CN112685968B - Axial flow compressor pneumatic design method based on space load customization thought - Google Patents
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Abstract
The invention aims to provide an axial flow compressor pneumatic design method based on a space load customization idea, and an axial flow compressor pneumatic design scheme meeting design index requirements is obtained through repeated iteration of links such as space load control design parameter selection, one-dimensional inverse problem through-flow design, one-dimensional characteristic analysis, S2 inverse problem through-flow design, blade modeling design and three-dimensional CFD calculation analysis. The invention can realize the customized design of the internal load of the compressor under multiple working condition points and the parametric pneumatic design under different dimensions through the load control parameters, thereby effectively solving the problem of the space load matching unbalance of the multistage axial flow compressor under the design working condition and the non-design working condition, improving the design precision and shortening the design period. Meanwhile, the method is not limited to the multistage axial flow compressor of the gas turbine, and is also suitable for the pneumatic design process of various industrial axial flow compressors and axial flow compressors of aircraft engines.
Description
Technical Field
The invention relates to a design method of a gas compressor, in particular to a pneumatic design method of an axial flow gas compressor.
Background
The compressor is one of three large core components of the gas turbine, and the performance of the compressor plays a decisive role in realizing the technical indexes of the gas turbine. Designing a compressor with excellent performance indexes and high reliability, reducing design cost and shortening design period simultaneously becomes one of the main research directions in the field of modern impeller mechanical design. In order to improve the efficiency and power of the gas turbine and expand the stable working range of the unit, the compressor is required to have stronger compression capacity, lower aerodynamic loss and wider stable working range. In order to meet the requirements, modern gas compressors are continuously developing towards the directions of high pressure ratio, high efficiency and large surge margin, which puts higher requirements on the pneumatic design of the gas compressors.
The axial-flow compressor is a typical structure form which is most widely applied in the compressor, and the pneumatic design technology of the axial-flow compressor is one of the most core technologies in the research and development system of the gas turbine. Meanwhile, due to the fact that the number of stages is large, the internal flow mechanism is relatively complex, mutual interference effect, space three-dimensional effect and strong nonlinearity among blade rows are quite remarkable, and design difficulty is extremely high. Therefore, advanced pneumatic design technology and means based on new ideas and new methods must be explored and developed to deal with the difficulty and challenge brought to the design of the compressor by the development of the gas turbine, and the method has very important significance for accelerating the establishment and the perfection of the design system for independently developing and developing the compressor and even the gas turbine.
Disclosure of Invention
The invention aims to provide an axial flow compressor pneumatic design method based on a space load customization idea for solving the problem of multi-stage axial flow compressor pneumatic design.
The purpose of the invention is realized as follows:
the invention relates to an axial flow compressor pneumatic design method based on a space load customization idea, which is characterized by comprising the following steps of:
(1) selecting space load control design parameters: based on the idea of customizing the space load, the design parameters capable of reasonably representing the load distribution condition of the axial flow compressor in the process of pneumatically designing the axial flow compressor from low dimensionality to high dimensionality are extracted and used as space load control parameters to carry out the pneumatic design of the axial flow compressor, three dimensionless parameters of a flow coefficient phi, a load coefficient psi and a reaction degree omega are used as the space load control parameters, and the specific formula is as follows:
in the formula, C1aIs the axial speed of the inlet of the movable blade; u is the peripheral speed; c1u、C2uRespectively the absolute tangential speeds of the inlet and the outlet of the movable vane;
(2) one-dimensional inverse problem flow design: adopting the extracted space load control parameters to carry out one-dimensional inverse problem design of the axial flow compressor and complete the step-by-step distribution rule design of the space load control parameters along the flow direction of the compressor; in the specific design process, input parameters comprise design conditions, inlet and outlet airflow conditions and partial geometric conditions, and meanwhile, according to the specific design requirements of the axial flow compressor to be designed, the step-by-step distribution rule of the flow coefficient phi, the load coefficient psi and the reaction degree omega at the mean diameter position of the compressor is selected, and the initial design scheme of the compressor is obtained through calculation;
(3) one-dimensional characteristic analysis: calculating and analyzing the one-dimensional positive problem characteristic of the axial flow compressor, and preliminarily predicting the total performance condition of the compressor at different rotating speeds; on the basis of obtaining the elementary-level geometric parameters of the middle section of the gas compressor, calculating the characteristics of the gas compressor under different rotating speeds by adopting an HARKIA algorithm based on a level superposition method;
(4) s2 inverse problem current flow design: based on the step-by-step distribution rule of the space load control parameters obtained by the one-dimensional inverse problem through-flow design along the flow direction of the compressor, the S2 inverse problem design of the axial flow compressor is carried out, and the design of the distribution rule of the space load control parameters along the radial direction of each row of blades of the compressor is completed:
(5) blade modeling design: the method comprises the following steps of (1) designing a two-dimensional blade profile and designing a three-dimensional blade;
firstly, on the basis of the reverse problem through-flow design result of S2, designing two-dimensional primitive blade profiles with different sections of each row of blades along the diameter, and calculating the minimum loss attack angle and the minimum loss relief angle of the blade profiles according to the working environment and the spatial position of the primitive blade profiles; designing two-dimensional geometric blade profiles of different positions of each row of blades along the diameter through typical blade profile load control parameters, and adopting blade profile geometric modeling parameters related to element blade profile mean camber lines and thickness distribution molded lines as typical blade profile load control parameters;
then selecting a radial stacking mode according to the space load distribution characteristics of each row of blades, and simultaneously adopting three-dimensional blade load control parameters to carry out bending, sweeping and other end region load regulation and control design to complete the three-dimensional geometric modeling of each row of blades of the gas compressor; the design parameters which can be associated with the radial pressure distribution of the blade body in the parametric modeling of the blade end region are used as three-dimensional blade load control parameters, so that the load regulation and control of the end region are realized;
(6) three-dimensional CFD computational analysis: the method comprises the steps of performing full three-dimensional CFD numerical simulation analysis work on design points and variable working conditions of the gas compressor, obtaining the performance and the internal flow field condition of the gas compressor at the design points and at different rotating speeds through three-dimensional CFD calculation, and judging whether the design requirements are met;
if the design requirement is met, the current pneumatic design scheme of the compressor is a final design scheme;
if the design requirement is not met, returning to the step needing to be adjusted to carry out design optimization according to the specific analysis result of the internal flow field of the compressor, wherein the design optimization comprises flow direction load optimization adjustment in one-dimensional inverse problem through-flow design, span direction load optimization adjustment in S2 inverse problem through-flow design, end region load optimization regulation and control in blade modeling design, and attack angle matching optimization of each blade row of the compressor through multi-working-point three-dimensional flow field joint analysis, and finally obtaining the pneumatic design scheme of the axial flow compressor meeting the design index requirement through repeated iteration.
The present invention may further comprise:
1. the matching of the through-flow capacity of each stage of the compressor is controlled through the flow coefficient phi, the distribution of the load of each stage of the compressor is controlled through the load coefficient psi, and the load distribution between the movable blade and the fixed blade of each stage is controlled through the reaction degree omega.
2. S2 the anti-problem through-flow design comprises the following specific steps:
firstly, the through-flow pneumatic parameters of the axial flow compressor are designed along the radial span-wise distortion rule of each row of blades to obtain the prewhirl C of each stage of movable blade inlet1uThe following formula is adopted for designing the distortion rule:
in the formula, Rm1The average radius of the inlet of the stage of the movable blade; u shapem1The peripheral speed, omega, at the position of the uniform diameter of the inlet of the stage of movable blademThe reaction degree at the stage of mean diameter is shown; psimThe load coefficient at the stage of mean diameter is taken as the load coefficient; a. b is a distortion rule design index;
when a is 1 and b is 1, the twisting rule of the equal ring quantity is obtained;
when a is equal to-1 and b is equal to 1, the equal reaction degree torsion law is obtained;
when a belongs to (-1,1) and b is 1, the distortion law is intermediate, wherein when a is 0 and b is 1, the distortion law is exponential vortex distortion law;
when a is 0 and b is 0, the constant vortex distortion law is obtained;
different distortion rule designs are realized by selecting different values of a and b, so that different positions R of inlets of movable blades of each stage of the gas compressor along the diameter are obtained1Pre-rotation distribution of (c);
after the spanwise distortion rule design is finished, an axisymmetric meridian flow surface is selected as a typical S2 flow surface, a one-dimensional inverse problem through-flow design and a spanwise distortion rule design result are used as input, the radial distribution condition of the total pressure recovery coefficient of the movable blades and the static blades is given, the inverse problem is solved by adopting a streamline curvature method, and the radial pneumatic parameter distribution of each movable blade row and each static blade row of the axial flow compressor is obtained.
3. The following method is adopted to calculate the minimum loss attack angle and the minimum drop angle of the blade profile:
angle of attack: i.e. iref＝i0+nθ+△i(l,Ma)
In the formula i0A zero bend cascade reference angle of attack; n is the rate of change of the angle of attack with the bend angle; theta is a blade-shaped bend angle; and the delta i (l, Ma) is a function related to the position of the blade profile along the diameter and the Mach number of the incoming flow and is used for correcting the influence of the three-dimensional effect and the Mach number on the attack angle.
And (3) the falling angle:
in the formula, delta0The blade grid reference falling relief angle is zero; m isσ＝1The change rate of the falling angle and the bending angle when the consistency of the blade cascade is 1 is shown; sigma is the consistency of the leaf cascade; e is a consistency index factor which is a function of the airfoil inlet flow angle; d delta di is the change rate of the blade profile relief angle along with the attack angle; delta (l, Ma) is a function related to the position of the blade profile along the diameter and the Mach number of an incoming flow and is used for correcting the influence of a three-dimensional effect and the Mach number on the drop angle;
the axial speed correction is a function of the axial speed of the blade type inlet and outlet.
The invention has the advantages that:
1. the axial flow compressor pneumatic design method based on the space load customization thought can realize customized design of the internal load of the compressor under multiple working condition points through the load control parameters, thereby effectively solving the problem of space load matching unbalance of the multistage axial flow compressor under the design working condition and the non-design working condition and improving the pneumatic performance of the compressor.
2. The axial flow compressor pneumatic design method based on the space load customization thought can realize parametric pneumatic design of the compressor under different dimensions, effectively improve the design precision, save a large amount of design iteration time and shorten the design period.
3. The axial flow compressor pneumatic design method based on the space load customization thought is not only limited to the multistage axial flow compressor of the gas turbine, but also is suitable for the pneumatic design process of various industrial axial flow compressors and axial flow compressors of aircraft engines.
Drawings
FIG. 1 is a flow chart of the present invention.
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
with reference to fig. 1, the specific implementation of the method for designing the axial flow compressor based on the idea of customizing the space load according to the present invention is realized by the following steps:
the method comprises the following steps: and selecting space load control design parameters. Based on the idea of customizing the space load, design parameters capable of reasonably representing the load distribution condition of the axial flow compressor in the process of pneumatically designing the axial flow compressor from low dimension to high dimension are extracted and used as space load control parameters to carry out the pneumatic design of the axial flow compressor. Three dimensionless parameters of a flow coefficient phi, a load coefficient psi and a reaction degree omega are generally adopted as space load control parameters, and a specific formula is as follows:
flow coefficient:
load factor:
degree of reaction:
in the formula, C1aIs the axial speed of the inlet of the movable blade; u is the peripheral speed; c1u、C2uRespectively the absolute tangential speeds of the inlet and the outlet of the movable vane.
The three typical dimensionless parameters are selected as space load control parameters, the matching of the through-flow capacity of each stage of the compressor is controlled through a flow coefficient phi, the distribution of the load of each stage of the compressor is controlled through a load coefficient psi, and the load distribution between each stage of the movable blade and the fixed blade is controlled through a reaction degree omega.
Step two: one-dimensional inverse problem flow-through design. And (3) carrying out one-dimensional inverse problem design work on the axial flow compressor by adopting the extracted space load control parameters, and finishing the step-by-step distribution rule design of the space load control parameters along the flow direction of the compressor. In the specific design process, the main input parameters comprise design conditions (rotating speed, stage pressure ratio and flow rate), inlet and outlet airflow conditions (inlet total pressure, total temperature, inlet and outlet airflow angles and inlet and outlet axial speeds) and partial geometric conditions (through-flow form, given runner outer diameter, axial clearance and the like), and meanwhile, according to the specific design requirements of the axial flow compressor to be designed, a proper flow coefficient phi, a proper load coefficient psi and a proper step-by-step distribution rule of reaction degree omega at the mean diameter position of the compressor are selected, and the initial design scheme of the compressor is obtained through calculation.
Step three: and (5) analyzing one-dimensional characteristics. And performing one-dimensional positive problem characteristic calculation and analysis work on the axial flow compressor, and preliminarily predicting the total performance condition of the compressor at different rotating speeds. On the basis of obtaining the elementary-level geometric parameters of the middle section of the compressor, the HARKIA algorithm based on the level superposition method is adopted to calculate the characteristics of the compressor under the conditions of different rotating speeds.
Step four: s2 inverse problem current flow design. And (3) performing S2 anti-problem design work of the axial flow compressor based on a step-by-step distribution rule of the space load control parameters obtained by one-dimensional anti-problem through-flow design along the flow direction of the compressor, and completing the design of the distribution rule of the space load control parameters along the radial direction of each row of blades of the compressor.
Firstly, the through-flow pneumatic parameters of the axial flow compressor are designed along the radial span-wise distortion rule of each row of blades to obtain the prewhirl C of each stage of movable blade inlet1u. Based on space load control parameters, the invention adopts the following formula to design the distortion rule:
in the formula, Rm1The average radius of the inlet of the stage of the movable blade; u shapem1The peripheral speed, omega, at the position of the uniform diameter of the inlet of the stage of movable blademThe reaction degree at the stage of mean diameter is shown; psimThe load factor at the mean diameter of the stage. The above parameters are obtained through one-dimensional inverse problem through-flow design; a. b is a distortion rule design index, and the value range of the distortion rule design index is usually in the range of-1 to + 1:
when a is 1 and b is 1, the law is equal ring volume (free vortex) distortion law;
when a is equal to-1 and b is equal to 1, the equal reaction degree torsion law is obtained;
when a belongs to (-1,1) and b is 1, the distortion law is intermediate, wherein when a is 0 and b is 1, the distortion law is exponential vortex distortion law;
when a is 0 and b is 0, the law of constant vortex distortion is obtained.
Different distortion rule designs are realized by selecting different values of a and b, so that different positions R of inlets of movable blades of each stage of the gas compressor along the diameter are obtained1Pre-rotation distribution of (c).
After the spanwise distortion rule design is completed, an axisymmetric meridian flow surface is selected as a typical S2 flow surface, one-dimensional inverse problem through-flow design and spanwise distortion rule design results are used as input, the distribution conditions of key loss parameters such as the efficiency of the movable blades and the total pressure recovery coefficient of the fixed blades in the radial direction are given, the inverse problem solution is carried out by adopting a streamline curvature method, and the radial pneumatic parameter distribution of each movable blade row and each static blade row of the axial flow compressor is obtained.
Step five: and (5) designing the shape of the blade. The method comprises two parts of work contents of two-dimensional blade profile design and three-dimensional blade design.
Firstly, on the basis of the reverse problem through-flow design result of S2, the two-dimensional element blade profile design of each row of blades along different diameters and different sections is carried out. And calculating the minimum loss attack angle and the minimum loss relief angle according to the working environment and the spatial position of the primitive blade profile. The invention adopts the following method to calculate the minimum loss attack angle and the minimum drop angle of the blade profile:
angle of attack: i.e. iref＝i0+nθ+△i(l,Ma)
In the formula i0A zero bend cascade reference angle of attack; n is the rate of change of the angle of attack with the bend angle; theta is a blade-shaped bend angle; and the delta i (l, Ma) is a function related to the position of the blade profile along the diameter and the Mach number of the incoming flow and is used for correcting the influence of the three-dimensional effect and the Mach number on the attack angle.
And (3) the falling angle:
in the formula, delta0The blade grid reference falling relief angle is zero; m isσ＝1The change rate of the falling angle and the bending angle when the consistency of the blade cascade is 1 is shown; sigma is the consistency of the leaf cascade; e is a consistency index factor which is a function of the airfoil inlet flow angle; d delta/di is the change rate of the blade profile relief angle along with the attack angle; delta delta (l, Ma) is the radial position of the profile andthe function related to the incoming flow Mach number is used for correcting the three-dimensional effect and the influence of the Mach number on the falling angle;
the axial speed correction is a function of the axial speed of the blade type inlet and outlet.
After the minimum loss attack angle and the fall angle of each elementary blade profile at the spatial position of the gas compressor are obtained, the two-dimensional geometric blade profile at different positions along the diameter of each row of blades is designed according to typical blade profile load control parameters. Typically, the geometric profile parameters of the airfoil associated with the primitive airfoil mean camber line and thickness profile are used as typical airfoil load control parameters, such as chord length, consistency, maximum deflection location, maximum thickness location, relative maximum thickness, curvature control parameters of the mean camber line and thickness profile, and the like.
And then selecting a proper radial stacking mode according to the space load distribution characteristics of each row of blades, and simultaneously adopting three-dimensional blade load control parameters to carry out bending, sweeping and other end region load regulation and control design to complete the three-dimensional geometric modeling of each row of blades of the gas compressor. Design parameters which can be associated with radial pressure distribution of a blade body in parametric modeling of a blade end region are usually adopted as three-dimensional blade load control parameters, so that load regulation and control of the end region are realized, such as bending angle and bending height in bent blade design, sweep angle and sweep height in swept blade design and the like.
Step six: and (4) three-dimensional CFD computational analysis. The method comprises the full three-dimensional CFD numerical simulation analysis work of the design point and the variable working condition of the gas compressor. And (3) obtaining the performance and the internal flow field condition of the gas compressor at the design point and at different rotating speeds through three-dimensional CFD calculation, and judging whether the design requirements are met.
If the design requirement is met, the current pneumatic design scheme of the compressor can be considered as a final design scheme;
if the design requirements are not met, returning to the step needing to be adjusted for design optimization according to the specific analysis result of the internal flow field of the compressor, wherein the step comprises flow direction load optimization adjustment in one-dimensional inverse problem through-flow design, spanwise load optimization adjustment in S2 inverse problem through-flow design, end region load optimization regulation and control in blade modeling design, attack angle matching optimization of each blade row of the compressor through multi-working-point three-dimensional flow field joint analysis and the like; for the axial-flow compressor with the rotatable guide/stationary blades, the method also comprises the optimization of the joint regulation rule of multiple rows of rotatable guide/stationary blades.
And through repeated iteration of the work of each link, the pneumatic design scheme of the axial flow compressor which finally meets the design index requirements is obtained.
The method for designing the axial flow compressor based on the space load customization idea has universality, is not limited to the multistage axial flow compressor of the gas turbine, and is also suitable for the pneumatic design process of the axial flow compressors of various industrial axial flow compressors and aircraft engines.
Claims (4)
1. The axial flow compressor pneumatic design method based on the space load customization idea is characterized by comprising the following steps:
(1) selecting space load control design parameters: based on the idea of customizing the space load, the design parameters capable of reasonably representing the load distribution condition of the axial flow compressor in the process of pneumatically designing the axial flow compressor from low dimensionality to high dimensionality are extracted and used as space load control parameters to carry out the pneumatic design of the axial flow compressor, three dimensionless parameters of a flow coefficient phi, a load coefficient psi and a reaction degree omega are used as the space load control parameters, and the specific formula is as follows:
in the formula, C1aIs the axial speed of the inlet of the movable blade; u is the peripheral speed; c1u、C2uRespectively the absolute tangential speeds of the inlet and the outlet of the movable vane;
(2) one-dimensional inverse problem flow design: adopting the extracted space load control parameters to carry out one-dimensional inverse problem design of the axial flow compressor and complete the step-by-step distribution rule design of the space load control parameters along the flow direction of the compressor; in the specific design process, input parameters comprise design conditions, inlet and outlet airflow conditions and partial geometric conditions, and meanwhile, according to the specific design requirements of the axial flow compressor to be designed, the step-by-step distribution rule of the flow coefficient phi, the load coefficient psi and the reaction degree omega at the mean diameter position of the compressor is selected, and the initial design scheme of the compressor is obtained through calculation;
(3) one-dimensional characteristic analysis: calculating and analyzing the one-dimensional positive problem characteristic of the axial flow compressor, and preliminarily predicting the total performance condition of the compressor at different rotating speeds; on the basis of obtaining the elementary-level geometric parameters of the middle section of the gas compressor, calculating the characteristics of the gas compressor under different rotating speeds by adopting an HARKIA algorithm based on a level superposition method;
(4) s2 inverse problem current flow design: based on the step-by-step distribution rule of the space load control parameters obtained by the one-dimensional inverse problem through-flow design along the flow direction of the compressor, the S2 inverse problem design of the axial flow compressor is carried out, and the design of the distribution rule of the space load control parameters along the radial direction of each row of blades of the compressor is completed:
(5) blade modeling design: the method comprises the following steps of (1) designing a two-dimensional blade profile and designing a three-dimensional blade;
firstly, on the basis of the reverse problem through-flow design result of S2, designing two-dimensional primitive blade profiles with different sections of each row of blades along the diameter, and calculating the minimum loss attack angle and the minimum loss relief angle of the blade profiles according to the working environment and the spatial position of the primitive blade profiles; designing two-dimensional geometric blade profiles of different positions of each row of blades along the diameter through typical blade profile load control parameters, and adopting blade profile geometric modeling parameters related to element blade profile mean camber lines and thickness distribution molded lines as typical blade profile load control parameters;
then selecting a radial stacking mode according to the space load distribution characteristics of each row of blades, and simultaneously adopting three-dimensional blade load control parameters to carry out load regulation and control design on a bending and sweeping end region to complete the three-dimensional geometric modeling of each row of blades of the gas compressor; the design parameters which can be associated with the radial pressure distribution of the blade body in the parametric modeling of the blade end region are used as three-dimensional blade load control parameters, so that the load regulation and control of the end region are realized;
(6) three-dimensional CFD computational analysis: the method comprises the steps of performing full three-dimensional CFD numerical simulation analysis work on design points and variable working conditions of the gas compressor, obtaining the performance and the internal flow field condition of the gas compressor at the design points and at different rotating speeds through three-dimensional CFD calculation, and judging whether the design requirements are met;
if the design requirement is met, the current pneumatic design scheme of the compressor is a final design scheme;
if the design requirement is not met, returning to the step needing to be adjusted to carry out design optimization according to the specific analysis result of the internal flow field of the compressor, wherein the design optimization comprises flow direction load optimization adjustment in one-dimensional inverse problem through-flow design, spanwise load optimization adjustment in S2 inverse problem through-flow design and end region load optimization regulation and control in blade modeling design, and attack angle matching optimization of each blade row of the compressor is carried out through multi-working-point three-dimensional flow field joint analysis, and the pneumatic design scheme of the axial flow compressor finally meeting the design index requirement is obtained through repeated iteration.
2. The method for designing the axial flow compressor aerodynamically based on the idea of customizing the space load according to claim 1, wherein: the matching of the through-flow capacity of each stage of the compressor is controlled through the flow coefficient phi, the distribution of the load of each stage of the compressor is controlled through the load coefficient psi, and the load distribution between the movable blade and the fixed blade of each stage is controlled through the reaction degree omega.
3. The method for designing the axial flow compressor aerodynamically based on the idea of customizing the space load according to claim 1, wherein: s2 the anti-problem through-flow design comprises the following specific steps:
firstly, the through-flow pneumatic parameters of the axial flow compressor are designed along the radial span-wise distortion rule of each row of blades to obtain the absolute tangential velocity C of each stage of movable blade inlet1uThe following formula is adopted for designing the distortion rule:
in the formula, Rm1The average radius of the inlet of the stage of the movable blade; u shapem1The peripheral speed, omega, at the position of the uniform diameter of the inlet of the stage of movable blademThe reaction degree at the stage of mean diameter is shown; psimThe load coefficient at the stage of mean diameter is taken as the load coefficient; a. b is a distortion rule design index;
when a is 1 and b is 1, the twisting rule of the equal ring quantity is obtained;
when a is equal to-1 and b is equal to 1, the equal reaction degree torsion law is obtained;
when a belongs to (-1,1) and b is 1, the distortion law is intermediate, wherein when a is 0 and b is 1, the distortion law is exponential vortex distortion law;
when a is 0 and b is 0, the constant vortex distortion law is obtained;
different distortion rule designs are realized by selecting different values of a and b, so that different positions R of inlets of movable blades of each stage of the gas compressor along the diameter are obtained1Pre-rotation distribution of (c);
after the spanwise distortion rule design is finished, an axisymmetric meridian flow surface is selected as a typical S2 flow surface, a one-dimensional inverse problem through-flow design and a spanwise distortion rule design result are used as input, the radial distribution condition of the total pressure recovery coefficient of the movable blades and the static blades is given, the inverse problem is solved by adopting a streamline curvature method, and the radial pneumatic parameter distribution of each movable blade row and each static blade row of the axial flow compressor is obtained.
4. The method for designing the axial flow compressor aerodynamically based on the idea of customizing the space load according to claim 1, wherein: the following method is adopted to calculate the minimum loss attack angle and the minimum drop angle of the blade profile:
angle of attack: i.e. iref＝i0+nθ+Δi(l,Ma)
In the formula i0A zero bend cascade reference angle of attack; n is the rate of change of the angle of attack with the bend angle; theta is a blade-shaped bend angle; the delta i (l, Ma) is a function related to the position of the blade profile along the diameter and the Mach number of the incoming flow and is used for correcting the influence of a three-dimensional effect and the Mach number on an attack angle;
and (3) the falling angle:
in the formula, delta0The blade grid reference falling relief angle is zero; m isσ＝1The change rate of the falling angle and the bending angle when the consistency of the blade cascade is 1 is shown; sigma is the consistency of the leaf cascade; e is a consistency index factor which is a function of the airfoil inlet flow angle; d delta/di is the change rate of the blade profile relief angle along with the attack angle; delta (l, Ma) is a function related to the position of the blade profile along the diameter and the Mach number of an incoming flow and is used for correcting the influence of a three-dimensional effect and the Mach number on the falling angle; deltaCaThe axial speed correction is a function of the axial speed of the blade type inlet and outlet.
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