CN109165440B - Full three-dimensional interstage pneumatic matching optimization method of axial flow compressor - Google Patents
Full three-dimensional interstage pneumatic matching optimization method of axial flow compressor Download PDFInfo
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Abstract
本发明提供了一种轴流压气机全三维级间气动匹配优化方法，对给定的轴流压气机叶片几何，采用RANS方法，进行全三维粘性内流场数值模拟，根据数值模拟结果，构造静叶各设计截面设计目标载荷，对于转子，计算得到动叶设计截面目标载荷分布，给定出口流量边界条件，保证优化前后流量不变，即达到最终完成压气机整体级间匹配改型设计的目的。本发明可对轴流压气机静子出口旋流角分布及转子压比分布在全三维环境下同时完成定量设计，从而可对轴流压气机转子及静子同时完成改型，突破了传统轴流压气机气动匹配改型技术不可同时对动、静叶进行匹配改型的局限，得到较为理想的气动匹配效果。
The invention provides a full three-dimensional interstage aerodynamic matching optimization method for an axial flow compressor. For a given axial flow compressor blade geometry, the RANS method is used to carry out numerical simulation of a full three-dimensional viscous inner flow field. The design target load of each design section of the stator blade, for the rotor, the target load distribution of the design section of the moving blade is calculated, and the outlet flow boundary conditions are given to ensure that the flow rate remains unchanged before and after optimization, that is, to achieve the final completion of the compressor overall interstage matching and retrofit design. Purpose. The invention can simultaneously complete the quantitative design of the swirl angle distribution and the rotor pressure ratio distribution at the stator outlet of the axial flow compressor in a full three-dimensional environment, so that the rotor and the stator of the axial flow compressor can be remodeled at the same time, breaking through the traditional axial flow compressor. The aerodynamic matching and modification technology is limited to the limitation that the dynamic and stationary vanes cannot be matched and modified at the same time, and an ideal aerodynamic matching effect can be obtained.
Description
Technical Field
The invention relates to the field of compressors, in particular to a pneumatic optimization method of an axial flow compressor.
Background
The document "Liu Showei, Wu Hu, Liang, Hou Chaoshan. Multistage Axial flow Compressor Inverse problem interstage pneumatic Matching Design Method [ J ]. propulsion technology, 2017,38(09):1987 & 1994" and the document "van Rooij M P C, Dang T Q, Larosiliere L M, Improving Aerodynamics Matching of Axial Compressor Using a Three-Dimensional Multistage investment Design Method [ J ]. Journal of Turbomechanics, 2007,129(1):108 & 118" are the closest prior art to the patent of the application.
The design method for interstage pneumatic matching of reverse problem of the multistage axial flow compressor provides a method for completing interstage pneumatic matching by giving a stationary blade outlet rotational flow angle by adopting a full three-dimensional reverse method means. The document can complete full three-dimensional inverse method matching modification of the axial flow compressor in a multistage environment, but the adopted technical scheme only modifies the stationary blades of the multistage axial flow compressor and does not consider the influence of pneumatic matching of the multi-axial flow compressor with the movable blades of the compressor, so that a method for modifying the movable blades of the compressor is not provided for solving the problem of pneumatic matching.
The pneumatic Matching Method is realized by carrying out pneumatic Design in a reverse Method in a multi-stage environment in the advancing Aerodynamic Matching of Axial Compressor Using a Three-Dimensional Multistage input Design Method. The document considers that the pneumatic matching design can obtain a satisfactory result only in a multistage environment, but the document only researches the full three-dimensional inverse method modification design of the movable blades of the axial flow compressor, does not consider the influence of the fixed blades on the pneumatic matching of the compressor, and does not provide a quantitative setting method of design parameters of the movable blades of the compressor during the pneumatic matching, so that the pneumatic matching scheme of the pneumatic matching method depends on the experience of designers and lacks a definite quantitative modification method.
According to the prior art, the direct optimization in the multi-stage environment of multi-step discussion in the field of pneumatic matching of the air compressor is not comprehensively considered in the prior art, and the influence of the lower-stage internal moving and static blade rows of the multi-stage environment on the pneumatic matching of the air compressor is not comprehensively considered; meanwhile, a quantitative design method aiming at the pneumatic matching problem lacks relevant conclusions, so that a quantitative method and means are not provided for completing pneumatic matching between the axial flow compressor and the stator blade row.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a definite quantitative pneumatic matching method for an axial flow compressor, so that the heat insulation efficiency of a design point of the compressor is improved under the condition of ensuring that the design parameters such as flow rate, pressure ratio and the like of the design point are not changed.
The technical scheme adopted by the invention for solving the technical problem comprises the following detailed steps:
step 1: given the spatial geometric configuration coordinates of the blades of the full three-dimensional axial flow compressor, called as initial blade geometry, giving the total inlet temperature T0, total inlet pressure P0, inlet airflow angle alpha and outlet back pressure P of the blades of the full three-dimensional axial flow compressor, for the given blade geometry of the axial flow compressor, numerically solving a Navier-Stokes equation (RANS) method for Reynolds time average, adopting a JST format based on the center of a grid body for spatial dispersion, adopting a mixed display Rugge-Kutta time propulsion format for time propulsion, adopting a B-L algebraic turbulence model for the turbulence model, carrying out numerical simulation on a full three-dimensional viscous internal flow field to obtain the numerical simulation result of the geometric flow field of the initial blade, respectively selecting four spatial spanwise positions of which the ratios of the spanwise height of the blade height to the blade height of 0%, 10%, 70% and 100% as design blade height sections for a rotor and a stator along the spatial spanwise positions, and on each design blade height section, equally dividing the blade into 40-50 equal parts along the axial position, and respectively calculating the blade profile thickness distribution delta on four design sections of the rotor and the stator, wherein the formula (1) is as follows:
δ＝|P+-P-| (1)
wherein, P+Is a space coordinate of the suction surface of the blade, P-Is the space coordinate of the pressure surface of the blade;
calculating to obtain modified virtual displacement of the camber line of the blade of the design section of the movable blade or the static blade by adopting a formula (2); firstly, for the stator blade, calculating to obtain a virtual displacement v of arc modification in the stator blade by adopting the formula (2)n：
In the formula,. DELTA.pspDesigning a target load, p, for a designer given a blade surface of a blade or a vane at the beginning of the design+Static pressure, p, obtained for numerical simulation of suction surfaces of moving or stationary blades-Static pressure, rho, obtained for numerical simulation of pressure surfaces of blades or vanes+And ρ-Density obtained by numerical simulation of suction and pressure surfaces of moving or stationary blades, respectively, c+And c-Respectively obtaining sound velocity through numerical simulation of a suction surface and a pressure surface of the movable blade or the stationary blade, wherein delta t is a virtual time step, and 1e-5-1e-6 is taken;
step 2: after numerical simulation of the initial geometric internal flow field of the stationary blade is completed, according to the numerical simulation result, design target loads of all design sections of the stationary blade are constructed, and design target loads delta p of the stationary blade are completedspAfter construction, the target load Δ p will be designedspSubstituting the formula (2) into the above formula, and calculating to obtain the virtual displacement of camber line modification in the stator vane, wherein the construction method of the design target load distribution of each design section of the stator vane comprises the following steps:
the design target loads of the leading edge point and the trailing edge point of the given blade are both 0, the load at each position of the initial blade geometry is obtained by adopting a numerical simulation method for solving the RANS equation in the step 1, so that for the four design blade height sections selected in the step 1, the load obtained by numerical simulation at the axial position of the 10 percent of the initial blade geometry, the load of the given leading edge point and the load of the given trailing edge point are used as the construction base points, the target loads at each axial position of each design blade height section selected in the step 1 are constructed by adopting a spline function, after the target loads are obtained, the integral of the design target load distribution along the axial direction is calculated by adopting a complex trapezoidal numerical integration method, and compared with the integral of the initial blade geometry load distribution along the axial direction, if the integral of the design target load distribution is greater than the integral of the initial blade geometry load distribution along the axial direction, the load numerical values of each point on the design target load distribution are reduced, until the designed target load integral is equal to the initial blade geometric load distribution along the axial integral; if the designed target load distribution integral is smaller than the axial integral of the initial blade geometric load distribution, amplifying the load numerical values of all points on the designed target load distribution until the designed target load integral is equal to the axial integral of the initial blade geometric load distribution, ensuring that the swirl angle of the stator outlet is kept unchanged by the means of adjusting the size of the designed target load integral, calculating to obtain the virtual displacement of the mean camber line of each designed section by adopting a formula (2) after the adjusted target load distribution is obtained, superposing the virtual displacement of the modified mean camber line obtained by calculation on the basis of the initial mean camber line coordinate of each designed section of the blade to obtain the updated spatial position coordinate of the mean camber line, superposing the thickness distribution of the designed section of the static blade on the mean camber line to obtain the updated blade profile of the designed section of the stator, and finishing the geometric modification of each designed section of the stator;
and step 3: for the rotor, according to the result obtained by numerical simulation in the step (1), ensuring that the pressure ratios at the positions of 0%, 70% and 100% of the blade heights are unchanged, adjusting the pressure ratio obtained by numerical simulation of 10% of the design section to be equal to the pressure ratio of 70% of the design section, then adopting piecewise linear interpolation to construct curve distribution of the design pressure ratios of the movable blade according to the pressure ratios at the positions of 0%, 10%, 70% and 100% of the blade heights, obtaining the design pressure ratios of all the design sections, and calculating the arithmetic mean value of the design pressure ratios of all the design sections; obtaining various flow field parameters of a flow field in the initial blade by adopting a numerical simulation method in the step 1, extracting an arithmetic mean value of each designed section pressure ratio in an initial blade geometric simulation result, comparing the arithmetic mean value with a constructed designed pressure ratio arithmetic mean value, and if the designed pressure ratio arithmetic mean value is larger than the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation, reducing the designed pressure ratio numerical value of each designed section until the designed pressure ratio arithmetic mean value is equal to the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation; if the design pressure ratio arithmetic mean value is smaller than the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation, amplifying the design pressure ratio numerical value of each design section until the design pressure ratio arithmetic mean value is equal to the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation, adopting the means for adjusting the design pressure ratio distribution to ensure that the pressure ratio of the compressor is unchanged before and after optimization, and after the design pressure ratio distribution of the movable blade is adjusted, calculating according to a formula (3) to obtain the target load distribution of the design section of the movable blade:
in the formula,. DELTA.pspAs a blade surface targetLoad, G is bucket flow, CpIs the specific heat capacity of air at constant pressure, T1 *Is the total temperature of the inlet of the movable blade, omega is the rotating angular velocity of the movable blade, eta*For adiabatic efficiency of the moving blades, Δ piFor actual loading of the bucket surface, AθiIs the tangential projection area of the camber line of the moving blade, picsp *Designing pressure ratio, pi, for moving bladesc *Taking the actual pressure ratio of the movable blade, wherein k is a specific heat ratio constant and is 1.4; LE (leading edge) and TE (trailing edge) represent the leading and trailing edges of the blade, riThe height coordinate of the design section in the spanwise direction;
obtaining target load distribution of each design section of the movable blade according to the formula (3), then obtaining arc virtual displacement in each design section of the movable blade according to the formula (2), wherein the method is the same as the method for obtaining the final blade profile of the fixed blade in the step (2), superposing the arc virtual displacement on the basis of the original arc space position coordinate of each design section of the movable blade, updating to obtain the arc space position coordinate of the modified movable blade, and then superposing the thickness distribution of the design section of the movable blade on the updated middle arc of the movable blade to obtain the updated design section blade profile of the movable blade, thereby completing the geometric modification of each design section of the movable blade;
and 4, step 4: and (3) giving outlet flow boundary conditions to ensure that the flow is unchanged before and after optimization, wherein the outlet flow boundary conditions are given as follows:
from the equation (4), the flow rate m is actually calculatedactualAnd specifying a design flow mimposedAt an initial back pressure pb oldOn the basis of the pressure difference, automatically completing the outlet back pressure pb newFinally meeting the flow design requirement, wherein omega is an adjusting relaxation factor;
according to the four steps, the pneumatic matching modification of the static blade and the movable blade is respectively completed, namely the purpose of finally completing the matching modification design of the integral interstage of the compressor is achieved.
The invention has the advantages that by adopting the technical scheme of the full three-dimensional inverse method design for the stator swirl angle and the rotor pressure ratio, quantitative design can be simultaneously completed for the distribution of the stator outlet swirl angle and the distribution of the rotor pressure ratio of the axial compressor in a full three-dimensional environment, so that modification can be simultaneously completed for the rotor and the stator of the axial compressor, and the limitation that the traditional axial compressor pneumatic matching modification technology can not simultaneously perform matching modification on the moving blade and the static blade is broken through. Meanwhile, the invention provides a quantitative construction method for the distribution of the moving blade pressure ratio and the static blade surface aerodynamic load distribution of the axial flow compressor, thereby obtaining a relatively ideal aerodynamic matching effect. By adopting the technical scheme of the invention to carry out interstage pneumatic matching on the NASA Stage 37, the adiabatic efficiency of the design point of the single-Stage compressor is improved by about 0.37% under the condition of ensuring that other design results of the single-Stage compressor are not changed.
Drawings
FIG. 1 is a flow chart of the aerodynamic matching of an axial compressor.
FIG. 2 is a graph comparing pressure ratio distributions.
Fig. 3 is a comparison view of respective sectional load distributions, in which fig. 3(a) is a comparison view of 0% sectional load distribution, fig. 3(b) is a comparison view of 10% sectional load distribution, fig. 3(c) is a comparison view of 70% sectional load distribution, and fig. 3(d) is a comparison view of 100% sectional load distribution.
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
Step 1: given the spatial geometric configuration coordinates of the blades of the full three-dimensional axial flow compressor, called as initial blade geometry, giving the total inlet temperature T0, total inlet pressure P0, inlet airflow angle alpha and outlet back pressure P of the blades of the full three-dimensional axial flow compressor, for the given blade geometry of the axial flow compressor, numerically solving a Navier-Stokes equation (RANS) method for Reynolds time average, adopting a JST format based on the center of a grid body for spatial dispersion, adopting a mixed display Rugge-Kutta time propulsion format for time propulsion, adopting a B-L algebraic turbulence model for the turbulence model, carrying out numerical simulation on a full three-dimensional viscous internal flow field to obtain the numerical simulation result of the geometric flow field of the initial blade, respectively selecting four spatial spanwise positions of which the ratios of the spanwise height of the blade height to the blade height of 0%, 10%, 70% and 100% as design blade height sections for a rotor and a stator along the spatial spanwise positions, and on each design blade height section, equally dividing the blade into 40-50 equal parts along the axial position, and respectively calculating the blade profile thickness distribution delta on four design sections of the rotor and the stator, wherein the formula (1) is as follows:
δ＝|P+-P-| (1)
wherein, P+Is a space coordinate of the suction surface of the blade, P-Is the space coordinate of the pressure surface of the blade;
calculating to obtain modified virtual displacement of the camber line of the blade of the design section of the movable blade or the static blade by adopting a formula (2); firstly, for the stator blade, calculating to obtain a virtual displacement v of arc modification in the stator blade by adopting the formula (2)n：
In the formula,. DELTA.pspDesigning a target load, p, for a designer given a blade surface of a blade or a vane at the beginning of the design+Static pressure, p, obtained for numerical simulation of suction surfaces of moving or stationary blades-Static pressure, rho, obtained for numerical simulation of pressure surfaces of blades or vanes+And ρ-Density obtained by numerical simulation of suction and pressure surfaces of moving or stationary blades, respectively, c+And c-Respectively obtaining sound velocity through numerical simulation of a suction surface and a pressure surface of the movable blade or the stationary blade, wherein delta t is a virtual time step, and 1e-5-1e-6 is taken;
step 2: after numerical simulation of the initial geometric internal flow field of the stationary blade is completed, according to the numerical simulation result, design target loads of all design sections of the stationary blade are constructed, and design target loads delta p of the stationary blade are completedspAfter construction, the target load Δ p will be designedspSubstituting the formula (2) into the above formula, and calculating to obtain the virtual displacement of camber line modification in the stator vane, wherein the construction method of the design target load distribution of each design section of the stator vane comprises the following steps:
the design target loads of the leading edge point and the trailing edge point of the given blade are both 0, the load at each position of the initial blade geometry is obtained by adopting a numerical simulation method for solving the RANS equation in the step 1, so that for the four design blade height sections selected in the step 1, the load obtained by numerical simulation at the axial position of the 10 percent of the initial blade geometry, the load of the given leading edge point and the load of the given trailing edge point are used as the construction base points, the target loads at each axial position of each design blade height section selected in the step 1 are constructed by adopting a spline function, after the target loads are obtained, the integral of the design target load distribution along the axial direction is calculated by adopting a complex trapezoidal numerical integration method, and compared with the integral of the initial blade geometry load distribution along the axial direction, if the integral of the design target load distribution is greater than the integral of the initial blade geometry load distribution along the axial direction, the load numerical values of each point on the design target load distribution are reduced, until the designed target load integral is equal to the initial blade geometric load distribution along the axial integral; if the designed target load distribution integral is smaller than the axial integral of the initial blade geometric load distribution, amplifying the load numerical values of all points on the designed target load distribution until the designed target load integral is equal to the axial integral of the initial blade geometric load distribution, ensuring that the swirl angle of the stator outlet is kept unchanged by the means of adjusting the size of the designed target load integral, calculating to obtain the virtual displacement of the mean camber line of each designed section by adopting a formula (2) after the adjusted target load distribution is obtained, superposing the virtual displacement of the modified mean camber line obtained by calculation on the basis of the initial mean camber line coordinate of each designed section of the blade to obtain the updated spatial position coordinate of the mean camber line, superposing the thickness distribution of the designed section of the static blade on the mean camber line to obtain the updated blade profile of the designed section of the stator, and finishing the geometric modification of each designed section of the stator;
and step 3: for the rotor, according to the result obtained by numerical simulation in the step (1), ensuring that the pressure ratios at the positions of 0%, 70% and 100% of the blade heights are unchanged, adjusting the pressure ratio obtained by numerical simulation of 10% of the design section to be equal to the pressure ratio of 70% of the design section, then adopting piecewise linear interpolation to construct curve distribution of the design pressure ratios of the movable blade according to the pressure ratios at the positions of 0%, 10%, 70% and 100% of the blade heights, obtaining the design pressure ratios of all the design sections, and calculating the arithmetic mean value of the design pressure ratios of all the design sections; obtaining various flow field parameters of a flow field in the initial blade by adopting a numerical simulation method in the step 1, extracting an arithmetic mean value of each designed section pressure ratio in an initial blade geometric simulation result, comparing the arithmetic mean value with a constructed designed pressure ratio arithmetic mean value, and if the designed pressure ratio arithmetic mean value is larger than the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation, reducing the designed pressure ratio numerical value of each designed section until the designed pressure ratio arithmetic mean value is equal to the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation; if the design pressure ratio arithmetic mean value is smaller than the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation, amplifying the design pressure ratio numerical value of each design section until the design pressure ratio arithmetic mean value is equal to the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation, adopting the means for adjusting the design pressure ratio distribution to ensure that the pressure ratio of the compressor is unchanged before and after optimization, and after the design pressure ratio distribution of the movable blade is adjusted, calculating according to a formula (3) to obtain the target load distribution of the design section of the movable blade:
in the formula,. DELTA.pspTarget load for blade surface, G bucket flow, CpIs the specific heat capacity of air at constant pressure, T1 *Is the total temperature of the inlet of the movable blade, omega is the rotating angular velocity of the movable blade, eta*For adiabatic efficiency of the moving blades, Δ piFor actual loading of the bucket surface, AθiIs the tangential projection area of the camber line of the moving blade, picsp *Designing pressure ratio, pi, for moving bladesc *Taking the actual pressure ratio of the movable blade, wherein k is a specific heat ratio constant and is 1.4; LE (leading edge) and TE (trailing edge) represent the leading and trailing edges of the blade, riThe height coordinate of the design section in the spanwise direction;
obtaining target load distribution of each design section of the movable blade according to the formula (3), then obtaining arc virtual displacement in each design section of the movable blade according to the formula (2), wherein the method is the same as the method for obtaining the final blade profile of the fixed blade in the step (2), superposing the arc virtual displacement on the basis of the original arc space position coordinate of each design section of the movable blade, updating to obtain the arc space position coordinate of the modified movable blade, and then superposing the thickness distribution of the design section of the movable blade on the updated middle arc of the movable blade to obtain the updated design section blade profile of the movable blade, thereby completing the geometric modification of each design section of the movable blade;
and 4, step 4: and (3) giving outlet flow boundary conditions to ensure that the flow is unchanged before and after optimization, wherein the outlet flow boundary conditions are given as follows:
from the equation (4), the flow rate m is actually calculatedactualAnd specifying a design flow mimposedAt an initial back pressure pb oldOn the basis of the pressure difference, automatically completing the outlet back pressure pb newFinally, the flow design requirement is met, wherein omega is a relaxation factor, and the flow design method takes omega as 0.05.
According to the four steps, the pneumatic matching modification of the static blade and the movable blade is respectively completed, namely the purpose of finally completing the matching modification design of the integral interstage of the compressor is achieved.
The embodiment adopts a matching scheme of simultaneously changing the rotor pressure ratio distribution and the stator surface load distribution to carry out Stage 37 design inching and stator blade exhaust dynamic matching design. Four leaf height positions of 0%, 10%, 70% and 100% are selected as design sections. For the upstream rotor, the pressure ratio distribution was adjusted as shown in fig. 2. FIG. 2 compares the Rotor 37 prototype pressure ratio distribution, the modified target pressure ratio distribution (red circles) and the pressure ratio distribution obtained when the matching design calculations were completed (blue solid lines). And then calculating the target load distribution of the movable blade according to the method.
The load distributions for the four design sections of the stator downstream thereof were constructed according to the method described in the summary of the invention, adjusting the initial load distribution (shown by the grey dashed line) to the target load distribution (shown by the red circle), as shown in fig. 3.
By adopting the method and the process, the full three-dimensional pneumatic matching calculation is carried out, and the pneumatic matching optimization design of Stage 37 is completed. The design results shown in table 1 were obtained. It can be seen that the pressure ratio and the flow rate of the designed point of the compressor are almost unchanged, but the adiabatic efficiency of the designed point is improved by 0.37%.
TABLE 1 Stage 37 design Point parameter comparison
Claims (1)
1. The full three-dimensional interstage pneumatic matching optimization method of the axial flow compressor is characterized by comprising the following steps:
step 1: given the spatial geometric configuration coordinates of the blades of the full three-dimensional axial flow compressor, called as initial blade geometry, giving the total inlet temperature T0, total inlet pressure P0, inlet airflow angle alpha and outlet back pressure P of the blade, for the given axial flow compressor blade geometry, numerically solving a Navier-Stokes equation (RANS) method for Reynolds time, adopting a JST format based on the center of a grid body for spatial dispersion, adopting a mixed display Rugge-Kutta time propulsion format for time propulsion, adopting a B-L algebraic turbulence model for a turbulence model, carrying out numerical simulation on a full three-dimensional viscous internal flow field to obtain the numerical simulation result of the geometric flow field of the initial blade, selecting four spatial spanwise positions of which the ratios of the spanwise height to the height of the blades are 0%, 10%, 70% and 100% respectively as design blade height sections for a rotor along a spatial spanwise position, selecting the spanwise height to the height of the blades and the height of the blades of the stator are 0% respectively, the four space spread positions of 10%, 70% and 100% are taken as design blade height sections, on each design blade height section, the blade is equally divided into 40-50 equal parts along the axial position, and for the rotor and the stator, the blade profile thickness distribution delta on the four design sections is respectively calculated, as shown in formula (1):
δ＝|P+-P-| (1)
wherein, P+Is a space coordinate of the suction surface of the blade, P-Is the space coordinate of the pressure surface of the blade;
calculating to obtain modified virtual displacement of the camber line of the blade of the design section of the movable blade or the static blade by adopting a formula (2); firstly, for the stator blade, calculating to obtain a virtual displacement v of arc modification in the stator blade by adopting the formula (2)n：
In the formula,. DELTA.pspDesigning a target load, p, for a designer given a blade surface of a blade or a vane at the beginning of the design+Static pressure, p, obtained for numerical simulation of suction surfaces of moving or stationary blades-Static pressure, rho, obtained for numerical simulation of pressure surfaces of blades or vanes+And ρ-Density obtained by numerical simulation of suction and pressure surfaces of moving or stationary blades, respectively, c+And c-Respectively obtaining sound velocity through numerical simulation of suction and pressure surfaces of the movable blade or the stationary blade, taking 10 as delta t as a virtual time step-6 To 10-5 ；
Step 2: after numerical simulation of the initial geometric internal flow field of the stationary blade is completed, according to the numerical simulation result, design target loads of all design sections of the stationary blade are constructed, and design target loads delta p of the stationary blade are completedspAfter construction, the target load Δ p will be designedspSubstituting the formula (2) into the above formula, and calculating to obtain the virtual displacement of camber line modification in the stator vane, wherein the construction method of the design target load distribution of each design section of the stator vane comprises the following steps:
the design target loads of the leading edge point and the trailing edge point of the given blade are both 0, the load at each position of the initial blade geometry is obtained by adopting a numerical simulation method for solving the RANS equation in the step 1, so that for the four design blade height sections selected in the step 1, the load obtained by numerical simulation at the axial position of the 10 percent of the initial blade geometry, the load of the given leading edge point and the load of the given trailing edge point are used as the construction base points, the target loads at each axial position of each design blade height section selected in the step 1 are constructed by adopting a spline function, after the target loads are obtained, the integral of the design target load distribution along the axial direction is calculated by adopting a complex trapezoidal numerical integration method, and compared with the integral of the initial blade geometry load distribution along the axial direction, if the integral of the design target load distribution is greater than the integral of the initial blade geometry load distribution along the axial direction, the load numerical values of each point on the design target load distribution are reduced, until the designed target load integral is equal to the initial blade geometric load distribution along the axial integral; if the designed target load distribution integral is smaller than the axial integral of the initial blade geometric load distribution, amplifying the load numerical values of all points on the designed target load distribution until the designed target load integral is equal to the axial integral of the initial blade geometric load distribution, ensuring that the swirl angle of the stator outlet is kept unchanged by the means of adjusting the size of the designed target load integral, calculating to obtain the virtual displacement of the mean camber line of each designed section by adopting a formula (2) after the adjusted target load distribution is obtained, superposing the virtual displacement of the modified mean camber line obtained by calculation on the basis of the initial mean camber line coordinate of each designed section of the blade to obtain the updated spatial position coordinate of the mean camber line, superposing the thickness distribution of the designed section of the static blade on the mean camber line to obtain the updated blade profile of the designed section of the stator, and finishing the geometric modification of each designed section of the stator;
and step 3: for the rotor, according to the result obtained by numerical simulation in the step (1), ensuring that the pressure ratios at the positions of 0%, 70% and 100% of the blade heights are unchanged, adjusting the pressure ratio obtained by numerical simulation of 10% of the design section to be equal to the pressure ratio of 70% of the design section, then adopting piecewise linear interpolation to construct curve distribution of the design pressure ratios of the movable blade according to the pressure ratios at the positions of 0%, 10%, 70% and 100% of the blade heights, obtaining the design pressure ratios of all the design sections, and calculating the arithmetic mean value of the design pressure ratios of all the design sections; obtaining various flow field parameters of a flow field in the initial blade by adopting a numerical simulation method in the step 1, extracting an arithmetic mean value of each designed section pressure ratio in an initial blade geometric simulation result, comparing the arithmetic mean value with a constructed designed pressure ratio arithmetic mean value, and if the designed pressure ratio arithmetic mean value is larger than the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation, reducing the designed pressure ratio numerical value of each designed section until the designed pressure ratio arithmetic mean value is equal to the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation; if the design pressure ratio arithmetic mean value is smaller than the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation, amplifying the design pressure ratio numerical value of each design section until the design pressure ratio arithmetic mean value is equal to the pressure ratio arithmetic mean value obtained by the initial blade geometric numerical simulation, adopting the means for adjusting the design pressure ratio distribution to ensure that the pressure ratio of the compressor is unchanged before and after optimization, and after the design pressure ratio distribution of the movable blade is adjusted, calculating according to a formula (3) to obtain the target load distribution of the design section of the movable blade:
in the formula,. DELTA.pspTarget load for blade surface, G bucket flow, CpIs the specific heat capacity of air at constant pressure, T1 *Is the total temperature of the inlet of the movable blade, omega is the rotating angular velocity of the movable blade, eta*For adiabatic efficiency of the moving blades, Δ piFor actual loading of the bucket surface, AθiIs the tangential projection area of the camber line of the moving blade, picsp *Designing pressure ratio, pi, for moving bladesc *Taking the actual pressure ratio of the movable blade, wherein k is a specific heat ratio constant and is 1.4; LE and TE represent the leading and trailing edges of the blade, riThe height coordinate of the design section in the spanwise direction;
obtaining target load distribution of each design section of the movable blade according to the formula (3), then obtaining arc virtual displacement in each design section of the movable blade according to the formula (2), wherein the method is the same as the method for obtaining the final blade profile of the fixed blade in the step (2), superposing the arc virtual displacement on the basis of the original arc space position coordinate of each design section of the movable blade, updating to obtain the arc space position coordinate of the modified movable blade, and then superposing the thickness distribution of the design section of the movable blade on the updated middle arc of the movable blade to obtain the updated design section blade profile of the movable blade, thereby completing the geometric modification of each design section of the movable blade;
and 4, step 4: and (3) giving outlet flow boundary conditions to ensure that the flow is unchanged before and after optimization, wherein the outlet flow boundary conditions are given as follows:
from the equation (4), the flow rate m is actually calculatedactualAnd specifying a design flow mimposedAt an initial back pressure pb oldOn the basis of the pressure difference, automatically completing the outlet back pressure pb newTo finally meet the flowDesigning requirement, wherein eta is a regulation relaxation factor;
according to the four steps, the pneumatic matching modification of the static blade and the movable blade is respectively completed, namely the purpose of finally completing the matching modification design of the integral interstage of the compressor is achieved.
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| CN111259559B (en) * | 2020-02-02 | 2023-03-24 | 上海交通大学 | Flow control method for reducing loss by cantilever stator blade front loading design |
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| CN112287580B (en) * | 2020-10-27 | 2022-11-29 | 中国船舶重工集团公司第七0三研究所 | Axial flow compressor surge boundary calculation method based on full three-dimensional numerical simulation |
| CN112685968B (en) * | 2020-12-22 | 2021-12-17 | 中国船舶重工集团公司第七0三研究所 | Axial flow compressor pneumatic design method based on space load customization thought |
| CN112861321B (en) * | 2021-01-14 | 2022-10-18 | 大连海事大学 | A method for end wall modeling of an axial flow compressor with tandem stator vanes |
| CN112711923B (en) * | 2021-03-26 | 2021-07-27 | 中国航发上海商用航空发动机制造有限责任公司 | Pneumatic matching design method for multistage gas compressor |
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