CN117195593B - Method, device, equipment and medium for acquiring gas flow parameters of blade - Google Patents
Method, device, equipment and medium for acquiring gas flow parameters of blade Download PDFInfo
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Abstract
The embodiment of the disclosure discloses a method, a device, equipment and a medium for acquiring gas flow parameters of a blade; the acquisition method comprises the following steps: determining a first target point position, a second target point position and a third target point position based on an inlet of the rotor blade at a one-dimensional uniform diameter and an outlet of the stator blade at the one-dimensional uniform diameter; determining a speed triangle of the first target point location and a speed triangle of the second target point location based on a set boundary condition and a first gas flow parameter of the first target point location; and determining the speed triangle of the third target point based on the speed triangle of the first target point and the speed triangle of the second target point.
Description
Technical Field
The embodiment of the disclosure relates to the technical field of gas flow design of axial flow compressors, in particular to a method, a device, equipment and a medium for acquiring gas flow parameters of blades.
Background
The 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. However, the development and marketing of new products of the axial compressor are severely restricted by the current situations of long period and high development cost of the structural design of the axial compressor.
The structural design of the axial flow compressor mainly comprises a one-dimensional uniform diameter design, an S2 flow surface through flow design, an S1 flow surface blade profile design, a three-dimensional blade modeling design, computational fluid dynamics (Computational Fluid Dynamics, CFD) computational verification and the like. Wherein, the one-dimensional average diameter refers to an average central line of a casing molded line and a hub line in the axial flow compressor. The one-dimensional uniform diameter design is an early stage of structural design of the axial flow compressor. The one-dimensional uniform diameter design comprises the steps of obtaining inlet gas flow parameters and outlet gas flow parameters of blades in each stage of the axial flow compressor at one-dimensional uniform diameter positions, and constructing geometric blade shapes at the one-dimensional uniform diameter positions through the obtained inlet gas flow parameters and outlet gas flow parameters.
However, in the one-dimensional uniform diameter design, if the inlet gas flow parameter and the outlet gas flow parameter of the blade at the one-dimensional uniform diameter position are unreasonably designed, the difficulty of optimizing the performance of the axial flow compressor through subsequent other design links is increased, the design iteration times of the axial flow compressor are increased, and the design period of the axial flow compressor is prolonged.
Disclosure of Invention
In view of this, embodiments of the present disclosure desire to provide a method, apparatus, device, and medium for acquiring a gas flow parameter of a blade; the gas flow parameters of the inlet and the outlet of the blades in each stage of the axial flow compressor at the one-dimensional uniform diameter position can be accurately obtained, the design precision of the axial flow compressor is improved, and the design period is shortened.
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 acquiring a gas flow parameter of a blade, the method including:
determining a first target point position, a second target point position and a third target point position based on an inlet of the rotor blade at a one-dimensional uniform diameter and an outlet of the stator blade at the one-dimensional uniform diameter; the first target point is positioned at an inlet of the rotor blade at a one-dimensional uniform diameter, the second target point is positioned at an outlet of the stator blade at the one-dimensional uniform diameter, and the third target point is positioned at an outlet of the rotor blade at the one-dimensional uniform diameter or an inlet of the stator blade at the one-dimensional uniform diameter;
determining a speed triangle of the first target point location and a speed triangle of the second target point location based on a set boundary condition and a first gas flow parameter of the first target point location;
determining a speed triangle of the third target point based on the speed triangle of the first target point and the speed triangle of the second target point; the speed triangle of the first target point position, the speed triangle of the second target point position and the speed triangle of the third target point position are used for representing gas flow parameters when the geometric modeling of the rotor blade and the stator blade is designed.
In a second aspect, embodiments of the present disclosure provide an acquisition device for a gas flow parameter of a blade, the acquisition device comprising: a first determination unit, a second determination unit, and a third determination unit; wherein,
the first determination section is configured to: determining a first target point position, a second target point position and a third target point position based on an inlet of the rotor blade at a one-dimensional uniform diameter and an outlet of the stator blade at the one-dimensional uniform diameter; the first target point is positioned at an inlet of the rotor blade at a one-dimensional uniform diameter, the second target point is positioned at an outlet of the stator blade at the one-dimensional uniform diameter, and the third target point is positioned at an outlet of the rotor blade at the one-dimensional uniform diameter or an inlet of the stator blade at the one-dimensional uniform diameter;
the second determination section is configured to: determining a speed triangle of the first target point location and a speed triangle of the second target point location based on a set boundary condition and a first gas flow parameter of the first target point location;
the third determination section is configured to: determining a speed triangle of the third target point based on the speed triangle of the first target point and the speed triangle of the second target point; the speed triangle of the first target point position, the speed triangle of the second target point position and the speed triangle of the third target point position are used for representing gas flow parameters when the geometric modeling of the rotor blade and the stator blade is designed.
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 method for acquiring the gas flow parameters of the blade according to the first aspect when the computer program is run.
In a fourth aspect, embodiments of the present disclosure provide a computer storage medium storing a program for acquiring a gas flow parameter of a blade, where the program for acquiring a gas flow parameter of a blade implements the steps of the method for acquiring a gas flow parameter of a blade according to the first aspect when executed by at least one processor.
The embodiment of the disclosure provides a method, a device, equipment and a medium for acquiring gas flow parameters of a blade; based on an inlet of the rotor blade at one-dimensional uniform diameter and an outlet of the stator blade at one-dimensional uniform diameter, a first target point position of the inlet of the rotor blade at one-dimensional uniform diameter, a second target point position of the outlet of the stator blade at one-dimensional uniform diameter and a third target point position of the outlet of the rotor blade at one-dimensional uniform diameter or the inlet of the stator blade at one-dimensional uniform diameter are determined. And determining a speed triangle of the first target point and a speed triangle of the second target point based on the set boundary condition and the first gas flow parameter of the first target point, and further determining to obtain the speed triangle of the third target point. The speed triangle of the first target point, the speed triangle of the second target point and the speed triangle of the third target point can be used for representing gas flow parameters when designing geometric modeling of the rotor blade and the stator blade. Through the technical scheme provided by the embodiment of the disclosure, the gas flow parameters of the inlet and the outlet of the rotor blade and the stator blade at the one-dimensional uniform diameter position can be accurately obtained, the design precision of the geometric modeling of the rotor blade and the stator blade is improved, and the design period of the axial flow compressor is shortened.
Drawings
Fig. 1 is a meridional view of a 2-stage axial compressor provided by an embodiment of the present disclosure.
Fig. 2 is a meridian view of an equal diameter axial compressor provided by an embodiment of the present disclosure.
Fig. 3 is a flowchart of a method for obtaining a gas flow parameter of a blade according to an embodiment of the disclosure.
FIG. 4 is a schematic illustration of the locations of the inlet and outlet of the rotor blade and stator blade at one-dimensional mean diameter positions provided by embodiments of the present disclosure.
Fig. 5 is a schematic diagram of a velocity triangle of a first target point according to an embodiment of the disclosure.
Fig. 6 is a schematic diagram of a velocity triangle of a second target point provided in an embodiment of the present disclosure.
Fig. 7 is a schematic diagram of a speed triangle of a third target point according to an embodiment of the disclosure.
Fig. 8 is a flowchart of an iterative calculation method for circumferential velocity of a first target point according to an embodiment of the present disclosure.
Fig. 9 is a schematic diagram of a velocity component 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 second target point provided in an embodiment of the present disclosure.
Fig. 11 is a schematic diagram of a velocity component triangle of a third target point provided in an embodiment of the present disclosure.
Fig. 12 is a schematic diagram of an apparatus for acquiring gas flow parameters of a blade according to an embodiment of the disclosure.
Fig. 13 is a schematic structural diagram of a computing device according to an embodiment of the 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.
Before describing the embodiments of the present disclosure in detail, it should be noted that the axial flow compressor shown in fig. 1 is taken as an example to describe the technical solution provided by the embodiments of the present disclosure, but the technical solution in the embodiments of the present disclosure is not limited to the axial flow compressor.
Each stage of the axial compressor includes a row of rotor blades and a row of stator blades. The rotor blades and stator blades described above may also be collectively referred to as blades. The principle of compressing gas in an axial flow compressor is that the rotor blades apply work to the gas to improve the pressure energy and kinetic energy of the gas, and then the kinetic energy of the gas is converted into static pressure energy through the diffusion action of the stator blades. Referring to fig. 1, a meridional view of a 2-stage axial compressor is illustratively provided. Wherein, the solid line G in fig. 1 represents a casing type line. The solid line H represents the hub line. The area between the casing and hub lines described above is a meridional view of the blade. The broken line D represents the average center line of the case line and the hub line. In some examples, the average centerline (dashed line D in fig. 1) of the casing and hub lines described above is also referred to as the "one-dimensional average diameter" of the axial compressor. The geometric shape of the rotor blade at the one-dimensional mean diameter position characterizes the average shape of the rotor blade's profile, and the geometric shape of the stator blade at the one-dimensional mean diameter position characterizes the average shape of the stator blade's profile. The geometric shape of the rotor and stator blades is typically constructed by calculating the gas flow parameters of the inlet and outlet of the rotor and stator blades at one-dimensional mean diameter positions. The dash-dot line Rs in fig. 1 indicates the rotation axis of the axial compressor.
As can be seen from the figure 1 of the drawings,in the stage I of the axial compressor, 1 rotor blade Rot1 and 1 stator blade Sta1 are included, and in the stage ii, 1 rotor blade Rot2 and 1 stator blade Sta2 are included. Wherein, as shown in figure 1,R 1 the average radius of the inlet of the rotor blade in each stage is expressed as the vertical distance between the inlet of the rotor blade at the one-dimensional mean diameter position and the rotation axis.R 2 The average radius of the outlets of the rotor blades in each stage is expressed, referring to the vertical distance between the outlets of the rotor blades at the one-dimensional average diameter position and the rotation axis.R 3 The average radius of the inlet of the stator blade in each stage is expressed as the vertical distance between the inlet of the stator blade at the one-dimensional average diameter position and the rotating shaft.R 4 The average radius of the outlet of the stator blade in each stage is expressed as the vertical distance between the outlet of the stator blade at the one-dimensional average diameter position and the rotating shaft.
In one-dimensional balance design of an axial compressor, to obtain inlet gas flow parameters and outlet gas flow parameters of rotor blades and stator blades in each stage of the axial compressor at one-dimensional balance positions, it is generally necessary to solve inlet speed triangles and outlet speed triangles of the rotor blades and stator blades in each stage at one-dimensional balance positions to obtain the inlet gas flow parameters and the outlet gas flow parameters of the rotor blades and stator blades in each stage at one-dimensional balance positions according to a functional relationship in the inlet speed triangles and the outlet speed triangles. Specifically, the inlet speed triangle refers to a vector triangle formed by an inlet absolute speed vector, an inlet relative speed vector and an inlet peripheral speed vector, and the outlet speed triangle refers to a vector triangle formed by an outlet absolute speed vector, an outlet relative speed vector and an outlet peripheral speed vector.
However, in the related art, the calculation of the inlet speed triangle and the outlet speed triangle of the rotor blade and the stator blade at the one-dimensional average diameter position in each stage is solved based on the specific case that the axial flow compressor is of the equal average diameter. Referring to fig. 2, a meridional view of an equal diameter axial compressor is shown. As can be seen from fig. 2, etcThe axial flow compressor with uniform diameter is mainly characterized in thatR 1 =R 2 =R 3 =R 4 . In this way, an axial compressor with equal diameter can be obtainedU 1 =U 2 =U 3 Wherein, the method comprises the steps of, wherein,U 1 representing the circumferential velocity of the inlet of the rotor blade at a one-dimensional mean diameter position,U 2 representing the circumferential velocity of the outlet of the stator blade at a one-dimensional mean diameter position,U 3 representing the circumferential velocity of the outlet of the rotor blade at a one-dimensional mean diameter position. However, the actual axial compressor is not provided with equal diameters, as in the axial compressor shown in fig. 1R 1 ≠R 2 ≠R 3 ≠R 4 That is, the circumferential speeds of the inlets and the outlets corresponding to the rotor blades and the stator blades of each stage in the axial flow compressor shown in FIG. 1 are not equalU 1 ≠U 2 ≠U 3 . Therefore, when the inlet speed triangle and the outlet speed triangle corresponding to the rotor blade and the stator blade are calculated, as the inlet peripheral speed and the outlet peripheral speed corresponding to the rotor blade and the stator blade are equal, the accuracy of the calculated inlet speed triangle and outlet speed triangle corresponding to the rotor blade and the stator blade is reduced, the rationality of the inlet gas flow parameter and the outlet gas flow parameter of the rotor blade and the stator blade at the one-dimensional uniform diameter position is affected, and the design accuracy of the axial flow compressor is reduced.
Based on the above description, it is desirable for the embodiments of the present disclosure to provide a technical solution capable of accurately obtaining the inlet gas flow parameter and the outlet gas flow parameter of the rotor blade and the stator blade in each stage of the axial flow compressor at the one-dimensional uniform diameter position, where the technical solution provided by the embodiments of the present disclosure can be applied to the non-uniform diameter axial flow compressor shown in fig. 1.
Referring to fig. 3, a method for obtaining a gas flow parameter of a blade according to an embodiment of the present disclosure is shown, and the design method specifically includes the following steps.
In step S301, a first target point location, a second target point location, and a third target point location are determined based on an inlet of the rotor blade at the one-dimensional average diameter and an outlet of the stator blade at the one-dimensional average diameter; wherein the first target point is located at an inlet of the rotor blade at a one-dimensional average diameter, the second target point is located at an outlet of the stator blade at a one-dimensional average diameter, and the third target point is located at an outlet of the rotor blade at a one-dimensional average diameter or an inlet of the stator blade at a one-dimensional average diameter.
In order to clearly show the positional relationship of the first target point, the second target point, and the third target point set in the embodiment of the present disclosure, the rotor blade Rot1 and the stator blade Sta1 in the stage i in fig. 1 are subjected to, for example, ring cutting along one-dimensional average diameter to obtain a schematic positional diagram of the inlet and outlet of the rotor blade Rot1 and the stator blade Sta1 at the one-dimensional average diameter position, as shown in fig. 4. Three target points set by embodiments of the present disclosure are shown in fig. 4. The three target points include a first target point Z1 located at an inlet of the rotor blade at a one-dimensional mean diameter position, a second target point Z2 located at an outlet of the stator blade at a one-dimensional mean diameter position, and a third target point Z3 located at an outlet of the rotor blade at a one-dimensional mean diameter position or an inlet of the stator blade at a one-dimensional mean diameter position.
The rotor blade Rot1 and stator blade Sta1 shown in fig. 4 are only for explaining the positional relationship of the first target point Z1, the second target point Z2, and the third target point Z3. In the specific implementation, the geometric shapes of the rotor blade Rot1 and the stator blade Sta1 are not yet determined. That is, in the implementation, the first target point location Z1 can be determined only by the inlet position of the rotor blade at the one-dimensional average diameter, the second target point location Z2 is determined by the outlet position of the stator blade at the one-dimensional average diameter, but the position of the third target point location Z3 is not determined.
In step S302, a velocity triangle of the first target point and a velocity triangle of the second target point are determined based on the set boundary condition and the first gas flow parameter of the first target point.
The boundary conditions described above are state equations. 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. Total pressure at the first target point as knownP t1 And total temperatureT t1 I.e. by means of the equation of stateCalculating to obtain the total enthalpy of the first target point position H t1 By means of the state equation->Calculating to obtain entropy of the first target point position>。
In some examples, according to the fluid state equationIsentropic enthalpy of the second target point position is calculatedH is2, Wherein, the method comprises the steps of, wherein,P 2 static pressure representing the second target point, +.>，pr ts Representing the total-to-static ratio.
The velocity triangle of the first target point is shown in fig. 5. As can be seen from FIG. 5, when the absolute velocity of, for example, the first target point is obtainedC 1 Relative velocity of first target point locationW 1 Circumferential velocity of first target point locationU 1 Absolute airflow angle of first target pointRelative air flow angle of the first target point position +.>The time can be determinedA speed triangle of the first target point location.
In some examples, to determine the velocity triangle of the first target point, the first gas flow parameter includes an absolute gas flow angle of the first target pointFlow coefficient of the first target point location +.>Stage load factor->。
The velocity triangle of the second target point is shown in fig. 6. As can be seen from FIG. 6, when the absolute velocity of, for example, the second target point is obtainedC 2 Relative velocity of the second target point locationW 2 Peripheral speed of the second target point locationU 2 Absolute airflow angle of second target point Then the speed triangle of the second target point location can be determined.
In some examples, to determine the velocity triangle of the second target point, the second gas flow parameter includes an absolute gas flow angle of the second target pointFlow coefficient of the second target point location +.>Average diameter ratio of second target point positionR r,1-2 And->。
In step S303, a speed triangle of the third target point is determined based on the speed triangle of the first target point and the speed triangle of the second target point; the speed triangle of the first target point, the speed triangle of the second target point and the speed triangle of the third target point are used for representing gas flow parameters when the geometric modeling of the rotor blade and the stator blade is designed.
The speed triangle of the third target point is shown in fig. 7. As can be seen from FIG. 7, when the absolute velocity of, for example, the third target point is obtainedC 3 Relative speed of the third target pointW 3 Peripheral speed of third target point positionU 3 Absolute airflow angle of third target pointAnd the relative air flow angle of the third target point position +.>The speed triangle of the third target point can be determined.
In the embodiment of the disclosure, when the speed triangle of the first target point, the speed triangle of the second target point and the speed triangle of the third target point are determined, in other words, the inlet speed triangle of the rotor blade at the one-dimensional uniform diameter position, the outlet speed triangle of the stator blade at the one-dimensional uniform diameter position and the outlet speed triangle gas flow parameters of the rotor blade at the one-dimensional uniform diameter position are obtained, so that the gas flow parameters, such as the gas flow angle and the speed, of the inlet and the outlet of the rotor blade and the stator blade at the one-dimensional uniform diameter position can be obtained, and further, the geometric blade shape of the rotor blade and the stator blade can be determined.
In a specific implementation, the solution for acquiring the gas flow parameters of the blade provided by the embodiments of the present disclosure can be executed by a computing device. In some examples, the computing device may be at least one of a smart phone, a smart watch, a desktop computer, a laptop computer, a virtual reality terminal, an augmented reality terminal, a wireless terminal, and a laptop portable computer. The computing device has communication capabilities and may access a wired network or a wireless network. The computing device may refer broadly to one of a plurality of terminals, and those skilled in the art will recognize that the number of terminals may be greater or lesser. It will be appreciated that the computing device bears the computing and processing effort in embodiments of the present disclosure, which are not limited in this regard.
For the solution shown in fig. 3, a first target point location of the inlet of the rotor blade at one-dimensional average diameter and a second target point location of the outlet of the stator blade at one-dimensional average diameter and a third target point location of the outlet of the rotor blade at one-dimensional average diameter or the inlet of the stator blade at one-dimensional average diameter are determined based on the inlet of the rotor blade at one-dimensional average diameter and the outlet of the stator blade at one-dimensional average diameter. And determining a speed triangle of the first target point and a speed triangle of the second target point based on the set boundary condition and the first gas flow parameter of the first target point, and further determining to obtain a speed triangle of the third target point. The speed triangle of the first target point, the speed triangle of the second target point and the speed triangle of the third target point can be used for representing gas flow parameters when designing the geometric modeling of the rotor blade and the stator blade. Through the technical scheme provided by the embodiment of the disclosure, the gas flow parameters of the inlet and the outlet of the rotor blade and the stator blade at the one-dimensional uniform diameter position can be accurately obtained, the design precision of the geometric modeling of the rotor blade and the stator blade is improved, and the design period of the axial flow compressor is shortened.
For the solution shown in fig. 3, in some possible embodiments, the determining the velocity triangle of the first target point and the velocity triangle of the second target point based on the set boundary condition and the first gas flow parameter of the first target point includes:
determining a circumferential speed of the first target point based on a set boundary condition and a first gas flow parameter of the first target point, an absolute speed of the first target point and an absolute speed of the second target point;
determining a speed triangle of the first target point based on the circumferential speed of the first target point, the absolute speed of the first target point and the absolute airflow angle of the first target point;
and determining a speed triangle of the second target point based on the absolute speed of the second target point and the absolute airflow angle of the second target point.
For the above embodiment, in some examples, determining the circumferential speed of the first target point based on the set boundary condition and the first gas flow parameter of the first target point, the absolute speed of the first target point and the absolute speed of the second target point includes:
Based on the known total enthalpy of the first target pointH t1 Isentropic enthalpy with the second target pointH is2, The isentropic enthalpy of the second target point is calculated according to the formula (1)H is2, Total enthalpy of the first target pointH t1 Is the initial difference of (2)：
（1）
In the first placeiIn the iterative calculation:
based on known stage load coefficientsFirst of alli-1 difference value calculated by iteration->Calculating the circumferential velocity of the first target point according to the formula (2)U i1, ：
（2）
Wherein wheniWhen=1, the firsti-1 difference value obtained by iterative calculationFor the initial difference；
Based on the circumferential velocity of the first target point locationU i1, Calculating the absolute velocity of the first target point according to the formula (3) and the formula (4)C i1, Absolute velocity of the second target pointC i2, ：
（3）
（4）
Wherein,a flow coefficient indicating the first target point; />An absolute airflow angle representing the first target point; />A flow coefficient indicating the second target point;R r,1-2 represents the average diameter ratio of the second target point position, and，R 1 representing the average radius of the inlet of the rotor blade;R 4 representing the average radius of the outlet of the stator blade; />Absolute air representing the second target pointA flow angle;
absolute velocity based on the second target point location C i2, Calculating the total enthalpy of the second target point according to the formula (5)H t i2, ：
（5）
Wherein,H t i2, is shown in the firstiThe total enthalpy of the second target point position is calculated in a plurality of iteration,；/>representing isentropic efficiency;
according toCalculated to be at the firstiDifference between total enthalpy of the second target point and total enthalpy of the first target point in iterative calculation +.>；
For the firstiThe difference between the total enthalpy of the second target point and the total enthalpy of the first target point obtained in the iterative calculationAnd the firsti-1 difference in the obtained total enthalpy of said second target point position and the total enthalpy of said first target point position in an iterative calculation ∈1>Comparing and calculating;
if it isAccording to->Calculating to obtain the mostThe peripheral velocity of the final first target pointU 1 And calculating the absolute velocity of the first target point according to the formula (3)C 1 And calculating the absolute velocity of the second target point according to formula (4)C 2 And the iterative computation is finished;
if it isBased on->Execute the firsti+1 iterative computations.
FIG. 8 shows the acquisition of the circumferential velocity of the first target point locationU 1 Absolute velocity of first target point positionC 1 And absolute velocity of the second target pointC 2 The method comprising the following steps.
In step S801, isentropic enthalpy of the second target point location is obtained according to equation (1) H is2, Total enthalpy from first target pointH t1 Is the initial difference of (2)。
In the first placeiIn the iterative calculation:
in step S802, the circumferential velocity of the first target point is calculated according to equation (2)U i1, 。
In some examples, the stage load factorIs known for the preset.
In step S803, the circumferential velocity of the first target point calculated based on step S802U i1, The absolute velocity of the first target point can be calculated according to the formulas (3) and (4)C i1, Absolute velocity of the second target point locationC i2, 。
In some examples, for the first of formulas (3) and (4)Flow coefficient of a target pointAbsolute air flow angle of first target point position +.>Flow coefficient of the second target point location +.>Absolute air flow angle of second target point position +.>Average diameter ratioR r,1-2 Are all preset.
In step S804, the absolute velocity of the first target point calculated in step S803 is usedC i1, Absolute velocity of the second target point locationC i2, Calculating according to formula (5) to obtain total enthalpy of the second target point positionH t i2, 。
In some examples, for isentropic efficiency in equation (5)Is preset.
In step S805, the total enthalpy of the second target point location calculated based on step S804 H t i2, According toCan be calculated to be at the firstiTotal enthalpy of second target point in iterative calculationH t i2, Total enthalpy from first target pointH t1 Difference between->。
In step S806, the calculated first step in step S805 is performediDifference between total enthalpy of second target point and total enthalpy of first target point obtained in iterative calculationAnd the firsti-difference +.1 of the total enthalpy of the second target point obtained in the iterative calculation and the total enthalpy of the first target point>A comparison is made. If the comparison result is less than or equal to 0.1, step S807 is executed, ending the iterative computation. On the contrary, based on->Step S802 is continued.
It will be appreciated that the total enthalpy of the uncertainty factor to the first target point location is eliminated by iterative calculations in embodiments of the present disclosureH t1 Total enthalpy with the second target pointH t2 So that the total enthalpy of the first target point locationH t1 Total enthalpy with the second target pointH t2 Can be as close as possible to promote the circumferential velocity of the first target pointU 1 Absolute velocity of first target point positionC 1 Absolute velocity of the second target pointC 2 And the calculation error is reduced.
For the above embodiment, in some examples, determining the velocity triangle of the first target point based on the circumferential velocity of the first target point, the absolute velocity of the first target point, and the absolute airflow angle of the first target point includes:
Based on the absolute velocity of the first target pointC 1 Absolute airflow angle of the first target pointCalculating the meridian component velocity of the absolute velocity of the first target point according to the formula (6) and the formula (7)C m1 And the circumferential component speed of the absolute speed of the first target point positionC u1 ：
（6）
（7）
Based on the circumferential velocity of the first target point locationU 1 Circumferential component speed of absolute speed of the first target pointC u1 Calculating a circumferential component velocity of the relative velocity of the first target point according to equation (8)W u1 ：
（8）
Meridian component velocity based on absolute velocity of first target point positionC m1 Calculating a meridian component velocity of the relative velocity of the first target point according to formula (9)W m1 ：
（9）
Circumferential component speed based on the relative speed of the first target pointW u1 Meridian component velocity of relative velocity with the first target point positionW m1 Calculating a relative air flow angle of the first target point according to formula (10)：
（10）
Meridian component speed based on relative speed of the first target point positionW m1 Angle of relative air flow to the first target pointCalculating the relative velocity of the first target point according to the formula (11)W 1 ：
（11）。
In an embodiment of the present disclosure, when the circumferential velocity of the first target point is obtained according to the method flow shown in fig. 8 U 1 Absolute velocity with first target pointC 1 Absolute airflow angle based on first target point locationAnd the corresponding relation between the velocity component triangle of the first target point shown in fig. 9 and the velocity triangle of the first target point shown in fig. 5, i.e. the relative velocity of the first target point can be obtainedW 1 Relative air flow angle of the first target point position +.>And the remaining velocity components shown in fig. 9, the velocity triangle for the first target point shown in fig. 5 can then be determined.
For the above embodiment, in some examples, determining the velocity triangle of the second target point based on the absolute velocity of the second target point and the absolute airflow angle of the second target point includes:
absolute velocity based on the second target point locationC 2 Absolute airflow angle of the second target pointCalculating the circumferential partial velocity of the absolute velocity of the second target point according to the formulas (12) and (13)C u2 And the meridian component velocity of the absolute velocity of the second target point positionC m2 ：
（12）
（13）。
When the absolute velocity of the second target point is obtained according to the method flow shown in fig. 8C 2 Absolute airflow angle based on second target point position The velocity triangle of the second target point shown in fig. 6 can be determined. From the correspondence between the velocity component triangle of the second target point shown in fig. 10 and the velocity triangle of the third target point shown in fig. 6, the remaining velocity components of the second target point shown in fig. 10 can be obtained.
For the solution shown in fig. 3, in some possible embodiments, determining the speed triangle of the third target point based on the speed triangle of the first target point and the speed triangle of the second target point includes:
calculating the average diameter ratio of the third target point according to the formula (14) and the formula (15) by adopting a linear interpolation modeR r,1-3 And the flow coefficient of the third target point：
（14）
（15）
Wherein,R r,1-2 represents the average diameter ratio of the second target point position, and，R 1 representing the rotorAverage radius of the inlet of the blade;R 4 representing the average radius of the outlet of the stator blade; />A flow coefficient indicating the first target point; />A flow coefficient indicating the second target point;
meridian component velocity based on absolute velocity of first target point positionC m1 Or the meridian component velocity of the absolute velocity of the second target point position C m2 Calculating the meridian component velocity of the absolute velocity of the third target point according to the formula (16) or the formula (17)C m3 ：
（16）
（17）
Wherein,and (2) andC 2 representing the absolute speed of said second target point, of->An absolute airflow angle representing the second target point;U 1 a peripheral speed indicating the first target point;
based on known rotor reaction forcesCalculating the enthalpy value of the third target point according to the formula (18)H 3 ：
（18）
Wherein,H t1 representing the total enthalpy of the first target point;H t2 representing the total enthalpy of the second target point;
meridian component velocity based on absolute velocity of third target point positionC m3 Enthalpy value with the third target pointH 3 Calculating an absolute airflow angle of the third target point according to formula (19)：
（19）
Meridian component velocity based on absolute velocity of third target point positionC m3 Absolute air flow angle with the third target pointCalculating the relative air flow angle of the third target point according to the formula (20) and the formula (21)>Absolute velocity of the third target pointC 3 ：
（20）
（21）
Meridian component velocity based on absolute velocity of third target point positionC m3 Angle of relative air flow to the third target pointCalculating the relative velocity of the third target point according to the formula (22) W 3 ：
（22）
Absolute velocity based on the third target pointC 3 Absolute air flow angle with the third target pointCalculating a circumferential component velocity of the absolute velocity of the third target point according to equation (24)C u3 ：
（23）
Based on the relative speed of the third target pointW 3 Angle of relative air flow to the third target pointCalculating a circumferential component velocity of the relative velocity of the third target point according to equation (24)W u3 ：
（24）
Circumferential component speed based on absolute speed of the third target pointC u3 Circumferential component speed of relative speed to the third target pointW u3 Calculating the peripheral velocity of the third target point according to the formula (25)U 3 ：
（25）。
In an embodiment of the present disclosure, when obtaining the meridional component velocity of the absolute velocity of the third target point locationC m3 Absolute airflow angle of third target pointAnd the relative air flow angle of the third target point position +.>In this case, the relative velocity of the third target point can be obtained from the correspondence between the velocity component triangle of the third target point shown in fig. 11 and the velocity triangle of the third target point shown in fig. 7W 3 Peripheral speed of third target point positionU 3 And the remaining velocity components shown in fig. 11, the velocity triangle for the third target point shown in fig. 7 can then be determined.
It will be appreciated that the speed triangle of the first target point corresponds to the speed triangle of the inlet of the rotor blade, the speed triangle of the second target point corresponds to the speed triangle of the outlet of the stator blade, and the speed triangle of the third target point corresponds to the speed triangle of the outlet of the rotor blade. The velocity triangle of the rotor blade outlet in the embodiments of the present disclosure can represent the velocity triangle of the stator blade inlet, so the method for obtaining the velocity triangle of the stator blade inlet is not described herein in detail.
Based on the same inventive concept as the foregoing technical solution, referring to fig. 12, there is shown an acquisition device 120 for a gas flow parameter of a blade according to an embodiment of the present disclosure, where the acquisition device 120 specifically includes: a first determination unit 1201, a second determination unit 1202, and a third determination unit 1203.
The first determination section 1201 described above is configured to: determining a first target point position, a second target point position and a third target point position based on an inlet of the rotor blade at a one-dimensional uniform diameter and an outlet of the stator blade at the one-dimensional uniform diameter; wherein the first target point is located at an inlet of the rotor blade at a one-dimensional average diameter, the second target point is located at an outlet of the stator blade at a one-dimensional average diameter, and the third target point is located at an outlet of the rotor blade at a one-dimensional average diameter or an inlet of the stator blade at a one-dimensional average diameter.
The second determination section 1202 described above is configured to: and determining a speed triangle of the first target point and a speed triangle of the second target point based on the set boundary condition and the first gas flow parameter of the first target point.
The third determination section 1203 described above is configured to: determining a speed triangle of the third target point based on the speed triangle of the first target point and the speed triangle of the second target point; the speed triangle of the first target point, the speed triangle of the second target point and the speed triangle of the third target point are used for representing gas flow parameters when the geometric modeling of the rotor blade and the stator blade is designed.
It should be noted that, in the obtaining device 120 for a gas flow parameter of a blade provided in the foregoing embodiment, when implementing the function thereof, only the division of the functional modules is illustrated, and in practical application, the above-mentioned functional allocation may be implemented by different functional modules according to needs, that is, the internal structure of the terminal is divided into different functional modules, so as to implement all or part of the functions described above. In addition, the device 120 for acquiring the gas flow parameter of the blade provided in the above embodiment belongs to the same concept as the embodiment of the method for acquiring the gas flow parameter of the blade, and the detailed implementation process of the device is shown in the method embodiment, which is not described herein.
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 gas flow parameter acquisition program for a blade, which when executed by at least one processor, implements the steps of the gas flow parameter acquisition method for the blade.
The acquisition device 120 and computer storage medium of the gas flow parameters of the blade described above, see fig. 13, which illustrates a specific hardware configuration of a computing device 130 of a computing apparatus 130 capable of implementing the acquisition device 120 of the gas flow parameters of the blade described above according to an embodiment of the present disclosure, where the computing device 130 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, etc. The computing device 130 includes: a communication interface 1301, a memory 1302 and a processor 1303; the various components are coupled together by a bus system 1304. It is appreciated that the bus system 1304 is used to facilitate connected communications between the components. The bus system 1304 includes a power bus, a control bus, and a status signal bus in addition to a data bus. But for clarity of illustration, the various buses are labeled as bus system 1304 in fig. 13. Wherein,
The communication interface 1301 is configured to receive and send signals in a process of receiving and sending information with other external network elements;
the memory 1302 is configured to store a computer program that can be executed by the processor 1303;
the processor 1303 is configured to execute the following steps when executing the computer program:
determining a first target point position, a second target point position and a third target point position based on an inlet of the rotor blade at a one-dimensional uniform diameter and an outlet of the stator blade at the one-dimensional uniform diameter; wherein the first target point is located at an inlet of the rotor blade at a one-dimensional average diameter, the second target point is located at an outlet of the stator blade at a one-dimensional average diameter, and the third target point is located at an outlet of the rotor blade at a one-dimensional average diameter or an inlet of the stator blade at a one-dimensional average diameter;
determining a speed triangle of the first target point and a speed triangle of the second target point based on the set boundary condition and a first gas flow parameter of the first target point;
determining a speed triangle of the third target point based on the speed triangle of the first target point and the speed triangle of the second target point; the speed triangle of the first target point, the speed triangle of the second target point and the speed triangle of the third target point are used for representing gas flow parameters when the geometric modeling of the rotor blade and the stator blade is designed.
It is to be appreciated that the memory 1302 in embodiments of the present disclosure may be either volatile memory or nonvolatile memory, or may include both volatile and nonvolatile memory. The nonvolatile Memory may be a Read-Only Memory (ROM), a programmable Read-Only Memory (ProgrammableROM, PROM), an Erasable programmable Read-Only Memory (EPROM), an electrically Erasable programmable Read-Only Memory (ElectricallyEPROM, EEPROM), or a flash Memory, among others. The volatile memory may be random access memory (Random Access Memory, RAM) which acts as an external cache. By way of example, and not limitation, many forms of RAM are available, such as Static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double Data Rate SDRAM (Double Data Rate SDRAM), enhanced SDRAM (EnhancedSDRAM, ESDRAM), synchronous DRAM (SLDRAM), and direct memory bus RAM (DRRAM). The memory 1302 of the systems and methods described herein is intended to comprise, without being limited to, these and any other suitable types of memory.
While processor 1303 may be an integrated circuit chip with signal processing capabilities. In implementation, the steps of the method described above may be performed by integrated logic circuitry in hardware or instructions in software in the processor 1303. The processor 1303 may be a general purpose processor, a digital signal processor (Digital Signal Processor, DSP), an application specific integrated circuit (Application Specific Integrated Circuit, ASIC), a field programmable gate array (Field Programmable Gate Array, FPGA) or other programmable logic device, discrete gate or transistor logic device, discrete hardware components. The various methods, steps and logic blocks of the disclosure in the embodiments of the disclosure may be implemented or performed. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. The steps of a method disclosed in connection with the embodiments of the present disclosure may be embodied directly in hardware, in a decoded processor, or in a combination of hardware and software modules in a decoded processor. The software modules may be located in a random access memory, flash memory, read only memory, programmable read only memory, or electrically erasable programmable memory, registers, etc. as well known in the art. The storage medium is located in the memory 1302, and the processor 1303 reads information in the memory 1302, and performs the steps of the method in combination with hardware.
It is to be understood that the embodiments described herein may be implemented in hardware, software, firmware, middleware, microcode, or a combination thereof. For a hardware implementation, the processing units may be implemented within one or more application specific integrated circuits (Application Specific Integrated Circuits, ASIC), digital signal processors (Digital Signal Processing, DSP), digital signal processing devices (DSP devices, DSPD), programmable logic devices (ProgrammableLogic Device, PLD), field programmable gate arrays (Field-Programmable Gate Array, FPGA), general purpose processors, controllers, microcontrollers, microprocessors, other electronic units configured to perform the functions described herein, or a combination thereof.
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 1303 is further configured to execute the steps of the method for acquiring the gas flow parameters of the blade in the foregoing technical solution when the computer program is executed, which is not 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 (7)
1. A method of acquiring gas flow parameters of a blade, the method comprising:
determining a first target point position, a second target point position and a third target point position based on an inlet of the rotor blade at a one-dimensional uniform diameter and an outlet of the stator blade at the one-dimensional uniform diameter; the first target point is positioned at an inlet of the rotor blade at a one-dimensional uniform diameter, the second target point is positioned at an outlet of the stator blade at the one-dimensional uniform diameter, and the third target point is positioned at an outlet of the rotor blade at the one-dimensional uniform diameter or an inlet of the stator blade at the one-dimensional uniform diameter;
determining a speed triangle of the first target point location and a speed triangle of the second target point location based on a set boundary condition and a first gas flow parameter of the first target point location;
Determining a speed triangle of the third target point based on the speed triangle of the first target point and the speed triangle of the second target point; the speed triangle of the first target point position, the speed triangle of the second target point position and the speed triangle of the third target point position are used for representing gas flow parameters when the geometric modeling of the rotor blade and the stator blade is designed;
wherein the determining the speed triangle of the first target point location and the speed triangle of the second target point location based on the set boundary condition and the first gas flow parameter of the first target point location includes:
determining the circumferential speed of the first target point based on the set boundary condition and the first gas flow parameter of the first target point, and the absolute speed of the first target point and the absolute speed of the second target point;
determining a speed triangle of the first target point based on the circumferential speed of the first target point, the absolute speed of the first target point and the absolute airflow angle of the first target point;
determining a speed triangle of the second target point based on the absolute speed of the second target point and the absolute airflow angle of the second target point;
The determining, based on the set boundary condition and the first gas flow parameter of the first target point location, the circumferential speed of the first target point location, the absolute speed of the first target point location and the absolute speed of the second target point location includes:
based on known conditionsTotal enthalpy of the first target pointH t1 Isentropic enthalpy with the second target point locationH is2, The isentropic enthalpy of the second target point position is calculated according to the formula (1)H is2, Total enthalpy with the first target pointH t1 Is the initial difference of (2)：
（1）
In the first placeiIn the iterative calculation:
based on known stage load coefficientsFirst of alli-1 difference value calculated by iteration->Calculating the circumferential velocity of the first target point according to the formula (2)U i1, ：
（2）
Wherein wheniWhen=1, the firsti-1 difference value obtained by iterative calculationFor the initial difference；
Based on the circumferential velocity of the first target point locationU i1, Calculating the absolute velocity of the first target point according to the formula (3) and the formula (4)C i1, Absolute velocity of the second target point locationC i2, ：
（3）
（4）
Wherein,a flow coefficient representing the first target point location; />An absolute airflow angle representing the first target point location; />A flow coefficient representing the second target point location; R r,1-2 Represents the average diameter ratio of the second target point position, and，R 1 representing an average radius of an inlet of the rotor blade;R 4 representing an average radius of an outlet of the stator vane; />An absolute airflow angle representing the second target point location;
based on the absolute velocity of the second target point locationC i2, Calculating the total enthalpy of the second target point according to the formula (5)H t i2, ：
（5）
Wherein,H t i2, is shown inFirst, theiThe total enthalpy of the second target point location in the iterative calculation,；/>representing isentropic efficiency;
according toCalculated to be at the firstiDifference between total enthalpy of the second target point and total enthalpy of the first target point in iterative calculation +.>；
For the firstiThe difference value of the total enthalpy of the second target point position and the total enthalpy of the first target point position obtained in the iterative calculationAnd the firsti-the resulting difference of the total enthalpy of said second target point location and the total enthalpy of said first target point location in 1 iterative calculation ∈1>Comparing and calculating;
if it isAccording to->Calculating to obtain the final circumferential velocity of the first target point positionU 1 And calculating the absolute velocity of the first target point according to the formula (3)C 1 And calculating the absolute velocity of the second target point according to formula (4)C 2 And the iterative computation is finished;
If it isBased on->Execute the firsti+1 iterative computations.
2. The method according to claim 1, wherein the determining the velocity triangle of the first target point based on the circumferential velocity of the first target point, the absolute velocity of the first target point, and the absolute airflow angle of the first target point includes:
based on the absolute velocity of the first target point locationC 1 Absolute airflow angle of the first target pointCalculating the meridian component velocity of the absolute velocity of the first target point according to the formula (6) and the formula (7)C m1 And the circumferential component speed of the absolute speed of the first target point positionC u1 ：
（6）
（7）
Based on the circumferential velocity of the first target point locationU 1 Circumferential component speed of absolute speed with the first target point positionC u1 Calculating a circumferential component speed of the relative speed of the first target point according to equation (8)W u1 ：
（8）
Meridian direction based on absolute velocity of the first target point locationC m1 Calculating a meridional component velocity of the relative velocity of the first target point according to formula (9)W m1 ：
（9）
Circumferential component speed based on relative speed of the first target point locationW u1 Meridional component velocity of relative velocity to the first target point location W m1 Calculating the relative air flow angle of the first target point according to the formula (10)：
（10）
Meridian component velocity based on relative velocity of the first target point locationW m1 Relative air flow angle to the first target pointCalculating the relative velocity of the first target point according to the formula (11)W 1 ：
（11）。
3. The method of claim 1, wherein the determining a velocity triangle for the second target point based on the absolute velocity of the second target point and the absolute airflow angle for the second target point comprises:
based on the absolute velocity of the second target point locationC 2 Absolute airflow angle of the second target pointCalculating the circumferential partial velocity of the absolute velocity of the second target point according to the formula (12) and the formula (13)C u2 And the meridian component velocity of the absolute velocity of the second target point positionC m2 ：
（12）
（13）。
4. The method of claim 1, wherein the determining the speed triangle for the third target point based on the speed triangle for the first target point and the speed triangle for the second target point comprises:
calculating according to the formula (14) and the formula (15) to obtain the average diameter ratio of the third target point position by adopting a linear interpolation mode R r,1-3 And the flow coefficient of the third target point position：
（14）
（15）
Wherein,R r,1-2 represents the average diameter ratio of the second target point position, and，R 1 representing an average radius of an inlet of the rotor blade;R 4 representing an average radius of an outlet of the stator vane; />A flow coefficient representing the first target point location; />A flow coefficient representing the second target point location;
meridian component velocity based on absolute velocity of the first target point positionC m1 Or the meridional component velocity of the absolute velocity of the second target point positionC m2 Calculating the meridian component velocity of the absolute velocity of the third target point according to the formula (16) or the formula (17)C m3 ：
（16）
（17）
Wherein,and (2) andC 2 representing the absolute speed of said second target point location,/->An absolute airflow angle representing the second target point location;U 1 representing a circumferential velocity of the first target point location;
based on known rotor reaction forcesCalculating the enthalpy value of the third target point according to the formula (18)H 3 ：
（18）
Wherein,H t1 representing the total enthalpy of the first target point location;H t2 representing the total enthalpy of the second target point location;
meridian component velocity based on absolute velocity of the third target point positionC m3 Enthalpy value with the third target pointH 3 Calculating the absolute airflow angle of the third target point according to the formula (19) ：
（19）
Meridian component velocity based on absolute velocity of the third target point positionC m3 Absolute airflow angle with the third target pointCalculating the relative air flow angle of the third target point according to the formula (20) and the formula (21)>Absolute velocity with the third target pointC 3 ：
（20）
（21）
Meridian component velocity based on absolute velocity of the third target point positionC m3 Relative air flow angle to the third target pointCalculating the relative velocity of the third target point according to the formula (22)W 3 ：
（22）
Based on the absolute velocity of the third target point locationC 3 Absolute airflow angle with the third target pointCalculating the circumferential component speed of the absolute speed of the third target point according to the formula (23)C u3 ：
（23）
Based on the relative velocity of the third target point locationW 3 Relative air flow angle to the third target pointCalculating a circumferential component speed of the relative speed of the third target point according to equation (24)W u3 ：
（24）
Circumferential component speed based on absolute speed of the third target point locationC u3 Circumferential component speed of relative speed to the third target pointW u3 The third target point is calculated according to formula (25)Peripheral speed of bitsU 3 ：
（25）。
5. An acquisition device of gas flow parameters of a blade, characterized in that the acquisition device comprises: a first determination unit, a second determination unit, and a third determination unit; wherein,
The first determination section is configured to: determining a first target point position, a second target point position and a third target point position based on an inlet of the rotor blade at a one-dimensional uniform diameter and an outlet of the stator blade at the one-dimensional uniform diameter; the first target point is positioned at an inlet of the rotor blade at a one-dimensional uniform diameter, the second target point is positioned at an outlet of the stator blade at the one-dimensional uniform diameter, and the third target point is positioned at an outlet of the rotor blade at the one-dimensional uniform diameter or an inlet of the stator blade at the one-dimensional uniform diameter;
the second determination section is configured to: determining a speed triangle of the first target point location and a speed triangle of the second target point location based on a set boundary condition and a first gas flow parameter of the first target point location;
the third determination section is configured to: determining a speed triangle of the third target point based on the speed triangle of the first target point and the speed triangle of the second target point; the speed triangle of the first target point position, the speed triangle of the second target point position and the speed triangle of the third target point position are used for representing gas flow parameters when the geometric modeling of the rotor blade and the stator blade is designed;
Wherein the second determination section is configured to:
determining the circumferential speed of the first target point based on the set boundary condition and the first gas flow parameter of the first target point, and the absolute speed of the first target point and the absolute speed of the second target point;
determining a speed triangle of the first target point based on the circumferential speed of the first target point, the absolute speed of the first target point and the absolute airflow angle of the first target point;
determining a speed triangle of the second target point based on the absolute speed of the second target point and the absolute airflow angle of the second target point;
wherein the second determining section is further configured to:
based on the known total enthalpy of the first target point locationH t1 Isentropic enthalpy with the second target point locationH is2, The isentropic enthalpy of the second target point position is calculated according to the formula (1)H is2, Total enthalpy with the first target pointH t1 Is the initial difference of (2)：
（1）
In the first placeiIn the iterative calculation:
based on known stage load coefficientsFirst of alli-1 difference value calculated by iteration->Calculating the circumferential velocity of the first target point according to the formula (2) U i1, ：
（2）
Wherein wheniWhen=1, the firsti-1 timeIterative calculation of the differenceFor the initial difference；
Based on the circumferential velocity of the first target point locationU i1, Calculating the absolute velocity of the first target point according to the formula (3) and the formula (4)C i1, Absolute velocity of the second target point locationC i2, ：
（3）
（4）
Wherein,a flow coefficient representing the first target point location; />An absolute airflow angle representing the first target point location; />A flow coefficient representing the second target point location;R r,1-2 represents the average diameter ratio of the second target point position, and，R 1 representing an average radius of an inlet of the rotor blade;R 4 representing an average radius of an outlet of the stator vane; />An absolute airflow angle representing the second target point location;
based on the absolute velocity of the second target point locationC i2, Calculating the total enthalpy of the second target point according to the formula (5)H t i2, ：
（5）
Wherein,H t i2, is shown in the firstiThe total enthalpy of the second target point location in the iterative calculation,；representing isentropic efficiency;
according toCalculated to be at the firstiDifference between total enthalpy of the second target point and total enthalpy of the first target point in iterative calculation +.>；
For the firstiThe difference value of the total enthalpy of the second target point position and the total enthalpy of the first target point position obtained in the iterative calculation And the firsti-the resulting difference of the total enthalpy of said second target point location and the total enthalpy of said first target point location in 1 iterative calculation ∈1>Comparing and calculating;
if it isAccording to->Calculating to obtain the final circumferential velocity of the first target point positionU 1 And calculating the absolute velocity of the first target point according to the formula (3)C 1 And calculating the absolute velocity of the second target point according to formula (4)C 2 And the iterative computation is finished;
if it isBased on->Execute the firsti+1 iterative computations.
6. 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 perform the steps of the method for acquiring gas flow parameters of the blade according to any one of claims 1 to 4 when running the computer program.
7. A computer storage medium storing a program for acquiring gas flow parameters of a blade, which when executed by at least one processor, implements the steps of the method for acquiring gas flow parameters of a blade according to any one of claims 1 to 4.
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