients, the absolute speed meridian split speeds and the densities respectively corresponding to the first target point position, the second target point position and the third target point position in all the single-stage axial flow compressors.
It should be noted that, in the radial flow channel obtaining device 190 of the multistage axial flow compressor provided in the foregoing embodiment, when the functions thereof are implemented, only the division of the functional modules is illustrated, and in practical application, the functional modules may be allocated to be implemented by different functional modules, that is, the internal structure of the terminal may be divided into different functional modules, so as to implement all or part of the functions described above. In addition, the meridian flow path acquiring device 190 of the multistage axial flow compressor provided in the above embodiment and the meridian flow path acquiring method embodiment of the multistage axial flow compressor belong to the same concept, and detailed implementation processes thereof are shown in the method embodiment and are not repeated here.
The components in this embodiment may be integrated in one processing unit, or each unit may exist alone physically, or two or more units may be integrated in one unit. The integrated units may be implemented in hardware or in software functional modules.
The above-described integrated units, if implemented in the form of software functional modules, may be stored in a computer-readable storage medium, if not sold or used as separate products, and based on such understanding, the technical solution of the present embodiment may be embodied essentially or partly in the form of a software product, or all or part of the technical solution may be embodied in a storage medium, where the computer software product includes several instructions to cause a computer device (which may be a personal computer, a server, or a network device, etc.) or processor to perform all or part of the steps of the above-described method of the present embodiment. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read Only Memory (ROM), a random access Memory (Random Access Memory, RAM), a magnetic disk, or an optical disk, or other various media capable of storing program codes.
Accordingly, the present embodiment provides a computer storage medium storing a meridian passage acquiring program of a multistage axial flow compressor, which when executed by at least one processor, implements the steps of the meridian passage acquiring method of the multistage axial flow compressor.
According to the above-mentioned meridian passage pick-up device 190 of the multistage axial compressor and the computer storage medium, referring to fig. 20, there is shown a specific hardware structure of a computing device 200 capable of implementing the meridian passage pick-up device 190 of the multistage axial compressor according to an embodiment of the present disclosure, the computing device 200 may be a wireless device, a mobile or cellular phone (including a so-called smart phone), a Personal Digital Assistant (PDA), a video game console (including a video display, a mobile video game device, a mobile video conference unit), a laptop computer, a desktop computer, a television set-top box, a tablet computing device, an electronic book reader, a fixed or mobile media player, or the like. The computing device 200 includes: a communication interface 2001, a memory 2002 and a processor 2003; the various components are coupled together by a bus system 2004. It is appreciated that the bus system 2004 is used to facilitate connected communications between these components. The bus system 2004 includes a power bus, a control bus, and a status signal bus in addition to the data bus. But for clarity of illustration, the various buses are labeled as bus system 2004 in fig. 20. Wherein,
A communication interface 2001, configured to receive and transmit signals during information transmission and reception with other external network elements;
A memory 2002 for storing a computer program capable of running on the processor 2003;
the processor 2003 is configured to execute the steps of the radial flow channel obtaining method of the multistage axial flow compressor according to the following technical solution when executing the computer program.
Optionally, the processor 2003 utilizes various interfaces and lines to connect various portions of the overall computing device, performing various functions of the computing device and processing data by executing or executing instructions, programs, code sets, or instruction sets stored in the memory 2002, and invoking data stored in the memory 2002. Alternatively, the processor 2003 may be implemented in at least one hardware form of digital signal Processing (DIGITAL SIGNAL Processing, DSP), field-Programmable gate array (Field-Programmable GATE ARRAY, FPGA), programmable logic array (Programmable Logic Array, PLA). The processor 2003 may integrate one or a combination of several of a central processing unit (Central Processing Unit, CPU), an image processor (Graphics Processing Unit, GPU), a neural network processor (Neural-network Processing Unit, NPU), and a baseband chip, etc. The CPU mainly processes an operating system, a user interface, an application program and the like; the GPU is used for rendering and drawing the content required to be displayed by the touch display screen; the NPU is used for realizing an artificial intelligence (ARTIFICIAL INTELLIGENCE, AI) function; the baseband chip is used for processing wireless communication. It will be appreciated that the baseband chip may not be integrated into the processor 2003 and may be implemented by a single chip.
Memory 2002 may include random access Memory (Random Access Memory, RAM) or Read-Only Memory (ROM). Optionally, the memory 2002 includes a non-transitory computer readable medium (non-transitory computer-readable storage medium). Memory 2002 may be used to store instructions, programs, code, sets of codes, or instruction sets. The memory 2002 may include a stored program area and a stored data area, wherein the stored program area may store instructions for implementing an operating system, instructions for at least one function (such as a touch function, a sound playing function, an image playing function, etc.), instructions for implementing the above respective method embodiments, etc.; the storage data area may store data created from the use of the computing device, and the like. In addition, those skilled in the art will appreciate that the structure of the computing device shown in the above-described figures is not limiting of the computing device, and that the computing device may include more or fewer components than shown, or may combine certain components, or a different arrangement of components. For example, the computing device further includes a display screen, a camera component, a microphone, a speaker, a radio frequency circuit, an input unit, a sensor (such as an acceleration sensor, an angular velocity sensor, a light sensor, etc.), an audio circuit, a WiFi module, a power supply, a bluetooth module, etc., which are not described herein.
For a software implementation, the techniques described herein may be implemented with modules (e.g., procedures, functions, and so on) that perform the functions described herein. The software codes may be stored in a memory and executed by a processor. The memory may be implemented within the processor or external to the processor. Specifically, the processor 2003 is further configured to execute the steps of the method for obtaining a meridian flow passage of the multistage axial compressor according to the foregoing technical solution when executing the computer program, which will not be described herein.
It should be noted that: the technical schemes described in the embodiments of the present disclosure may be arbitrarily combined without any conflict.
The foregoing is merely specific embodiments of the disclosure, but the protection scope of the disclosure is not limited thereto, and any person skilled in the art can easily think about changes or substitutions within the technical scope of the disclosure, and it is intended to cover the scope of the disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.

Claims (11)

1. The meridian flow passage acquiring method of the multistage axial flow compressor is characterized by comprising the following steps of:
for each single-stage axial flow compressor of the multi-stage axial flow compressors, determining a first target point location, a second target point location and a third target point location based on the inlet of the rotor blade and the outlet of the stator blade; wherein the first target point is located at an inlet of the rotor blade, the second target point is located at an outlet of the rotor blade or an inlet of the stator blade, and the third target point is located at an outlet of the stator blade;
Based on the flow coefficient corresponding to the inlet of the multistage axial flow compressor and the flow coefficient corresponding to the outlet of the multistage axial flow compressor, acquiring the flow coefficients corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor respectively;
Acquiring meridian component speeds of absolute speeds corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor based on set boundary conditions and pneumatic parameters at an inlet and an outlet in the multi-stage axial flow compressor;
acquiring densities corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor based on pneumatic parameters respectively set by the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor;
Determining the geometric shape of a meridian flow passage in the multistage axial flow compressor based on flow coefficients, absolute speed meridian split speeds and densities respectively corresponding to a first target point position, a second target point position and a third target point position in all the single-stage axial flow compressors;
The obtaining the flow coefficients corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor based on the flow coefficients corresponding to the inlet of the multi-stage axial flow compressor and the flow coefficients corresponding to the outlet of the multi-stage axial flow compressor includes:
Calculating according to formula (1) to obtain a flow coefficient corresponding to a first target point position in the nth single-stage axial flow compressor ：
（1）
Wherein k 1 =2n-1, N is 1-N and N is the number of single-stage axial flow compressors contained in the multistage axial flow compressor; x 1=1;x2 = 2n+1; representing flow coefficients corresponding to the inlet of the multistage axial flow compressor; /(I) Representing flow coefficients corresponding to the outlet of the multistage axial flow compressor;
Calculating according to formula (2) to obtain a flow coefficient corresponding to a second target point position in the nth single-stage axial flow compressor ：
（2）
Wherein k 2 =2n;
Calculating according to formula (3) to obtain a flow coefficient corresponding to a third target point position in the nth single-stage axial flow compressor ：
（3）
Where k 3 =2n+1.
2. The method for obtaining a meridian flow path according to claim 1, wherein obtaining meridian component speeds of absolute speeds corresponding to the first, second and third target points in each single-stage axial flow compressor based on the set boundary conditions and aerodynamic parameters at the inlet and the outlet of the multi-stage axial flow compressor includes:
Determining a circumferential speed U 1,1 and an absolute speed C 1,1 corresponding to a first target point position in a1 st single-stage axial flow compressor in the multi-stage axial flow compressor and an absolute speed C N,3 corresponding to a third target point position in an N th single-stage axial flow compressor in the multi-stage axial flow compressor based on set boundary conditions and aerodynamic parameters at an inlet and an outlet in the multi-stage axial flow compressor;
In the nth single stage axial flow compressor:
Determining a meridian component speed of the absolute speed corresponding to the first target point position in the nth single-stage axial flow compressor based on the absolute speed C n,1 corresponding to the first target point position in the nth single-stage axial flow compressor; wherein N is more than or equal to 1 and less than or equal to N, and N represents the number of single-stage axial flow compressors contained in the multistage axial flow compressors;
Determining the meridian component speed of the absolute speed corresponding to the third target point in the nth single-stage axial flow compressor based on the absolute speed C n,3 corresponding to the third target point in the nth single-stage axial flow compressor;
And determining the meridian split speed of the absolute speed corresponding to the second target point position in the nth single-stage axial flow compressor based on the circumferential speed corresponding to the first target point position in the nth single-stage axial flow compressor and the meridian split speed of the absolute speed or based on the circumferential speed corresponding to the first target point position in the nth single-stage axial flow compressor and the meridian split speed of the absolute speed corresponding to the third target point position.
3. The method according to claim 2, wherein determining the circumferential speed U 1,1 and the absolute speed C 1,1 corresponding to the first target point in the 1 st single-stage axial compressor of the multi-stage axial compressors and the absolute speed C N,3 corresponding to the third target point in the nth single-stage axial compressor of the multi-stage axial compressors based on the set boundary conditions and aerodynamic parameters at the inlet and the outlet of the multi-stage axial compressors includes:
Based on the set total enthalpy H 1,t,1 at the inlet of the multistage axial flow compressor and isentropic enthalpy H N,is at the outlet of the multistage axial flow compressor, calculating according to formula (4) to obtain an initial difference value between the isentropic enthalpy H N,is and the total enthalpy H 1,t,1 at the inlet ：
（4）
In the first placeIn the iterative calculation:
stage load coefficient corresponding to 1 st stage axial flow compressor based on setting Stage load coefficients/>, corresponding to the nth single-stage axial flow compressorFirst/>Difference value obtained in iterative calculation/>Calculating according to formula (5) to obtain a peripheral speed U 1,1,i corresponding to a first target point in the 1 st single-stage axial flow compressor:
（5）
Wherein when When said/>Difference value obtained in iterative calculation/>For the initial difference；
Based on the peripheral speed U 1,1,i corresponding to the first target point in the 1 st single-stage axial flow compressor, calculating according to the formula (6) and the formula (7) respectively to obtain an absolute speed C 1,1,i corresponding to the first target point in the 1 st single-stage axial flow compressor and an absolute speed C N,3,i corresponding to the third target point in the nth single-stage axial flow compressor:
（6）
（7）
Wherein, Representing flow coefficients corresponding to the inlet of the multistage axial flow compressor; alpha 1,1 represents an absolute airflow angle corresponding to a first target point in the 1 st single-stage axial flow compressor; /(I)Representing flow coefficients corresponding to the outlet of the multistage axial flow compressor; r r,1-N represents the average diameter ratio between the outlet and the inlet of the multistage axial compressor, andR m,1 represents the average radius at the inlet of the multistage axial compressor; r m,N represents the average radius at the outlet of the multistage axial compressor; alpha N,3 represents an absolute airflow angle corresponding to a third target point in the nth single-stage axial-flow compressor;
Based on the absolute speed C N,3,i corresponding to the third target point in the nth single-stage axial-flow compressor, calculating to obtain the total enthalpy H N,t,3,i at the outlet of the multistage axial-flow compressor according to the following formula (8):
（8）
Wherein, ；/>Representing isentropic efficiency;
According to Calculated as (I) >Difference/>, of total enthalpy H N,t,3,i at the outlet and total enthalpy H 1,t,1 at the inlet of the multistage axial compressor in a secondary iterative calculation；
For the firstDifference/>, between total enthalpy H N,t,3,i at the outlet and total enthalpy H 1,t,1 at the inlet of the multistage axial compressor obtained in a secondary iterative calculationAnd/>Difference/>, between total enthalpy H N,t,3,i-1 at the outlet and total enthalpy H 1,t,1 at the inlet of the multistage axial compressor obtained in a secondary iterative calculationComparing and calculating;
If it is According to/>Calculating to obtain the final peripheral speed U 1,1 corresponding to the first target point in the 1 st single-stage axial-flow compressor, calculating to obtain the absolute speed C 1,1 corresponding to the first target point in the 1 st single-stage axial-flow compressor according to the formula (6), calculating to obtain the absolute speed C N,3 corresponding to the third target point in the N single-stage axial-flow compressor according to the formula (7), and ending the iterative calculation;
If it is Based on/>Execute the/>And (5) carrying out iterative calculation.
4. The method of claim 2, wherein determining the meridian split velocity of the absolute velocity corresponding to the first target point in the nth single-stage axial compressor based on the absolute velocity C n,1 corresponding to the first target point in the nth single-stage axial compressor comprises:
According to the absolute speed C n,1 corresponding to the first target point in the nth single-stage axial flow compressor, the meridian split speed C n,m,1 of the absolute speed corresponding to the first target point in the nth single-stage axial flow compressor is obtained according to the formula (9):
（9）
Wherein, And representing the absolute airflow angle corresponding to the first target point position in the nth single-stage axial-flow compressor.
5. The method of claim 2, wherein determining the meridian split velocity of the absolute velocity corresponding to the third target point in the nth single-stage axial compressor based on the absolute velocity C n,3 corresponding to the third target point in the nth single-stage axial compressor comprises:
According to the absolute speed C n,3 corresponding to the third target point in the nth single-stage axial flow compressor, the meridian split speed C n,m,3 of the absolute speed corresponding to the third target point in the nth single-stage axial flow compressor is obtained according to the formula (10):
（10）
wherein, C n,3 represents the absolute speed corresponding to the third target point in the nth single-stage axial flow compressor; And representing the absolute airflow angle corresponding to the third target point in the nth single-stage axial flow compressor.
6. The method according to claim 2, wherein the determining the meridian split velocity based on the circumferential velocity and the absolute velocity corresponding to the first target point in the nth single-stage axial flow compressor or the meridian split velocity based on the circumferential velocity and the absolute velocity corresponding to the third target point in the nth single-stage axial flow compressor includes:
Based on the circumferential speed U n,1 corresponding to the first target point in the nth single-stage axial flow compressor and the meridian split speed C n,m,1 of the absolute speed, or the circumferential speed U n,1 corresponding to the first target point in the nth single-stage axial flow compressor and the meridian split speed C n,m,3 of the absolute speed corresponding to the third target point, calculating according to formula (11) or formula (12) to obtain the meridian split speed C n,m,2 of the absolute speed corresponding to the second target point in the nth single-stage axial flow compressor:
（11）
（12）
Wherein R r,1-n,2 represents the average diameter ratio of the second target point position in the nth single-stage axial flow compressor to the first target point position in the 1 st single-stage axial flow compressor, and ，k2=2n,x1=1,x2=2n+1；/>Representing a flow coefficient corresponding to a second target point position in the nth single-stage axial flow compressor; /(I)Representing a flow coefficient corresponding to a first target point position in the nth single-stage axial flow compressor; /(I)Representing a flow coefficient corresponding to a third target point position in the nth single-stage axial flow compressor; r r,1-n,3 represents the average diameter ratio of the third target point position in the nth single-stage axial-flow compressor to the first target point position in the 1 st single-stage axial-flow compressor, and，k3=2n+1。
7. The method of claim 1, wherein the obtaining the densities of the first, second, and third target points in each single-stage axial-flow compressor based on the pneumatic parameters respectively set by the first, second, and third target points in each single-stage axial-flow compressor includes:
Based on the total enthalpy H n,t,1 corresponding to the first target point in the set nth single-stage axial flow compressor, obtaining a static enthalpy value H n,1 corresponding to the first target point in the nth single-stage axial flow compressor according to the formula (13):
（13）
Wherein C n,1 represents an absolute speed corresponding to a first target point in the nth single-stage axial flow compressor;
Based on the static enthalpy value H n,1 and the entropy value s n,1 corresponding to the first target point in the nth single-stage axial flow compressor, obtaining the density corresponding to the first target point in the nth single-stage axial flow compressor according to formula (14) ：
（14）
Based on isentropic static enthalpy H N,3,is and absolute speed C N,3 corresponding to a third target point in the set Nth single-stage axial flow compressor, isentropic total enthalpy H N,3t,is corresponding to the third target point of the Nth single-stage axial flow compressor is obtained according to formula (15):
（15）
Obtaining an isentropic total enthalpy difference delta H tt,1-N,is corresponding to the N single-stage axial flow compressor according to a difference value between isentropic total enthalpy H N,3t,is corresponding to a third target point position in the N single-stage axial flow compressor and total enthalpy H 1,t,1 corresponding to a first target point position in the 1 st single-stage axial flow compressor;
based on the isentropic total enthalpy difference Δh tt,1-N,is corresponding to the nth single-stage axial flow compressor and the isentropic total enthalpy difference Δh tt,1-n,is corresponding to the nth single-stage axial flow compressor, calculating according to formula (16) to obtain isentropic total enthalpy H n,3t,is corresponding to a third target point in the nth single-stage axial flow compressor:
（16）
Wherein, Representing a stage load coefficient corresponding to the nth single-stage axial flow compressor; /(I)Representing a stage load coefficient corresponding to the 1 st single-stage axial flow compressor; /(I)Representing the stage load coefficient corresponding to the 2 nd single-stage axial flow compressor; /(I)Representing a stage load coefficient corresponding to the Nth single-stage axial flow compressor;
Based on isentropic total enthalpy H n,3t,is corresponding to a third target point in the nth single-stage axial flow compressor, isentropic static enthalpy H n,3,is corresponding to the third target point in the nth single-stage axial flow compressor is calculated according to formula (17):
（17）
wherein C n,3 represents an absolute speed corresponding to a third target point in the nth single-stage axial flow compressor;
Based on isentropic static enthalpy H n,3,is corresponding to a third target point in the nth single-stage axial flow compressor and entropy value s n,1 corresponding to the first target point, calculating according to formula (18) to obtain static pressure P n,3 corresponding to the third target point in the nth single-stage axial flow compressor:
（18）
based on the static pressure P n,3 and the static enthalpy H n,3 corresponding to the third target point in the nth single-stage axial-flow compressor, calculating according to formula (19) to obtain the density corresponding to the third target point in the nth single-stage axial-flow compressor ：
（19）
Based on the rotor strength corresponding to the nth single-stage axial flow compressorAnd calculating according to the formula (20) to obtain isentropic static enthalpy H n,2,is corresponding to a second target point position in the nth single-stage axial flow compressor:
（20）
Based on isentropic static enthalpy H n,2,is corresponding to a second target point position in the nth single-stage axial flow compressor and entropy value s n,1 corresponding to a first target point position, static pressure P n,2 corresponding to the second target point position in the nth single-stage axial flow compressor is calculated according to formula (21):
（21）
Based on the static pressure P n,2 and the static enthalpy H n,2 corresponding to the second target point in the nth single-stage axial-flow compressor, calculating according to formula (22) to obtain the density corresponding to the second target point in the nth single-stage axial-flow compressor ：
（22）。
8. The method of claim 1, wherein determining the geometry of the meridian passage in the multistage axial compressor based on the flow coefficients, the absolute velocity meridian speeds and the densities respectively corresponding to the first, second and third target points in the multistage axial compressor comprises:
based on the density and absolute radial velocity of the jth target point in the nth single-stage axial flow compressor, calculating according to formula (23) to obtain an annular area A n,j corresponding to the jth target point in the nth single-stage axial flow compressor:
（23）
Wherein M represents mass flow; Representing the density corresponding to the jth target point in the nth single-stage axial flow compressor; c n,m,j represents the meridian direction component speed of the absolute speed corresponding to the j-th target point in the n-th single-stage axial flow compressor;
based on the set circumferential speed U n,m,j corresponding to the j-th target point in the n-th single-stage axial-flow compressor at the uniform diameter position, calculating according to formula (24) to obtain an average radius R n,m,j corresponding to the j-th target point in the n-th single-stage axial-flow compressor:
（24）
Wherein w represents the rotational speed; ，/> Representing the circumferential speed corresponding to a first target point position in the nth single-stage axial flow compressor; /(I) Representing the average diameter ratio of a j-th target point position in the nth single-stage axial flow compressor to a first target point position in the 1 st single-stage axial flow compressor;
Based on an annular area A n,j and an average radius R n,m,j corresponding to a jth target point in the nth single-stage axial flow compressor, acquiring a casing radius R n,j,t and a hub radius R n,j,h corresponding to the jth target point in the nth single-stage axial flow compressor according to a formula (25) and a formula (26):
（25）
（26）
And determining the geometric shape of a meridian flow passage in the multistage axial flow compressors based on the case radius R n,j,t and the hub radius R n,j,h corresponding to the j-th target point in all the single-stage axial flow compressors.
9. A meridian flow passage acquiring device of a multistage axial flow compressor, which is characterized by comprising a first determining part, a first acquiring part, a second acquiring part, a third acquiring part and a second determining part; wherein,
The first determination section is configured to: for each single-stage axial flow compressor of the multi-stage axial flow compressors, determining a first target point location, a second target point location and a third target point location based on the inlet of the rotor blade and the outlet of the stator blade; wherein the first target point is located at an inlet of the rotor blade, the second target point is located at an outlet of the rotor blade or an inlet of the stator blade, and the third target point is located at an outlet of the stator blade;
The first acquisition section is configured to: based on the flow coefficient corresponding to the inlet of the multistage axial flow compressor and the flow coefficient corresponding to the outlet of the multistage axial flow compressor, acquiring the flow coefficients corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor respectively;
The second acquisition section is configured to: acquiring meridian component speeds of absolute speeds corresponding to a first target point position, a second target point position and a third target point position in each single-stage axial flow compressor based on set boundary conditions and pneumatic parameters at an inlet and an outlet in the multi-stage axial flow compressor;
The third acquisition section is configured to: acquiring densities corresponding to the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor based on pneumatic parameters respectively set by the first target point position, the second target point position and the third target point position in each single-stage axial flow compressor;
The second determination section is configured to: determining the geometric shape of a meridian flow passage in the multistage axial flow compressor based on flow coefficients, absolute speed meridian split speeds and densities respectively corresponding to a first target point position, a second target point position and a third target point position in all the single-stage axial flow compressors;
Wherein the first acquisition section is configured to:
Calculating according to formula (1) to obtain a flow coefficient corresponding to a first target point position in the nth single-stage axial flow compressor ：
（1）
Wherein k 1 =2n-1, N is 1-N and N is the number of single-stage axial flow compressors contained in the multistage axial flow compressor; x 1=1;x2 = 2n+1; representing flow coefficients corresponding to the inlet of the multistage axial flow compressor; /(I) Representing flow coefficients corresponding to the outlet of the multistage axial flow compressor;
Calculating according to formula (2) to obtain a flow coefficient corresponding to a second target point position in the nth single-stage axial flow compressor ：
（2）
Wherein k 2 =2n;
Calculating according to formula (3) to obtain a flow coefficient corresponding to a third target point position in the nth single-stage axial flow compressor ：
（3）
Where k 3 =2n+1.
10. A computing device, the computing device comprising: a communication interface, a memory and a processor; the components are coupled together by a bus system; wherein,
The communication interface is used for receiving and transmitting signals in the process of receiving and transmitting information with other external network elements;
The memory is used for storing a computer program capable of running on the processor;
the processor is configured to execute the steps of the radial flow channel acquisition method of the multistage axial flow compressor according to any one of claims 1 to 8 when the computer program is executed.
11. A computer storage medium, characterized in that it stores a meridian passage acquisition program of a multistage axial compressor, which when executed by at least one processor, implements the steps of the meridian passage acquisition method of a multistage axial compressor according to any one of claims 1 to 8.
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