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CN113312706A - Turbine blade row interference single-tone noise quasi-three-dimensional linear calculation method - Google Patents

Turbine blade row interference single-tone noise quasi-three-dimensional linear calculation method Download PDF

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CN113312706A
CN113312706A CN202110670868.2A CN202110670868A CN113312706A CN 113312706 A CN113312706 A CN 113312706A CN 202110670868 A CN202110670868 A CN 202110670868A CN 113312706 A CN113312706 A CN 113312706A
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向康深
陈伟杰
陶孟尧
同航
乔渭阳
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Northwestern Polytechnical University
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Abstract

The invention relates to a turbine blade row interference single-tone noise quasi-three-dimensional linear calculation method, belonging to the field of impeller mechanical aerodynamic acoustics; firstly, acquiring inlet and outlet pneumatic parameters and geometric parameters of cross sections at N different spanwise heights based on a pneumatic design result of a turbine through-flow stage; then, carrying out 'segmentation and linearization' treatment on the sections at different spanwise heights to obtain a segment I and a segment II which are axially divided by each section; then, establishing an upstream blade wake model subjected to coefficient correction, namely wake speed loss distribution; and finally, calculating the 'cut-off' mode and the corresponding acoustic power of the turbine blade row single-tone noise under different harmonic frequencies through Hanson, Tylor and Sofrin theories, and superposing all the mode acoustic powers under the frequency to obtain the total acoustic power corresponding to the frequency. The calculation method is based on the through-flow aerodynamic design result, and the acoustic effect under the design working condition can be effectively evaluated without knowing the three-dimensional detailed aerodynamic parameters and geometric parameters of the turbine blade.

Description

Turbine blade row interference single-tone noise quasi-three-dimensional linear calculation method
Technical Field
The invention belongs to the field of impeller machinery aerodynamic acoustics, and particularly relates to a turbine blade row interference single-tone noise quasi-three-dimensional linear calculation method.
Background
In the field of aircraft engines, with the increasing bypass ratio, low-pressure turbines are becoming one of the important noise sources for aircraft engines. Since the turbine noise prediction capability is insufficient due to the fact that the research on the turbine noise is insufficient for a long time, development of a corresponding turbine noise prediction model and a corresponding calculation method are urgently needed.
To accommodate the design goals of new generation engines of high efficiency and low noise, the predecessors in the field propose an integrated design concept of low pressure turbine aerodynamics/acoustics based on the traditional turbine design flow, i.e. coupling the acoustic design to the aerodynamic design process. Therefore, in order to meet the requirements of integrated aerodynamic-acoustic design of the turbine, corresponding acoustic evaluation means need to be developed at each stage of the aerodynamic design of the turbine, and the invention is a turbine blade row interference single tone noise calculation method suitable for the stage of through-flow aerodynamic design.
Because the blade row interference noise generation mechanism of the impeller machinery is the same, the blade row interference single-tone noise calculation model suitable for the fan/compressor can be considered to be applied to the turbine, but the turbine blade is typically characterized by a large turning angle relative to the fan/compressor blade. Therefore, the model must take the large turning angle characteristic of the turbine into consideration, so that the model is assumed to be more fit to the real geometry of the turbine.
In the prior art, an axial flow turbine fine acoustic experimental device and an axial flow turbine fine acoustic experimental method (with a patent number of CN112268708A), a low-pressure turbine noise experimental method and an improved method thereof (with a patent number of CN108760329A), which mainly take a turbine aerodynamic noise experimental device and an experimental method, are mainly focused on solving the problems existing in a real turbine acoustic experimental method, and have no specific relation with the content of the invention. The invention provides a turbine blade row interference single tone noise calculation method aiming at a turbine through-flow aerodynamic design result, namely under the condition that three-dimensional detailed design parameters (aerodynamic parameters and geometric parameters) of turbine blades are unknown. Nothing in the patent application is found to be relevant for the present invention.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to make up for the defect of the noise prediction capability of the turbine, the invention provides a turbine blade row interference single-tone noise quasi-three-dimensional linear calculation method. The turbine blade row is taken as an object, based on a Hanson two-dimensional leaf-grid single-tone noise prediction model, a Tylor and Sofrin pipeline acoustic modal propagation and cutoff theory and a Goldsterin pipeline acoustic theory, aiming at the characteristics of large turning angles of blades, a segmented linearization idea and a correction wake model suitable for the characteristics of turbine wakes are provided, and simultaneously a strip theory is introduced to obtain a turbine blade row single-tone noise quasi-three-dimensional linearization calculation method, thereby laying a certain foundation for developing the aerodynamic-acoustic integrated design of an aero-engine turbine.
The technical scheme of the invention is as follows: a turbine blade row interference single-tone noise quasi-three-dimensional linear calculation method is characterized by comprising the following specific steps:
step 1: acquiring inlet and outlet pneumatic parameters and geometric parameters of cross sections at N different spanwise heights based on a pneumatic design result of a turbine through-flow stage, wherein the number of N is based on the pneumatic design result;
step 2: performing 'segmentation linearization' treatment on the sections at different spanwise heights to obtain a segment I and a segment II which are divided by the sections along the axial direction;
and step 3: establishing an upstream blade wake model subjected to coefficient correction, namely wake speed loss distribution; the wake velocity loss distribution satisfies the gaussian distribution:
Figure BDA0003116081450000021
wherein, wυAmount of velocity loss, wcThe maximum amount of speed loss is the maximum amount of speed loss,
Figure BDA0003116081450000022
is a coordinate perpendicular to the flow direction of the incoming wake, and Y is the maximum wake width;
the intensity of the upstream wake changes obviously when flowing in the real blade channel, so that corresponding wake velocity loss distribution needs to be provided for the segments I and II, namely for wcAnd correcting the distribution and the Y distribution:
and 4, step 4: based on a Hanson turbine single-tone noise prediction model, combining the correction trail model obtained in the step 3, taking the parameters obtained in the step 1 as input, respectively calculating the unsteady pneumatic load of each segment of each spanwise section blade, and then combining the pneumatic loads on two-dimensional blade grids with different spanwise heights to serve as the unsteady pneumatic load force distribution of the whole quasi-three-dimensional blade surface;
and 5: and (4) calculating the 'cut-off' mode and the corresponding acoustic power of the single-tone noise of the turbine blade row under different harmonic frequencies based on the unsteady aerodynamic load force distribution of the quasi-three-dimensional blade surface obtained in the step (4) by combining Tylor and Sofrin pipeline acoustic mode propagation and cut-off theory and Goldsterin pipeline acoustic theory, and superposing all the mode acoustic powers under the frequencies to obtain the total acoustic power corresponding to the frequencies.
The further technical scheme of the invention is as follows: the number N of the sections in the step 1 and the geometric parameters and the pneumatic parameters of all the sections are from through-flow design results;
the further technical scheme of the invention is as follows: the method for segmenting and linearizing the line in the step 2 comprises the following steps:
firstly, determining five geometric parameters of each section through a turbine through-flow aerodynamic design, wherein a leading edge point is an A point, a trailing edge point is a C point, and an air inlet angle is theta1The exit angle is theta2The axial chord length of the blade is C;
then A, C, theta1And theta2Jointly determining the point of inflection B, C1And C2Respectively the axial chord lengths of the AB section and the BC section; dividing each section into an AB section and a BC section along the axial direction to finish the segmentation;
and finally, performing linearization assumption on the AB section and the BC section to finish linearization.
The further technical scheme of the invention is as follows: in step 3, the modified trail models corresponding to the segment I and the segment II are respectively:
I：
Figure BDA0003116081450000031
II：
Figure BDA0003116081450000032
in the formula, CDIn order to be a coefficient of resistance,
Figure BDA0003116081450000033
are relative coordinates along the chord of the upstream blade.
The further technical scheme of the invention is as follows: in step 4, the relationship between the upstream wake induced wash-up speed on the downstream blade surface and the unsteady aerodynamic load on the blade surface follows the kernel function in the Hanson model, as shown in the following formula:
Figure BDA0003116081450000034
in the formula, KSS, KRS, KSR and KRR are respectively the influence coefficient of the upstream stator blade load on the blade load, the influence coefficient of the downstream rotor blade load on the upstream stator blade load, the influence coefficient of the upstream stator blade load on the downstream rotor blade load and the influence of the downstream rotor blade load on the blade load; LS and LR represent aerodynamic load force distribution of stator and rotor blade surfaces, respectively; WS and WR represent the wash-up velocity profiles of the stator blade surface and the rotor blade surface, respectively.
The further technical scheme of the invention is as follows: in the step 5, combining the Tylor and Sofrin pipeline acoustic mode propagation and cutoff theory and the Goldstein single-tone noise pipeline acoustic mode theory, calculating the acoustic power of each cut-off mode of the turbine blade row single-tone noise under different harmonic frequencies, and superposing all the cut-off modes to obtain the total acoustic power under the frequency.
Advantageous effects
The invention has the beneficial effects that:
1. the calculation method is based on the through-flow aerodynamic design result, and the acoustic effect under the design working condition can be effectively evaluated without knowing the three-dimensional detailed aerodynamic parameters and geometric parameters of the turbine blade;
2. the 'segmentation linearization' theory proposed by the calculation method is proposed aiming at the geometric characteristics of the large turning angle of the turbine blade. Unlike the linear assumption of a fan/compressor, in principle, "piecewise linear" is closer to the true geometry of the turbine blades. This is one of the most important ideas of the present invention.
3. The correction trail model provided by the calculation method is a result obtained by carrying out numerical model fitting average on a plurality of real turbine cases. The significance of the correction is that compared with the original wake velocity loss distribution in the Hanson two-dimensional leaf-grid model, the width of the wake of the turbine blade and the maximum loss depth of the wake are obviously changed due to the large radius of the trailing edge of the turbine blade and the accelerated flow of the air flow, so that the coefficient correction needs to be carried out on the wake model in order to enhance the applicability of the model to the turbine.
4. The Goldstein pipeline acoustic mode theory introduced by the calculation method is widely applied to the field of turbine aerodynamic acoustic research, and takes important pipeline effect inside an aircraft engine turbine into consideration, namely, under the condition of pipeline boundary, acoustic waves can only be transmitted in a pipeline in a specific 'cut-through' mode.
Drawings
FIG. 1: a flow chart of a turbine blade row interference single tone noise quasi-three-dimensional linear computing method;
FIG. 2: turbine blade "banding" schematic;
FIG. 3: a section 'segmented line' schematic diagram of the turbine blade;
FIG. 4: the turbine blade row is a 'piecewise linear' wake interference diagram;
FIG. 5: is a basic parameter table 1 of the turbine experiment table in the specific embodiment of the invention;
FIG. 6: is a geometric parameter table 2 obtained after the through-flow pneumatic design of the turbine in the specific embodiment of the invention is completed;
FIG. 7: in the specific embodiment of the invention, taking a turbine test bed of an aeromechanics and aeroacoustics laboratory of northwest industrial university as an example, the through-flow pneumatic design result is taken as an input calculation result table 3;
FIG. 8: the method is a comparison schematic diagram of the calculation results under different blade row gaps.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
Referring to fig. 1 to 5, the technical solution proposed by the present invention is: based on a Hanson two-dimensional leaf-grating single-tone noise prediction model, a Tylor and Sofrin pipeline acoustic modal propagation and cutoff theory and a Goldsterin pipeline acoustic theory, aiming at the characteristics of a large turning angle of a blade, a segmentation and linearization idea is provided, a correction wake model suitable for the characteristics of a turbine wake is provided, a strip theory is introduced, the two-dimensional leaf-grating theory is developed to a quasi-three-dimensional stage, and the quasi-three-dimensional linearization calculation method of the single-tone noise of the turbine blade row is obtained, wherein the main calculation process is shown in figure 1, and the method mainly comprises the following steps in detail:
1. and acquiring inlet and outlet pneumatic parameters and geometric parameters of the cross sections at N different spanwise heights based on the turbine through-flow pneumatic design result. For the sake of illustration, this time taking the turbine test bench of the aerodynamic and aeroacoustic laboratory of northwest university as an example, table 1 shows the basic parameters of the turbine test bench, and the geometric parameters obtained after the through-flow aerodynamic design of the turbine is completed are shown in table 2. In the table: let-angle and outlet-angle are defined as the angle between the direction of the airflow and the axis, and turning angle is defined as the difference between the first two angles. In addition, the total pressure of the stator inlet is 116.52375kpa, the static pressure of the rotor outlet is 106.2748kpa, and the inlet mach number is 0.12.
2. The turbine blade sections of different spanwise heights are "piecewise linear" as shown in FIG. 3, for example, for a certain radius section. In the figure: point A is the leading edge point, point C is the trailing edge point, theta1Is the inlet angle, theta2And C is the axial chord length of the blade. After the turbine through-flow pneumatic design is completed, the design method can be usedFive pieces of parameter information of the respective sections are determined. Point B is a blade section inflection point, C1And C2The axial chord lengths of the AB section and the BC section respectively. These three parameters may be determined from the first five parameters. The 'segmentation' is to divide each section into an AB section and a BC section along the axial direction; the "linearization" is to make the AB segment and BC segment with a certain thickness undergo the linearization assumption respectively to obtain I and II.
3. For the blades in a certain stage of turbine blade row and downstream, a coefficient-corrected upstream blade wake model, namely a wake velocity loss distribution, applicable to I and II is respectively provided.
The wake velocity loss distribution satisfies the gaussian distribution:
Figure BDA0003116081450000061
wherein wυAmount of velocity loss, wcThe maximum amount of speed loss is the maximum amount of speed loss,
Figure BDA0003116081450000062
is the coordinate of the vertical incoming flow wake direction, and Y is the maximum wake width. The large turning angle of the turbine blade results in the difference in aerodynamic loads generated by the upstream wake on the section I and the section II of the blade. Thus, the present patent proposes modified w for segment I and segment II, respectivelycDistribution and Y distribution, the interference mechanism of which is shown in fig. 4.
I：
Figure BDA0003116081450000063
II：
Figure BDA0003116081450000064
4. Based on a Hanson turbine single-tone noise prediction model, combining with the correction trail model provided in the step 3, respectively calculating unsteady aerodynamic loads of I and II of each extended section, and then combining the aerodynamic loads of I and II on two-dimensional spangles with different extended sections, so as to obtain unsteady aerodynamic load force distribution of the whole quasi-three-dimensional blade surface. Wherein the relationship between the upstream wake induced wash-up velocity at the downstream blade surface and the unsteady aerodynamic loading of the blade surface follows the kernel function in Hanson's model as follows:
Figure BDA0003116081450000071
the details of the part are shown in Hanson two-dimensional leaf-grid monophonic noise prediction model, and are not described in detail here.
5. After aerodynamic force load distribution on the surface of the blade is obtained, the Tylor and Sofrin pipeline acoustic mode propagation and cut-off theory and the Goldstein single-tone noise pipeline acoustic mode theory are combined, acoustic power of cut-off modes under different harmonic frequencies is calculated, and the total acoustic power under the frequencies can be obtained by superposing the acoustic power of all the cut-off modes. The basic equations for Tylor and Sofrin pipeline acoustic mode propagation with the cutoff theory and Goldsterin single tone noise pipeline acoustic mode theory are given below. Taking a turbine test bed of an aeromechanics and aeroacoustics laboratory of northwest university as an example, the through-flow aerodynamic design result is taken as an input, and the calculation result is shown in table 3. Notably, under this design condition, the 1BPF is "cut off" in the pipe. In the table, BPF represents blade passing frequency, m represents circumferential mode, n represents radial mode, Real Amplitude and Imag Amplitude represent Real part and imaginary part of Amplitude of each mode respectively, and PWL is total sound power at the frequency. To further illustrate that the calculation method can evaluate the noise variation caused by the design details, fig. 5 shows the comparison of the calculation results under different blade row clearances. The results show that the calculation method can predict the noise change caused by different geometric design changes.
Tyler and Sofrin give the axial wavenumber form of the interfering rotational pressure modes:
Figure BDA0003116081450000072
definition of
Figure BDA0003116081450000073
Indicating the critical circumferential Mach number, Tyler and Sofrin indicate that when MmIs less than
Figure BDA0003116081450000074
When the sound wave is cut off, the amplitude can be quickly attenuated along the axial direction, and MmIs greater than
Figure BDA0003116081450000075
When the acoustic wave exhibits a propagation characteristic. More applied to engineering is the following simple method:
Figure BDA0003116081450000076
in the formula, p represents the number of spatial harmonics caused by a stator or distortion, and the "cutoff" condition is satisfied when the above formula is satisfied.
Goldsterin single-tone noise pipeline acoustic mode theory gives (m, n) -order mode amplitude of a certain blade at a certain frequency, and the expression is as follows:
Figure BDA0003116081450000081
where Ω is the rotational frequency of the following blade row, and if the following blade row is a stator, Ω is 0. The (m, n) modal amplitude at this frequency for V blades is then:
Figure BDA0003116081450000082
after the modal amplitude is calculated, the acoustic power corresponding to the modal can be calculated:
Figure BDA0003116081450000083
in the formula, the symbols are. + -. and
Figure BDA0003116081450000084
the upper sign indicates counter-current (negative x-direction) propagation and the lower sign indicates downstream (positive x-direction) propagation. Superposing all modal acoustic powers at the frequency to calculate the acoustic power corresponding to the frequency:
Figure BDA0003116081450000085
the method is a general calculation formula for calculating the acoustic modal amplitude and the acoustic power level of the pipeline according to the unsteady pressure pulsation of the surface of the blade.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.

Claims (6)

1.一种涡轮叶片排干涉单音噪声准三维线化计算方法，其特征在于具体步骤如下：1. a quasi-three-dimensional linearization calculation method for turbine blade row interference single-tone noise, is characterized in that concrete steps are as follows: 步骤1：基于涡轮通流阶段气动设计结果，得到N个不同展向高度处截面的进出口气动参数和几何参数，N的个数以气动设计结果为准；Step 1: Based on the aerodynamic design results of the turbine through-flow stage, obtain the inlet and outlet aerodynamic parameters and geometric parameters of N sections at different spanwise heights, and the number of N is subject to the aerodynamic design results; 步骤2：对不同展向高度处的截面进行“分段线化”处理，得到各截面沿轴向划分的片段I和片段II；Step 2: Perform "segmental linearization" processing on the sections at different spanwise heights to obtain segment I and segment II divided by each section along the axial direction; 步骤3：建立经过系数修正的上游叶片尾迹模型，即尾迹速度损失分布；尾迹速度损失分布均满足高斯分布：
Figure FDA0003116081440000011
Step 3: Establish a coefficient-corrected upstream blade wake model, that is, the wake velocity loss distribution; the wake velocity loss distributions all satisfy the Gaussian distribution:
Figure FDA0003116081440000011
 其中，wυ为速度损失量，wc为最大速度损失量,
Figure FDA0003116081440000012
为垂直来流尾迹流向的坐标，Y为最大尾迹宽度；Among them, w υ is the speed loss, w c is the maximum speed loss,
Figure FDA0003116081440000012
is the coordinate of the vertical wake flow direction, and Y is the maximum wake width; 上游尾迹强度在真实叶片通道内流动时会发生明显变化，因此针对片段I和片段II需要提出对应的尾迹速度损失分布，即对wc分布和Y分布进行修正：The upstream wake intensity will change significantly when flowing in the real blade channel. Therefore, the corresponding wake velocity loss distribution needs to be proposed for segment I and segment II, that is, the w c distribution and the Y distribution are corrected: 步骤4：基于Hanson叶轮机单音噪声预测模型，结合步骤3得到的修正尾迹模型，以步骤1得到的参数作为输入，分别计算各个展向截面的叶片各片段的非定常气动载荷，然后将不同展向高度的二维叶珊上的气动载荷合并，以此作为整个准三维叶片表面的非定常气动载荷力分布；Step 4: Based on the Hanson turbine single-tone noise prediction model, combined with the modified wake model obtained in step 3, and using the parameters obtained in step 1 as input, calculate the unsteady aerodynamic load of each blade segment of each span-wise section, and then calculate the different The aerodynamic loads on the two-dimensional leaf ridge of spanwise height are combined as the unsteady aerodynamic load force distribution on the entire quasi-three-dimensional blade surface; 步骤5：基于步骤4得到的准三维叶片表面的非定常气动载荷力分布，结合Tylor和Sofrin管道声模态传播与截止理论和Goldsterin管道声学理论，计算不同谐波频率下的涡轮叶片排单音噪声的“截通”模态及对应的声功率，将该频率下所有的模态声功率进行叠加，就可以得到该频率对应的总声功率。Step 5: Based on the unsteady aerodynamic load force distribution of the quasi-3D blade surface obtained in Step 4, combined with the Tylor and Sofrin duct acoustic modal propagation and cutoff theory and Goldsterin duct acoustic theory, calculate the single tone of the turbine blade row at different harmonic frequencies The "cut-off" mode of the noise and the corresponding sound power, and the total sound power corresponding to the frequency can be obtained by superimposing all the modal sound powers at the frequency. 2.根据权利要求1所述涡轮叶片排干涉单音噪声准三维线化计算方法，其特征在于：所述步骤1的截面数N和各个截面的几何参数和气动参数均来自于通流设计结果。2. The quasi-three-dimensional linearization calculation method of the interference single-tone noise of the turbine blade row according to claim 1, is characterized in that: the section number N of the step 1 and the geometrical parameters and aerodynamic parameters of each section all come from the through-flow design result . 3.根据权利要求1所述涡轮叶片排干涉单音噪声准三维线化计算方法，其特征在于：所述步骤2的分段线化的方法为：3. according to the described turbine blade row interference monophonic noise quasi-three-dimensional linearization calculation method of claim 1, it is characterized in that: the method for segmented linearization of described step 2 is: 首先，通过涡轮通流气动设计确定各截面的五个几何参数，其中，前缘点为A点、尾缘点为C点、进气角为θ1、出口角为θ2，叶片轴向弦长为C；Firstly, the five geometric parameters of each section are determined by the turbine through-flow aerodynamic design, among which, the leading edge point is point A, the trailing edge point is point C, the intake angle is θ 1 , the outlet angle is θ 2 , the blade axial chord is length is C; 然后，由A、C、θ1和θ2共同确定分段拐点B，C1和C2分别为AB段和BC段的轴向弦长；将各个截面沿轴向分成AB段和BC段，完成分段；Then, the segmental inflection point B is jointly determined by A, C, θ 1 and θ 2 , C 1 and C 2 are the axial chord lengths of the AB and BC segments respectively; each section is divided into AB segments and BC segments along the axial direction, complete the segment; 最后，将AB段和BC段进行线化假设，完成线化。Finally, the AB segment and the BC segment are assumed to be linearized to complete the linearization. 4.根据权利要求1所述涡轮叶片排干涉单音噪声准三维线化计算方法，其特征在于：所述步骤3中，与片段I和片段II相对应的修正尾迹模型分别是：4. according to the described turbine blade row interference monophonic noise quasi-three-dimensional linearization calculation method of claim 1, it is characterized in that: in described step 3, and the correction wake model corresponding to segment I and segment II are respectively:
Figure FDA0003116081440000021
Figure FDA0003116081440000021
Figure FDA0003116081440000022
Figure FDA0003116081440000022
 式中，CD为阻力系数，
Figure FDA0003116081440000023
为沿上游叶片弦长方向的相对坐标。where CD is the drag coefficient,
Figure FDA0003116081440000023
is the relative coordinate along the chord length of the upstream blade. 5.根据权利要求1所述涡轮叶片排干涉单音噪声准三维线化计算方法，其特征在于：所述步骤4中，上游尾迹在下游叶片表面引起的上洗速度和叶片表面的非定常气动力载荷之间的关系沿用Hanson模型中的核函数，如下式所示：5 . The method for quasi-three-dimensional linearization of single-tone noise of turbine blade row interference according to claim 1 , wherein in the step 4, the upwash velocity caused by the upstream wake on the surface of the downstream blade and the unsteady gas flow on the blade surface. 6 . The relationship between the dynamic loads follows the kernel function in the Hanson model, as shown in the following formula:
Figure FDA0003116081440000024
Figure FDA0003116081440000024
 式中，KSS、KRS、KSR、KRR分别为上游静子叶片载荷对本身的影响系数、下游转子叶片载荷对上游静子叶片载荷的影响系数、上游静子叶片载荷对下游转子叶片载荷的影响系数，下游转子叶片载荷对本身的影响；LS和LR分别代表静子叶片和转子叶片表面的气动载荷力分布；WS和WR分别代表静子叶片表面和转子叶片表面的上洗速度分布。In the formula, KSS, KRS, KSR and KRR are the influence coefficient of the upstream stator blade load on itself, the influence coefficient of the downstream rotor blade load on the upstream stator blade load, the influence coefficient of the upstream stator blade load on the downstream rotor blade load, and the downstream rotor blade load. The influence of blade load on itself; LS and LR represent the aerodynamic load force distribution on the stator blade and rotor blade surface, respectively; WS and WR represent the upwash velocity distribution on the stator blade surface and rotor blade surface, respectively. 6.根据权利要求1所述涡轮叶片排干涉单音噪声准三维线化计算方法，其特征在于：所述步骤5中，结合Tylor和Sofrin管道声模态传播与截止理论和Goldsterin单音噪声管道声模态理论，计算不同谐波频率下的涡轮叶片排单音噪声的各个“截通”模态的声功率，将所有“截通”模态进行叠加即可得到该频率下的总声功率。6. The method for quasi-three-dimensional linearization of turbine blade row interference single-tone noise according to claim 1, characterized in that: in the step 5, in combination with Tylor and Sofrin pipeline acoustic modal propagation and cut-off theory and Goldsterin single-tone noise pipeline Acoustic mode theory, calculate the sound power of each "cut-off" mode of single-tone noise of turbine blades at different harmonic frequencies, and superimpose all "cut-off" modes to obtain the total sound power at this frequency. .
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