CN117634100A - 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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CN117634100A
CN117634100A CN202410106032.3A CN202410106032A CN117634100A CN 117634100 A CN117634100 A CN 117634100A CN 202410106032 A CN202410106032 A CN 202410106032A CN 117634100 A CN117634100 A CN 117634100A
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target point
axial flow
flow compressor
stage axial
point position
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CN117634100B (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 a 1 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 Representing the radius of the casing corresponding to each single-stage axial-flow compressor, which means that each single-stage axial-flow compressor corresponds toThe vertical distance between the casing molded line and the rotating shaft.R m The average radius corresponding to each single-stage axial flow compressor is indicated to be the vertical distance between the average diameter position corresponding to each single-stage axial flow compressor and the rotating shaft.R h The wheel hub radius corresponding to each single-stage axial flow compressor is indicated, and the vertical distance between the wheel hub molded line corresponding to each single-stage axial flow compressor and the rotating shaft is indicated.
It can be understood that in the structural design of the meridian flow passage, the hub radius corresponding to each single-stage axial flow compressor needs to be obtainedR t Average radiusR m Hub radiusR h . 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 specific implementation, the multistage axial compressor is not designed with equal outer diameters, equal 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, with the 1 st and 2 nd single stage axial flow compressors in fig. 1, for example, three target points in the 1 st single stage axial flow compressor as shown in fig. 8 include the first target point Z located at the inlet of the rotor blade Rot1 1,1 A second target point Z located at the outlet of the rotor blade Rot1 or at the inlet of the stator blade Sta1 1,2 And a third target point Z located at the outlet of stator vane Sta1 1,3 . 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 to say the third target point Z of the 1 st single stage axial compressor at the outlet of the stator vane Sta1 1,3 Is the 2 nd single-stage axial flow pressureFirst target point Z of the aerostat at the inlet of rotor blade Rot2 2,1 In particular, therefore, a second target point Z is provided at the outlet of the rotor blade Rot2 or at the inlet of the stator blade Sta2 in the 2 nd single-stage axial-flow compressor 2,2 And setting a third target point position Z at the outlet of the stator blade Sta2 2,3 And (3) obtaining the product.
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 first flow coefficient NA flow coefficient corresponding to a third target point in the single-stage axial flow compressor, wherein,Nrepresenting the number of single stage axial compressors included in the multistage axial 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 is known for total pressure at the inlet of multistage axial compressorsP 1,t,1 And total temperatureT 1,t,1 I.e. by means of the equation of stateCalculating to obtain total enthalpy at inlet of multistage axial flow compressorH 1,t,1 By means of state equationsCalculating to obtain entropy value of inlet of multistage axial flow compressors 1,1 . It will be appreciated that the total enthalpy at the inlet of a multistage axial compressorH 1,t,1 The total enthalpy corresponding to the first target point position in the 1 st single-stage axial flow compressor and the entropy value at the inlet of the multi-stage axial flow compressor s 1,1 The entropy value corresponding to the first target point position in the 1 st single-stage axial flow compressor.
In some examples, according to the fluid state equationIsentropic enthalpy at the outlet of the multistage axial flow compressor is calculatedH N,is Wherein, the method comprises the steps of, wherein,P N,3 represents the static pressure at the outlet of a multistage axial compressor,/->，/>Representing the total-to-static ratio.
For the firstnFor a single stage axial flow compressor, the velocity triangle for the first target point is shown in fig. 9. As shown in FIG. 9, the firstnThe pneumatic parameters corresponding to the speed triangle of the first target point position in the single-stage axial flow compressor comprise the absolute speed of the first target point positionC n,1 Relative velocity of first target point locationW n,1 Circumferential velocity of first target point locationU n,1 Absolute airflow angle of first target pointα n,1 Relative airflow angle of first target pointβ n,1 Further, based on the correspondence between the velocity triangle of the first target point shown in fig. 9 and the velocity component triangle of the first target point shown in fig. 10, the meridian component velocity of the absolute velocity of the first target point is obtainedC n,m,1 。
For the firstnFor a single stage axial flow compressor, the velocity triangle for the second target point is shown in fig. 11. As shown in FIG. 11, the firstnThe pneumatic parameters corresponding to the speed triangle of the second target point in the single-stage axial flow compressor comprise the absolute speed of the second target point C n,2 Relative velocity of the second target point locationW n,2 Peripheral speed of the second target point locationU n,2 Absolute airflow angle of second target pointα n,2 Further, based on the correspondence between the velocity triangle of the second target point shown in fig. 11 and the velocity component triangle of the second target point shown in fig. 12, the meridian component velocity of the absolute velocity of the second target point is obtainedC n,m,2 。
For the firstnFor a single stage axial flow compressor, the speed triangle for the third target point is shown in fig. 13. As shown in FIG. 13, the firstnThe pneumatic parameters corresponding to the speed triangle of the third target point in the single-stage axial flow compressor comprise the absolute speed of the third target pointC n,3 Peripheral speed of third target point positionU n,3 Absolute airflow angle of third target pointα n,3 Further, based on the correspondence between the velocity triangle of the third target point shown in fig. 13 and the velocity component triangle of the third target point shown in fig. 14, the meridian component velocity of the absolute velocity of the third target point is obtainedC n,m,3 . It will be appreciated that the firstnAerodynamic parameters corresponding to a third target point in a single stage axial flow compressor, e.g. the firstnAbsolute speed of third target point in single stage axial flow compressor C n,3 First, thenPeripheral speed of third target point in single-stage axial-flow compressorU n,3 First of allnAbsolute airflow angle of third target point in single-stage axial-flow compressorα n,3 Is equal to the firstnAerodynamic parameters corresponding to a first target point in +1 single stage axial flow compressors, e.g. thnAbsolute velocity of first target point in +1 single stage axial flow compressorsC n+1,1 First, thenCircumferential velocity of first target point in +1 single stage axial flow compressorsU n+1,1 First of allnAbsolute first target point in +1 single stage axial flow compressorsAngle to the air flowα n+1,1 。
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:
calculated according to formula (1)nFlow coefficient corresponding to first target point position in single-stage axial flow compressor：
（1）
Wherein,k 1 =2n-1，1≤n≤N，Nrepresenting the number of single-stage axial compressors included in the multi-stage axial compressor;x 1 =1；x 2 =2n+1；representing flow coefficients corresponding to inlets of the multistage axial flow compressor; />Representing flow coefficients corresponding to the outlets of the multistage axial flow compressors;
calculated according to formula (2)nFlow coefficient corresponding to second target point position in single-stage axial flow compressor：
（2）
Wherein,k 2 =2n；
calculated according to formula (3)nFlow coefficient corresponding to third target point position in single-stage axial flow compressor：
（3）
Wherein,k 3 =2n+1。
in the implementation process, the flow coefficient corresponding to the inlet of the multistage axial flow compressorAnd the flow coefficient corresponding to the outlet of the multistage axial-flow compressor +. >The 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:
based on the set boundary conditions and aerodynamic parameters at the inlet and outlet of the multistage axial compressor, determining the circumferential speed corresponding to the first target point in the 1 st single-stage axial compressor of the multistage axial compressorU 1,1 And absolute velocityC 1,1 First stage in multistage axial compressorNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3 ；
In the first placenIn a single stage axial flow compressor:
based on the firstnAbsolute velocity corresponding to first target point in single-stage axial flow compressorC n,1 Determine the first nMeridian direction component speed of absolute speed corresponding to first target point in single-stage axial flow compressor; wherein, the content of the active ingredients is less than or equal to 1 percentn≤N，NRepresenting the number of single-stage axial compressors included in the multi-stage axial compressor;
based on the firstnAbsolute speed corresponding to third target point in single-stage axial-flow compressorC n,3 Determine the firstnMeridian direction component speed of absolute speed corresponding to third target point in single-stage axial flow compressor;
based on the firstnThe radial component speed of the circumferential speed and the absolute speed corresponding to the first target point position in the single-stage axial flow compressor or based on the first target point positionnDetermining the radial component speed of the circumferential speed corresponding to the first target point position and the absolute speed corresponding to the third target point position in the single-stage axial flow compressornAnd the radial component speed of the absolute speed corresponding to the second target point position in the single-stage axial flow compressor.
In the embodiment of the disclosure, the circumferential speed corresponding to the first target point position in the 1 st single-stage axial flow compressor is calculated firstU 1,1 And absolute velocityC 1,1 First of allNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3 And obtaining 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 step by step.
For the above embodiments, in some examples, the circumferential speed corresponding to the first target point in the 1 st single stage axial flow compressor of the multi-stage axial flow compressor is determined based on the set boundary conditions and the aerodynamic parameters at the inlet and at the outlet of the multi-stage axial flow compressorU 1,1 And absolute velocityC 1,1 First stage in multistage axial compressorNCorresponding to a third target point in the single-stage axial-flow compressorAbsolute velocity of (2)C N,3 Comprising:
based on the total enthalpy at the inlet of a set multistage axial compressorH 1,t,1 Isentropic enthalpy at the outlet of a multistage axial compressorH N,is Isentropic enthalpy is calculated according to equation (4)H N,is Total enthalpy at the inletH 1,t,1 Is the initial difference of (2)：
（4）
In the first placeIn the iterative calculation:
stage load coefficient corresponding to 1 st stage axial flow compressor based on settingAnd (d)NStage load factor corresponding to single-stage axial flow compressors +.>First->The difference delta obtained in the iterative calculationH tt,1-N,i-1 Calculating according to formula (5) to obtain the circumferential speed corresponding to the first target point position in the 1 st single-stage axial flow compressorU 1,1,i ：
（5）
Wherein whenAt the time->Difference value obtained in iterative calculation>For the initial difference +.>；
Based on the circumferential speed corresponding to the first target point in the 1 st single-stage axial flow compressor U 1,1,i Calculating according to the formula (6) and the formula (7) to obtain the absolute speed corresponding to the first target point position in the 1 st single-stage axial flow compressorC 1,1,i First of allNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3,i ：
（6）
（7）
Wherein,representing flow coefficients corresponding to inlets of the multistage axial flow compressor; />Representing an absolute airflow angle corresponding to a first target point position in the 1 st single-stage axial flow compressor; />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 Representing the average radius at the inlet of the multistage axial compressor;R m,N representing the average radius at the outlet of the multistage axial compressor; />Represent the firstNAbsolute airflow angles corresponding to third target points in the single-stage axial flow compressors;
based on the firstNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3,i The total enthalpy at the outlet of the multistage axial compressor is calculated according to the following formula (8)H N,t,3,i ：
（8）
Wherein,；/>representing isentropic efficiency;
according toCalculated to be at->Total enthalpy at the outlet of a multistage axial compressor in a secondary iterative calculationH N,t,3,i Total enthalpy at the inlet H 1,t,1 Difference of->；
For the firstTotal enthalpy at the outlet of a multistage axial compressor obtained in a secondary iterative calculationH N,t,3,i Total enthalpy at the inletH 1,t,1 Difference of->And->Total enthalpy at the outlet of a multistage axial compressor obtained in a secondary iterative calculationH N,t,3,i-1 Total enthalpy at the inletH 1,t,1 Difference of->Comparing and calculating;
if it isAccording to->Calculating to obtain the circumferential speed corresponding to the first target point position in the final 1 st single-stage axial flow compressorU 1,1 And calculating according to formula (6) to obtain the absolute speed corresponding to the first target point position in the 1 st single-stage axial flow compressorC 1,1 And calculate according to equation (7) to obtain the firstNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3 And the iterative computation is finished;
if it isBased on->Execute->And (5) carrying out iterative calculation.
FIG. 15 shows the acquisition of the circumferential velocity corresponding to the first target point in the 1 st single stage axial flow compressorU 1,1 Absolute velocityC 1,1 And (d)NAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3 The method comprises the following steps:
in step S1501, isentropic enthalpy at the outlet of the multistage axial compressor is obtained according to equation (4)H N,is Total enthalpy at inlet of multistage axial compressor H 1,t,1 Is the initial difference of (2)。
In the first placeIn the iterative calculation:
in step S1502, a circumferential velocity corresponding to a first target point in the 1 st single-stage axial flow compressor is calculated according to equation (5)U 1,1,i 。
In some examples, the 1 st single stage axial flow compressor corresponds to a stage load factorTo the firstNStage load factor corresponding to single-stage axial flow compressors +.>Is preset.
In step S1503, the circumferential velocity corresponding to the first target point in the 1 st single-stage axial flow compressor calculated in step S1502U 1,1,i According to the formula (6) and the formula (7), the absolute speed corresponding to the first target point position in the 1 st single-stage axial flow compressor can be calculatedC 1,1,i First of allNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3,i 。
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 compressor>Absolute air flow angle corresponding to first target point in 1 st single-stage axial flow compressor>First, theNAbsolute airflow angle corresponding to third target point in single-stage axial-flow compressor and average diameter ratio between outlet and inlet of multi-stage axial-flow compressor R r,1-N Are all preset.
In step S1504, the calculated first step is based on step S1503NAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3,i Calculating according to formula (8) to obtain total enthalpy of outlet of multistage axial flow compressorH N,t,3,i 。
In some examples, for isentropic efficiency in equation (8)Is preset.
In step S1505, the total enthalpy of the outlet of the multistage axial compressor calculated based on step S1504H N,t,3,i According toCan be calculated to be at +.>Total enthalpy of outlet of multistage axial compressor in secondary iterative calculationH N,t,3,i Total enthalpy at the inletH 1,t,1 Difference of->。
In step S1506, the calculated first step of step S1505 is performedTotal enthalpy at the outlet of a multistage axial compressor obtained in a secondary iterative calculationH N,t,3,i Total enthalpy at the inletH 1,t,1 Difference of->And->Total enthalpy at the outlet of a multistage axial compressor obtained in a secondary iterative calculationH N,t,3,i-1 Total enthalpy at the inletH 1,t,1 Difference of->A comparison is made. If the comparison result is less than or equal to 0.1, step S1507 is executed to end the iterative computation. On the contrary, based on->Step S1502 is continued to be executed.
It will be appreciated that the total enthalpy at the inlet of the multistage axial compressor is eliminated by iterative calculations in embodiments of the present disclosure H 1,t,1 Isentropic enthalpy at the outlet of a multistage axial compressorH N,is The influence of (2) is such that the total enthalpy at the inlet of the multistage axial compressorH 1,t,1 Isentropic enthalpy at the outlet of a multistage axial compressorH N,is Can be as close as possible to promote the circumferential speed corresponding to the first target point in the 1 st single-stage axial flow compressorU 1,1 And absolute velocityC 1,1 First stage in multistage axial compressorNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3 And the calculation error is reduced.
For the above embodiments, in some examples, based on the firstnAbsolute velocity corresponding to first target point in single-stage axial flow compressorC n,1 Determine the firstnThe meridional component speed of the absolute speed corresponding to the first target point in the single-stage axial flow compressor comprises:
according to the firstnAbsolute velocity corresponding to first target point in single-stage axial flow compressorC n,1 Obtaining the first according to formula (9)nMeridian direction component speed of absolute speed corresponding to first target point position in single-stage axial flow compressorC n,m,1 ：
（9）
Wherein,represent the firstnSingle stage axial flow pressureAbsolute airflow angle corresponding to a first target point in the air machine.
Taking the 1 st single-stage axial flow compressor as an example, when the circumferential speed corresponding to the first target point in the 1 st single-stage axial flow compressor is calculated U 1,1 And absolute velocityC 1,1 When the absolute airflow angle corresponding to the first target point position 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 meridian component speed representing absolute speed corresponding to first target point in 1 st single-stage axial flow compressor;C 1,u,1 a circumferential component speed representing an absolute speed corresponding to a first target point location in the 1 st single-stage axial flow compressor;W 1,1 represents the 1 st sheetThe relative speed corresponding to the first target point position in the stage axial flow compressor;W 1,u,1 a circumferential component speed representing a relative speed corresponding to a first target point location in a 1 st single stage axial flow compressor;W 1,m,1 meridian component speed representing relative speed corresponding to the first target point 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, based on the firstnAbsolute speed corresponding to third target point in single-stage axial-flow compressorC n,3 Determine the firstnThe meridian direction component speed of the absolute speed corresponding to the third target point in the single-stage axial flow compressor comprises the following components:
according to the firstnAbsolute speed corresponding to third target point in single-stage axial-flow compressorC n,3 Obtaining the first according to formula (10)nMeridian direction component speed of absolute speed corresponding to third target point position in single-stage axial flow compressorC n,m,3 ：
（10）
Wherein,C n,3 represent the firstnAbsolute speed corresponding to a third target point in the single-stage axial flow compressor;represent the firstnAbsolute airflow angle corresponding to a third target point in the single-stage axial flow compressor.
It will be appreciated that in computing the firstnMeridian direction component speed of absolute speed corresponding to third target point position in single-stage axial flow compressorC n,m,3 At the time of oneThe following relationship may be set in some examples:C n,3 =C N,3 and. When it is known thatnAbsolute speed corresponding to third target point in single-stage axial-flow compressorC n,3 Absolute air flow angle corresponding to the third target point>In the case of (2), the first can be calculated according to the formula (10) nMeridian direction component speed of absolute speed corresponding to third target point position in single-stage axial flow compressorC n,m,3 . Of course, in the implementation process, the absolute speed corresponding to the third target point in each single-stage axial-flow compressorC n,3 Absolute airflow angle corresponding to third target pointThe setting can be performed according to actual conditions.
Taking the 1 st single-stage axial flow compressor as an example, when settingC 1,3 =C N,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 meridian component speed representing absolute speed corresponding to third target point in 1 st single-stage axial flow compressor;C 1,u,3 representing the third target point position in the 1 st single-stage axial flow compressorCircumferential component speed of absolute velocity of (c).
In the specific implementation process, the firstnAbsolute speed corresponding to third target point in single-stage axial-flow compressorC n,3 Is the firstnAbsolute velocity corresponding to first target point in +1 single stage axial flow compressorsC n+1,1 In the known positionnAbsolute velocity corresponding to first target point in +1 single stage axial flow compressors C n+1,1 When the first step is calculated according to the above formula (9)nRadial component speed of absolute speed corresponding to first target point position in +1 single-stage axial flow compressorsC n+1,m,1 . 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, based on the firstnThe radial component speed of the circumferential speed and the absolute speed corresponding to the first target point position in the single-stage axial flow compressor or based on the first target point positionnDetermining the radial component speed of the circumferential speed corresponding to the first target point position and the absolute speed corresponding to the third target point position in the single-stage axial flow compressornThe meridian direction component speed of the absolute speed corresponding to the second target point position in the single-stage axial flow compressor comprises the following components:
based on the firstnCircumferential velocity corresponding to first target point in single-stage axial flow compressorU n,1 Meridian component velocity of absolute velocityC n,m,1 Or (1)nCircumferential velocity corresponding to first target point in single-stage axial flow compressorU n,1 And the meridian component speed of the absolute speed corresponding to the third target point positionC n,m,3 The first is calculated according to the formula (11) or the formula (12) nMeridian direction component speed of absolute speed corresponding to second target point position in single-stage axial flow compressorC n,m,2 ：
（11）
（12）
Wherein,R r,1-n,2 represent the firstnThe average diameter ratio of the second target point position in the single-stage axial flow compressor to the first target point position in the 1 st single-stage axial flow compressor，k 2 =2n，x 1 =1，x 2 =2n+1；/>Represent the firstnThe flow coefficient corresponding to the second target point position in the single-stage axial flow compressor; />Represent the firstnThe flow coefficient corresponding to a first target point position in the single-stage axial flow compressor; />Represents the firstnA flow coefficient corresponding to a third target point position in the single-stage axial flow compressor;R r,1-n,3 represent the firstnThe average diameter ratio of the third target point position in the single-stage axial flow compressor to the first target point position in the 1 st single-stage axial flow compressor，k 3 =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, the ratio of the average diameter of the outlet to the average diameter of the inlet of the known multistage axial flow compressor R r,1-N Calculated by linear interpolationTo the firstnAverage diameter ratio of first target point position in single-stage axial flow compressor to first target point position in 1 st single-stage axial flow compressorR r,1-n,1 The specific relation is as follows:
。
and, calculate according to the following formulanAverage diameter ratio of second target point position in single-stage axial flow compressor to first target point position in 1 st single-stage axial flow compressorR r,1-n,2 ：
。
And, calculate according to the following formulanAverage diameter ratio of third target point position in single-stage axial-flow compressor to first target point position in 1 st single-stage axial-flow compressorR r,1-n,3 ：
。
In some examples, when the absolute radial component velocity of the absolute velocity corresponding to the second target point in the 1 st single-stage axial compressor is obtained for the 1 st single-stage axial compressorC 1,m,2 Then, the absolute airflow angle corresponding to the second target point position in the 1 st single-stage axial-flow compressor can be obtained according to the following formula：
Wherein,H 1,2 representing 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 position 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, ++ >Represent the firstNTotal enthalpy difference corresponding to the single-stage axial flow compressor and +.>Is 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 meridian component speed representing absolute speed corresponding to second target point in 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 representing the absolute speed corresponding to a second target point position in the 1 st single-stage axial flow compressor;W 1,2 representing the relative speed corresponding to a second target point position in the 1 st single-stage axial flow compressor;R r,1-1,2 and 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 is represented.
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:
Setting-based firstnTotal enthalpy corresponding to a first target point in a single stage axial flow compressorH n,t,1 Obtaining the first according to formula (13)nStatic enthalpy value corresponding to first target point position in single-stage axial flow compressorH n,1 ：
（13）
Wherein,C n,1 represent the firstnAbsolute speed corresponding to a first target point in the single-stage axial flow compressors;
based on the firstnStatic enthalpy value corresponding to first target point position in single-stage axial flow compressorH n,1 Sum entropy values n,1 Obtaining the first according to formula (14)nDensity corresponding to first target point in single-stage axial flow compressor：
（14）
Setting-based firstNIsentropic static enthalpy corresponding to third target point position in single-stage axial flow compressorH N,3,is And absolute velocityC N,3 Obtaining the first according to formula (15)NIsentropic total enthalpy corresponding to third target point position of single-stage axial flow compressorH N,3t,is ：
（15）
According to the firstNIsentropic total enthalpy corresponding to third target point position in single-stage axial flow compressorH N,3t,is Total enthalpy corresponding to a first target point in a 1 st single stage axial flow compressorH 1,t,1 Obtain the difference of (1)NIsentropic total enthalpy difference delta corresponding to single-stage axial flow compressorsH tt,1-N,is ；
Based on the firstNIsentropic total enthalpy difference delta corresponding to single-stage axial flow compressorsH tt,1-N,is And the firstnIsentropic total enthalpy difference delta corresponding to single-stage axial flow compressors H tt,1-n,is Calculated according to formula (16)nIsentropic total enthalpy corresponding to third target point position in single-stage axial flow compressorH n,3t,is ：
（16）
Wherein,represent the firstnThe stage load coefficients corresponding to the single-stage axial flow compressors; />Representing the stage load coefficient corresponding to the 1 st single-stage axial flow compressor; />Representing a stage load coefficient corresponding to the 2 nd single-stage axial flow compressor; />Represent the firstNThe stage load coefficients corresponding to the single-stage axial flow compressors;
based on the firstnIsentropic total enthalpy corresponding to third target point position in single-stage axial flow compressorH n,3t,is Calculated according to formula (17)nIsentropic static enthalpy corresponding to third target point position in single-stage axial flow compressorH n,3,is ：
（17）
Wherein,C n,3 represent the firstnAbsolute speed corresponding to a third target point in the single-stage axial flow compressor;
based on the firstnIsentropic static enthalpy corresponding to third target point position in single-stage axial flow compressorH n,3,is Entropy value corresponding to first target point positions n,1 The first is calculated according to the formula (18)nStatic pressure value corresponding to third target point position in single-stage axial-flow compressorP n,3 ：
（18）
Based on the firstnStatic pressure corresponding to third target point position in single-stage axial-flow compressorP n,3 And static enthalpyH n,3 The first is calculated according to the formula (19) nDensity corresponding to third target point in single-stage axial-flow compressor：
（19）
Based on the firstnStage rotor force corresponding to single-stage axial flow compressorAccording to formula (20) Calculating to obtain the firstnIsentropic static enthalpy corresponding to second target point position in single-stage axial flow compressorH n,2,is ：
（20）
Based on the firstnIsentropic static enthalpy corresponding to second target point position in single-stage axial flow compressorH n,2,is Entropy value corresponding to first target point positions n,1 The first is calculated according to the formula (21)nStatic pressure value corresponding to second target point position in single-stage axial-flow compressorP n,2 ：
（21）
Based on the firstnStatic pressure corresponding to second target point position in single-stage axial-flow compressorP n,2 And static enthalpyH n,2 Calculated according to formula (22)nDensity corresponding to the second target point in single stage axial flow compressor：
（22）。
It should be noted that, in the embodiment of the present disclosure, the total enthalpy corresponding to the first target point in the 1 st single-stage axial flow compressor is dividedH 1,t,1 Is based on the equation of stateBesides calculation, the total enthalpy corresponding to the first target point position in other single-stage axial flow compressorsH n,t,1 The total enthalpy corresponding to a third target point position in the adjacent last single-stage axial flow compressor.
Further, it will be appreciated that the firstnStatic enthalpy corresponding to third target point position in single-stage axial flow compressor H n,3 Can be according toCalculating to obtain the firstnTotal enthalpy corresponding to a third target point in a single stage axial flow compressorH n,t,3 Further according to->And (5) calculating to obtain the product.
On the other hand, the firstnStatic enthalpy corresponding to second target point position in single-stage axial flow compressorH n,2 Can be according toAnd (5) calculating to obtain the product.
In yet another aspect, in an embodiment of the present disclosure, the firstnFirst stage in single stage axial flow compressorjThe static pressure of the target point location can be based onCalculated, wherein->Represent the firstnFirst stage in single stage axial flow compressorjIsentropic static enthalpy corresponding to the target point location, < ->Represent the firstnEntropy value corresponding to first target point in single-stage axial compressor. In some examples, when according +.>Calculating to obtain the firstNWhen the static pressure corresponding to the third target point position in the single-stage axial-flow compressor is knownNTotal enthalpy corresponding to the third target point in the single-stage axial flow compressor>In the case of (2), the first can be calculatedNEntropy value corresponding to first target point position in single-stage axial flow compressors N,1 . Based on this, the first is setNSingle-stage shaftEntropy value corresponding to first target point position in flow compressors N,1 Equal to the firstN-entropy value corresponding to a third target point in 1 single stage axial flow compressor s N-1,3 And (1)N-entropy value corresponding to a third target point in 1 single stage axial flow compressors N-1,3 Equal to the firstN-entropy value corresponding to a first target point in 1 single stage axial flow compressors N-1,1 Thus based on the firstN-entropy value corresponding to a first target point in 1 single stage axial flow compressors N-1,1 And (d)N-1 total enthalpy ++corresponding to the third target point in the single-stage axial compressor>In the case of (1), can be calculated to obtain the firstNAnd (3) calculating the static pressure corresponding to the third target point position in the 1 single-stage axial-flow compressors repeatedly step by step to obtain the static pressure of each target point position in each single-stage axial-flow compressor. In other examples, it is also possible to set the static pressure at each target point in all single-stage axial compressors to be the same, so 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 firstnIn single-stage axial-flow compressorsFirst, thejThe density and absolute velocity meridian velocity corresponding to the target point position are calculated according to the formula (23)nFirst stage in single stage axial flow compressorjAnnular area corresponding to target point positionA n,j ：
（23）
Wherein,Mrepresenting mass flow;represent the firstnFirst stage in single stage axial flow compressorjDensity corresponding to the target point location;C n,m,j represent the firstnFirst stage in single stage axial flow compressorjMeridian component speed of absolute speed corresponding to the target point position;
setting-based firstnFirst stage in single stage axial flow compressorjCircumferential velocity corresponding to the position of the target point at the uniform diameter positionU n,m,j Calculated according to formula (24)nFirst stage in single stage axial flow compressorjAverage radius corresponding to target point positionR n,m,j ：
（24）
Wherein,indicating the rotation speed; />，/>Represents the firstnThe circumferential speed corresponding to a first target point position in the single-stage axial flow compressors; / >Represents the firstnFirst stage in single stage axial flow compressorjTarget point position and the 1 st single-stage axial flow compressorThe average diameter ratio of the first target point position;
based on the firstnFirst stage in single stage axial flow compressorjAnnular area corresponding to target point positionA n,j Average radiusR n,m,j Obtaining the first according to the formulas (25) and (26)nFirst stage in single stage axial flow compressorjCase radius corresponding to target point positionR n,j,t And hub radiusR n,j,h ：
（25）/>
（26）
Based on the first of all single-stage axial compressorsjCase radius corresponding to target point positionR n,j,t And hub radiusR n,j,h The geometry of the meridional flow channels in the multistage axial compressor is determined.
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 shows radial flow geometry parameters in a single stage axial flow compressor, wherein chord m Representing the axial chord length of the blade row in each single stage axial flow compressor.
In the specific implementation, the rotation speedwAnd mass flow rateMIs preset.
In some examples, as shown in fig. 17 and 18, the blade row axial chord length is generally measured by the chord lengthchordAnd (3) mountingCorner angleθThe specific relationship is determined jointly as follows:
at the chord length of the bladechordAnd angle of installationThe 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 to implement artificial intelligence (Artificial Intelligence, AI) functionality; 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.
The Memory 2002 may include a random access Memory (Random Access Memory, RAM) or a 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 (12)

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;
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.
2. The method of claim 1, wherein the obtaining flow coefficients corresponding to the first, second, and third target points 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:
calculated according to formula (1)nFlow coefficient corresponding to first target point position in single-stage axial flow compressor：
（1）
Wherein,k 1 =2n-1，1≤n≤N，Nrepresenting the number of single-stage axial compressors contained in the multistage axial compressor;x 1 =1；x 2 =2n+1；representing flow coefficients corresponding to the inlet of the multistage axial flow compressor; />Representing flow coefficients corresponding to the outlet of the multistage axial flow compressor;
the first step is calculated according to the formula (2)nFlow coefficient corresponding to second target point position in single-stage axial flow compressor ：
（2）
Wherein,k 2 =2n；
the first is calculated according to the formula (3)nFlow coefficient corresponding to third target point position in single-stage axial flow compressor：
（3）
Wherein,k 3 =2n+1。
3. 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:
based on the set boundary conditions and aerodynamic parameters at the inlet and outlet of the multistage axial flow compressor, determining the circumferential speed corresponding to the first target point in the 1 st single-stage axial flow compressor of the multistage axial flow compressorsU 1,1 And absolute velocityC 1,1 A first stage of the multistage axial compressorNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3 ；
In the first placenIn a single stage axial flow compressor:
based on the firstnAbsolute velocity corresponding to first target point in single-stage axial flow compressorC n,1 Determining the firstnMeridian direction component speed of absolute speed corresponding to first target point in single-stage axial flow compressor; wherein, the content of the active ingredients is less than or equal to 1 percent n≤N，NRepresenting the number of single-stage axial compressors contained in the multistage axial compressor;
based on the firstnAbsolute speed corresponding to third target point in single-stage axial-flow compressorC n,3 Determining the firstnMeridian direction component speed of absolute speed corresponding to third target point in single-stage axial flow compressor;
based on the firstnThe radial component speed of the circumferential speed and the absolute speed corresponding to the first target point position in the single-stage axial flow compressor or based on the first target point positionnDetermining the radial component speed of the circumferential speed corresponding to the first target point position and the absolute speed corresponding to the third target point position in the single-stage axial flow compressornSecond order in single stage axial flow compressorMeridian component velocity of absolute velocity corresponding to the standard point position.
4. The method according to claim 3, wherein the circumferential velocity corresponding to the first target point in the 1 st single-stage axial flow compressor in the multistage axial flow compressor is determined based on the set boundary conditions and aerodynamic parameters at the inlet and the outlet of the multistage axial flow compressorU 1,1 And absolute velocityC 1,1 A first stage of the multistage axial compressor NAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3 Comprising:
based on the set total enthalpy at the inlet of the multistage axial compressorH 1,t,1 Isentropic enthalpy at the outlet of the multistage axial compressorH N,is The isentropic enthalpy is calculated according to the formula (4)H N,is Total enthalpy at the inletH 1,t,1 Is the initial difference of (2)：
（4）
In the first placeIn the iterative calculation:
stage load coefficient corresponding to 1 st stage axial flow compressor based on settingTo the firstNStage load factor corresponding to single-stage axial flow compressors +.>First->Difference value obtained in iterative calculation>Calculating according to formula (5) to obtain the circumferential speed corresponding to the first target point position in the 1 st single-stage axial flow compressorU 1,1,i ：
（5）
Wherein whenWhen said->Difference value obtained in iterative calculation>For the initial difference；
Based on the circumferential speed corresponding to the first target point in the 1 st single-stage axial flow compressorU 1,1,i Calculating according to the formula (6) and the formula (7) to obtain the absolute speed corresponding to the first target point position in the 1 st single-stage axial flow compressorC 1,1,i And the firstNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3,i ：
（6）
（7）
Wherein,representing flow coefficients corresponding to the inlet of the multistage axial flow compressor; α 1,1 Representing an absolute airflow angle corresponding to a first target point in the 1 st single-stage axial flow compressor; />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-flow compressor, and，R m,1 representing an average radius at an inlet of the multistage axial compressor;R m,N representing an average radius at an outlet of the multistage axial compressor;α N,3 represents the firstNAbsolute airflow angles corresponding to third target points in the single-stage axial flow compressors;
based on the firstNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3,i Calculating the total enthalpy at the outlet of the multistage axial compressor according to the following formula (8)H N,t,3,i ：
（8）
Wherein,；/>representing isentropic efficiency;
according toCalculated to be at->Total enthalpy at the outlet of the multistage axial compressor in a secondary iterative calculationH N,t,3,i Total enthalpy at the inletH 1,t,1 Difference of->；
For the firstTotal enthalpy at the outlet of the multistage axial compressor obtained in a secondary iterative calculationH N,t,3,i Total enthalpy at the inletH 1,t,1 Difference of->And->Total enthalpy at the outlet of the multistage axial compressor obtained in a secondary iterative calculationH N,t,3,i-1 Total enthalpy at the inlet H 1,t,1 Difference of->Comparing and calculating;
if it isAccording to->Calculating to obtain the final circumferential speed corresponding to the first target point position in the 1 st single-stage axial flow compressorU 1,1 Calculating according to formula (6) to obtain the absolute speed corresponding to the first target point in the 1 st single-stage axial flow compressorC 1,1 And calculating according to formula (7) to obtain the firstNAbsolute speed corresponding to third target point in single-stage axial-flow compressorC N,3 And the iterative calculation ends；
If it isBased on->Execute->And (5) carrying out iterative calculation.
5. The method according to claim 3, wherein the meridian flow path is based on the first aspectnAbsolute velocity corresponding to first target point in single-stage axial flow compressorC n,1 Determining the firstnThe meridional component speed of the absolute speed corresponding to the first target point in the single-stage axial flow compressor comprises:
according to the firstnAbsolute velocity corresponding to first target point in single-stage axial flow compressorC n,1 Obtaining the first step according to formula (9)nMeridian direction component speed of absolute speed corresponding to first target point position in single-stage axial flow compressorC n,m,1 ：
（9）
Wherein,represents the firstnAbsolute airflow angle corresponding to a first target point in the single-stage axial flow compressor.
6. The method according to claim 3, wherein the meridian flow path is based on the first aspectnAbsolute speed corresponding to third target point in single-stage axial-flow compressorC n,3 Determining the firstnAbsolute velocity corresponding to third target point in single-stage axial-flow compressorMeridional component velocity, comprising:
according to the firstnAbsolute speed corresponding to third target point in single-stage axial-flow compressorC n,3 Obtaining the first step according to formula (10)nMeridian direction component speed of absolute speed corresponding to third target point position in single-stage axial flow compressorC n,m,3 ：
（10）
Wherein,C n,3 represent the firstnAbsolute speed corresponding to a third target point in the single-stage axial flow compressor;represents the firstnAbsolute airflow angle corresponding to a third target point in the single-stage axial flow compressor.
7. The method according to claim 3, wherein the meridian flow path is based on the first aspectnThe radial component speed of the circumferential speed and the absolute speed corresponding to the first target point position in the single-stage axial flow compressor or based on the first target point positionnDetermining the radial component speed of the circumferential speed corresponding to the first target point position and the absolute speed corresponding to the third target point position in the single-stage axial flow compressor nThe meridian direction component speed of the absolute speed corresponding to the second target point position in the single-stage axial flow compressor comprises the following components:
based on the firstnCircumferential velocity corresponding to first target point in single-stage axial flow compressorU n,1 Meridian component velocity of absolute velocityC n,m,1 Or the firstnCircumferential velocity corresponding to first target point in single-stage axial flow compressorU n,1 And meridian component speed of absolute speed corresponding to the third target point positionC n,m,3 The first step is calculated according to the formula (11) or the formula (12)nFirst stage in single stage axial flow compressorMeridian direction component speed of absolute speed corresponding to two target pointsC n,m,2 ：
（11）
（12）
Wherein,R r,1-n,2 represents the firstnThe average diameter ratio of the second target point position in the single-stage axial flow compressor to the first target point position in the 1 st single-stage axial flow compressor，k 2 =2n，x 1 =1，x 2 =2n+1；/>Represents the firstnThe flow coefficient corresponding to the second target point position in the single-stage axial flow compressor; />Represents the firstnThe flow coefficient corresponding to a first target point position in the single-stage axial flow compressor; />Represents the firstnA flow coefficient corresponding to a third target point position in the single-stage axial flow compressor;R r,1-n,3 represents the firstnThe average diameter ratio of the third target point position in the single-stage axial flow compressor to the first target point position in the 1 st single-stage axial flow compressor ，k 3 =2n+1。
8. 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:
setting-based firstnTotal enthalpy corresponding to a first target point in a single stage axial flow compressorH n,t,1 The first is obtained according to formula (13)nStatic enthalpy value corresponding to first target point position in single-stage axial flow compressorH n,1 ：
（13）
Wherein,C n,1 represents the firstnAbsolute speed corresponding to a first target point in the single-stage axial flow compressors;
based on the firstnStatic enthalpy value corresponding to first target point position in single-stage axial flow compressorH n,1 Sum entropy values n,1 Obtaining the first according to formula (14)nDensity corresponding to first target point in single-stage axial flow compressor：
（14）
Setting-based firstNIsentropic static enthalpy corresponding to third target point position in single-stage axial flow compressorH N,3,is And absolute velocityC N,3 Obtaining the first according to formula (15)NIsentropic total enthalpy corresponding to third target point position of single-stage axial flow compressor H N,3t,is ：
（15）
According to the firstNIsentropic total enthalpy corresponding to third target point position in single-stage axial flow compressorH N,3t,is Total enthalpy corresponding to a first target point in a 1 st single stage axial flow compressorH 1,t,1 Obtain the difference of said firstNIsentropic total enthalpy difference delta corresponding to single-stage axial flow compressorsH tt,1-N,is ；
Based on the firstNIsentropic total enthalpy difference delta corresponding to single-stage axial flow compressorsH tt,1-N,is And the first is connected withnIsentropic total enthalpy difference delta corresponding to single-stage axial flow compressorsH tt,1-n,is The first is calculated according to the formula (16)nIsentropic total enthalpy corresponding to third target point position in single-stage axial flow compressorH n,3t,is ：
（16）
Wherein,represents the firstnThe stage load coefficients corresponding to the single-stage axial flow compressors; />Representing a stage load coefficient corresponding to the 1 st single-stage axial flow compressor; />Representing the stage load coefficient corresponding to the 2 nd single-stage axial flow compressor; />Represents the firstNThe stage load coefficients corresponding to the single-stage axial flow compressors;
based on the firstnIsentropic total enthalpy corresponding to third target point position in single-stage axial flow compressorH n,3t,is The first step is calculated according to the formula (17)nIsentropic static enthalpy corresponding to third target point position in single-stage axial flow compressorH n,3,is ：
（17）
Wherein,C n,3 represents the firstnAbsolute speed corresponding to a third target point in the single-stage axial flow compressor;
Based on the firstnIsentropic static enthalpy corresponding to third target point position in single-stage axial flow compressorH n,3,is Entropy value corresponding to first target point positions n,1 The first step is calculated according to the formula (18)nStatic pressure corresponding to third target point position in single-stage axial-flow compressorP n,3 ：
（18）
Based on the firstnStatic pressure corresponding to third target point position in single-stage axial-flow compressorP n,3 And static enthalpyH n,3 The first step is calculated according to the formula (19)nDensity corresponding to third target point in single-stage axial-flow compressor：
（19）
Based on the firstnRotor strength corresponding to single-stage axial flow compressorThe first step is calculated according to the formula (20)nIsentropic static enthalpy corresponding to second target point position in single-stage axial flow compressorH n,2,is ：
（20）
Based on the firstnIsentropic static enthalpy corresponding to second target point position in single-stage axial flow compressorH n,2,is Entropy value corresponding to first target point positions n,1 The first step is calculated according to the formula (21)nStatic pressure corresponding to second target point position in single-stage axial-flow compressorP n,2 ：
（21）
Based on the firstnStatic pressure corresponding to second target point position in single-stage axial-flow compressorP n,2 And static enthalpyH n,2 The first is calculated according to the formula (22)nDensity corresponding to the second target point in single stage axial flow compressor ：
（22）。
9. 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 firstnFirst stage in single stage axial flow compressorjThe density and absolute velocity meridian velocity corresponding to the target point position are calculated according to the formula (23) to obtain the firstnFirst stage in single stage axial flow compressorjAnnular area corresponding to target point positionA n,j ：
（23）
Wherein,Mrepresenting mass flow;represents the firstnFirst stage in single stage axial flow compressorjDensity corresponding to the target point location;C n,m,j represents the firstnFirst stage in single stage axial flow compressorjMeridian component speed of absolute speed corresponding to the target point position;
setting-based said firstnFirst stage in single stage axial flow compressorjCircumferential velocity corresponding to the position of the target point at the uniform diameter positionU n,m,j The first step is calculated according to the formula (24)nFirst stage in single stage axial flow compressorjAverage radius corresponding to target point positionR n,m,j ：
（24）
Wherein, wIndicating the rotation speed;，/>represents the firstnThe circumferential speed corresponding to a first target point position in the single-stage axial flow compressors; />Represents the firstnFirst stage in single stage axial flow compressorjThe average diameter ratio of the target point position to the first target point position in the 1 st single-stage axial flow compressor;
based on the firstnFirst stage in single stage axial flow compressorjAnnular area corresponding to target point positionA n,j Average radiusR n,m,j According to the formula (25) and the formula26 Acquiring the firstnFirst stage in single stage axial flow compressorjCase radius corresponding to target point positionR n,j,t And hub radiusR n,j,h ：
（25）
（26）
Based on the first of the all single-stage axial flow compressorsjCase radius corresponding to target point positionR n,j,t And hub radiusR n,j,h The geometry of the meridional flow channels in the multistage axial compressor is determined.
10. 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: 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.
11. 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 9 when the computer program is executed.
12. 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 9.
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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190093554A1 (en) * 2016-03-14 2019-03-28 Mitsubishi Heavy Industries ,Ltd. Multistage axial compressor and gas turbine
CN112594064A (en) * 2020-11-25 2021-04-02 北京航空航天大学 S2 flow field diagnosis method based on interstage measurement parameters of axial flow compressor
CN112685968A (en) * 2020-12-22 2021-04-20 中国船舶重工集团公司第七0三研究所 Axial flow compressor pneumatic design method based on space load customization thought
CN112943668A (en) * 2021-02-24 2021-06-11 南京航空航天大学 Dynamic stall process prediction method for aviation axial flow compressor under complex intake distortion
CN113309729A (en) * 2021-07-29 2021-08-27 中国航发上海商用航空发动机制造有限责任公司 Multistage axial flow compressor test monitoring method and device

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190093554A1 (en) * 2016-03-14 2019-03-28 Mitsubishi Heavy Industries ,Ltd. Multistage axial compressor and gas turbine
CN112594064A (en) * 2020-11-25 2021-04-02 北京航空航天大学 S2 flow field diagnosis method based on interstage measurement parameters of axial flow compressor
CN112685968A (en) * 2020-12-22 2021-04-20 中国船舶重工集团公司第七0三研究所 Axial flow compressor pneumatic design method based on space load customization thought
CN112943668A (en) * 2021-02-24 2021-06-11 南京航空航天大学 Dynamic stall process prediction method for aviation axial flow compressor under complex intake distortion
CN113309729A (en) * 2021-07-29 2021-08-27 中国航发上海商用航空发动机制造有限责任公司 Multistage axial flow compressor test monitoring method and device

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
C. SHANGCHEN: "Modeling_and_simulation_of_compressor_servo_system", 《CSAA/IET INTERNATIONAL CONFERENCE ON AIRCRAFT UTILITY SYSTEMS (AUS 2020)》, 22 September 2021 (2021-09-22) *
闫转运;成金鑫;陈江;: "多级轴流压气机通流造型一体化设计研究", 工程热物理学报, no. 06, 15 June 2016 (2016-06-15) *
韩万龙: "低速引射式风力涡轮气动设计及优化", 《中国博士学位论文全文数据库》, 15 February 2017 (2017-02-15) *
黄松: "压气机叶片几何气动性能优化设计方法综述", 《推进技术》, 16 June 2023 (2023-06-16) *

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