CN111144036A - Multi-scale simulation analysis method for propeller noise - Google Patents

Multi-scale simulation analysis method for propeller noise Download PDF

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CN111144036A
CN111144036A CN202010134770.0A CN202010134770A CN111144036A CN 111144036 A CN111144036 A CN 111144036A CN 202010134770 A CN202010134770 A CN 202010134770A CN 111144036 A CN111144036 A CN 111144036A
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曾奇
陈灏
王佳飞
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Shanghai Suochen Information Technology Co ltd
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Abstract

The multi-scale simulation analysis method of the propeller noise comprises the following steps: carrying out dimension analysis, progressive analysis, statistical analysis and correlation analysis on the noise to obtain a noise expression, carrying out Fourier transform on the noise expression and rewriting the noise expression by combining a Green function: and carrying out physical modeling on the propeller noise based on the rewritten noise expression and the physical process of the propeller noise to obtain a modeling model: dividing each single blade of the propeller into n parts along the axial direction or the radial direction, wherein n is initially 1; analyzing each parameter in the modeling model corresponding to each division part, and calculating a far-field noise spectrum function of each division part; calculating a far-field noise spectrum function of a single blade; and calculating an error value between the far-field noise spectrum function of the single blade and the far-field noise spectrum function obtained by the test, if the error value is greater than a set value, re-dividing the blade area for calculation, and otherwise, using the modeling division process as a propeller noise simulation method for the blade configuration and the number of the blades of the propeller.

Description

Multi-scale simulation analysis method for propeller noise
Technical Field
The invention relates to the technical field of noise simulation analysis, in particular to a multi-scale simulation analysis method for propeller noise.
Background
At present, the noise simulation analysis technology mainly adopts two methods of empirical formula and numerical simulation. In particular, in the last decade, domestic popular general commercial acoustic software carries out numerical simulation under the macro scale, and numerical simulation algorithms such as a finite element and boundary element method are adopted for medium and low frequency bands, and a statistical energy method is adopted for medium and high frequency bands. The numerical calculation method adopted by the existing general commercial software can solve the noise simulation problem of a part of component levels, but the noise problem under the micro scale is not considered, and the system level noise simulation analysis facing large-scale and complex equipment is difficult to carry out.
For example, concealment is a key factor for ensuring the battle effectiveness of submarines, and the main factor for destroying the concealment of the submarines is radiation noise from propellers. Traditionally, the noise of the propeller is measured through experiments in China, an empirical formula is used for assistance, and a simulation method can be rarely used for effectively realizing complex noise simulation of the propeller. The traditional propeller noise simulation is mainly carried out through the experience of engineers, the achievement of the project design purpose depends on the richness of the experience of the engineers and the accuracy and the applicability of various empirical formulas.
Disclosure of Invention
Aiming at the problems and the defects in the prior art, the invention provides a multi-scale simulation analysis method suitable for full-frequency-domain multi-scale propeller noise.
The invention solves the technical problems through the following technical scheme:
the invention provides a multi-scale simulation analysis method for propeller noise, which is characterized by comprising the following steps of:
s1, respectively carrying out dimensional analysis, progressive analysis, statistical analysis and correlation analysis on the noise under a specific coordinate system through Ffowcs Williams/Hawking equation to obtain a noise expression:
Figure BDA0002396948520000021
wherein П (x, ω) is noise power spectral density, S (y) is an integral surface, x is a far-field coordinate vector, y is a near-field or sound source coordinate vector, ω is angular frequency, ki is wave number, ni is direction, G0 is Green's function,
Figure BDA0002396948520000022
representing surface power spectral density;
s2, carrying out Fourier transform on the noise expression, and rewriting the noise expression by combining with a Green function to obtain a rewritten noise expression:
Figure BDA0002396948520000023
wherein x is a far-field coordinate vector, y is a near-field or sound source coordinate vector, ω is an angular frequency, ki is a wavenumber, ni is a direction, G0 is a Green's function, l is a sound source reference dimension,
Figure BDA0002396948520000024
representing surface power spectral density;
s3, carrying out physical modeling on the propeller noise based on the rewritten noise expression and the physical process of the propeller noise to obtain a modeling model:
Figure BDA0002396948520000025
s4, for each single blade of the propeller: dividing a single blade into n parts along axial or radial division, wherein the initial value of n is 1;
s5, analyzing the environment medium correlation function in the modeling model corresponding to each divided part of the single blade
Figure BDA0002396948520000031
Mach number correlation function W (M), spherical diffusion effect H (r) r-2Transmitting the amplification effect delta-2Atmospheric absorption effect
Figure BDA0002396948520000032
Directivity function
Figure BDA0002396948520000033
Geometric amplitude function AGFlow amplitude function AFDimension L of sound sourcesBsDoppler shift function fd and spectral function F (M, F)d) Calculating a frequency spectrum function of the far-field noise corresponding to each division part based on a modeling model; based on each divided part pairCalculating the spectrum function of the far-field noise of a single blade according to the spectrum function of the far-field noise;
s6, calculating an error value between the spectrum function of the far-field noise of the single blade in the step S5 and the spectrum function of the far-field noise obtained through the test, if the error value is larger than a set error value, re-dividing the blade area n to be n +1, and executing the steps S5-S6 again, otherwise, taking the modeling division process corresponding to the error value smaller than or equal to the set error value as a propeller noise simulation method of the blade configuration and the blade number of the propeller, and in the future, directly carrying out high-precision noise simulation suitable for the propeller noise with the same/similar blade configuration and the same blade number according to the propeller noise simulation method of the blade configuration and the blade number.
Preferably, the directivity function is calculated using a formula
Figure BDA0002396948520000034
The formula is as follows:
Figure BDA0002396948520000035
wherein Bs is the span length of the sound source, r2ξ, ξ as the squared distance from the sound source to the far-field noise monitor point locationiRepresenting the local field vector and the component coordinates.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows:
the invention provides an effective and accurate propeller noise simulation method, which is used for assisting the design analysis and test manufacture of the acoustic performance of the propeller.
The method can be directly used for design optimization of the ship and naval vessel propeller, and engineers do not rely on manual experience for optimization any more.
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FIG. 1 is a flow chart of a multi-scale simulation analysis method of propeller noise according to a preferred embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
As shown in fig. 1, the present embodiment provides a multi-scale simulation analysis method of propeller noise, which includes the following steps:
step 101, starting from basic theories of pneumatic acoustics and flow acoustics, performing dimensional analysis, progressive analysis, statistical analysis and correlation analysis on noise under a specific coordinate system through an Ffowcs Williams/Hawking equation to obtain a noise expression:
Figure BDA0002396948520000041
wherein, n (x, ω) is noise power spectral density, S (y) is an integral surface, x is a far-field coordinate vector, y is a near-field or sound source coordinate vector, ω is angular frequency, ki is wave number, ni is direction, G0 is Green's function,
Figure BDA0002396948520000042
representing the surface power spectral density.
102, performing Fourier transform on the noise expression, and rewriting the noise expression by combining a Green function to obtain a rewritten noise expression:
Figure BDA0002396948520000051
wherein x is a far-field coordinate vector, y is a near-field or sound source coordinate vector, ω is an angular frequency, ki is a wavenumber, ni is a direction, G0 is a Green's function, l is a sound source reference dimension,
Figure BDA0002396948520000052
representing the surface power spectral density.
The gradient of the green's function in the above equation effectively has only two component directions in a plane perpendicular to the parallel direction because of the invariance of the surface normal in that direction. A form suitable for dimensional analysis is therefore employed here to extract the functionally dependent noise and various parameters between the far fields.
103, carrying out physical modeling on the propeller noise based on the rewritten noise expression and the physical process of the propeller noise to obtain a modeling model:
Figure BDA0002396948520000053
step 104, for each single blade of the propeller: the division in the axial or radial direction divides the individual blade into n sections, n being initially 1.
Step 105, analyzing the environmental medium correlation function in the modeling model corresponding to each divided part of the single blade
Figure BDA0002396948520000054
Mach number correlation function W (M), spherical diffusion effect H (r) r-2Transmitting the amplification effect delta-2Atmospheric absorption effect
Figure BDA0002396948520000055
Directivity function
Figure BDA0002396948520000056
Geometric amplitude function AGFlow amplitude function AFDimension L of sound sourcesBsDoppler shift function fdAnd the spectral function F (M, d)f) Calculating a frequency spectrum function of the far-field noise corresponding to each division part based on a modeling model; and calculating the spectrum function of the far-field noise of the single blade based on the spectrum function of the far-field noise corresponding to each divided part.
The simulation of the noise directivity function has very significant characteristics, i.e. like dipole radiation, the directivity function can be expressed as:
Figure BDA0002396948520000061
in the above formula, D is the directivity function, Bs is the sound source span length, η, η1、η2Is azimuth,. kappa.is constant, ξ is directivity parameter, G0Is a modeling function. Each term can be expressed as an algebraic function or a rational function, so that either direct theoretical integration or numerical integration can be performed. However, the expression of the theoretical integration is too complicated and long, so that the method is simplified, and the main characteristics of directivity are captured through simple analysis and analysis, so that an integration result with a simpler form can be obtained.
Figure BDA0002396948520000062
In the above formula: bs is the sound source span length, r2ξ, ξ as the squared distance from the sound source to the far-field noise monitor point locationiRepresenting the local field vector and the component coordinates.
Step 106, calculating an error value between the spectrum function of the far-field noise of the single blade in the step 105 and the spectrum function of the far-field noise obtained through the test, if the error value is greater than a set error value, re-dividing the blade region n to n +1, and executing the step 105 and 106 again, otherwise, taking the modeling division process corresponding to the error value less than or equal to the set error value as a propeller noise simulation method of the blade configuration and the blade number of the propeller, and directly performing high-precision noise simulation suitable for the propeller noise with the same/similar blade configuration and the same blade number according to the propeller noise simulation method of the blade configuration and the blade number in the future.
For example: firstly, the single blade of the propeller is not divided, the single blade is used as a compact sound source to be processed, based on each parameter in a single blade analysis modeling model, a spectrum function of far-field noise corresponding to the single blade is calculated, an error value between the spectrum function of the far-field noise of the single blade and the spectrum function of the far-field propeller noise obtained through tests is calculated to be large, and if the error value is larger than a set error value, the blade area is divided again.
The method comprises the steps of dividing a single blade into 2 parts along the axial direction or the radial direction, processing each divided part as a compact sound source, analyzing each parameter in a modeling model based on the 1 st part of the single blade, calculating a spectrum function of far-field noise corresponding to the 1 st part, analyzing each parameter in the modeling model based on the 2 nd part of the single blade, calculating a spectrum function of the far-field noise corresponding to the 2 nd part, and calculating a spectrum function of the far-field noise of the single blade based on the spectrum function of the far-field noise corresponding to the 1 st part and the spectrum function of the far-field noise corresponding to the 2 nd part. If the error value between the frequency spectrum function of the far-field noise of the single blade and the frequency spectrum function of the far-field propeller noise obtained by the experiment is smaller than the set error value, the modeling model and the single blade are divided into 2 corresponding flows along the axial direction or the radial direction to be used as a propeller noise simulation method with the blade configuration and the blade number, high-precision noise simulation suitable for the propeller noise with the same/similar blade configuration and the same blade number can be directly carried out in the future according to the propeller noise simulation method of the blade configuration, and subsequent optimization can be carried out at any time.
When a propeller with the same/similar blade configuration and the same number of blades as the propeller of the invention is encountered in the future, the following process can be adopted for noise simulation analysis:
s1, respectively carrying out dimensional analysis, progressive analysis, statistical analysis and correlation analysis on the noise under a specific coordinate system through Ffowcs Williams/Hawking equation to obtain a noise expression:
Figure BDA0002396948520000071
s2, carrying out Fourier transform on the noise expression, and rewriting the noise expression by combining with a Green function to obtain a rewritten noise expression:
Figure BDA0002396948520000072
s3, carrying out physical modeling on the propeller noise based on the rewritten noise expression and the physical process of the propeller noise to obtain a modeling model:
Figure BDA0002396948520000081
s4, for each single blade of the propeller: dividing a single blade into 2 parts along the axial direction or the radial direction;
s5, analyzing the environment medium correlation function in the modeling model corresponding to each divided part of the single blade
Figure BDA0002396948520000082
Mach number correlation function W (M), spherical diffusion effect r-2Transmitting the amplification effect delta-2Atmospheric absorption effect
Figure BDA0002396948520000083
Directivity function
Figure BDA0002396948520000084
Geometric amplitude function AGFlow amplitude function AFDimension L of sound sourcesBsDoppler shift function fdAnd a spectral function F (M, F)d) Calculating a frequency spectrum function of the far-field noise corresponding to each division part based on a modeling model; the spectrum function of the far-field noise of the single blade is calculated based on the spectrum function of the far-field noise corresponding to the first division and the spectrum function of the far-field noise corresponding to the second division.
The invention adopts a simple and effective model to describe the complex physical phenomenon, thereby avoiding the comprehensive solution of the complex physical phenomenon, and the method is effective and practical in engineering. For engineering applications, building simple and efficient models to describe the specific physical mechanisms of interest naturally becomes the best practice in the industry.
Compared with other methods, the method has the first strong term of high precision. The present invention does not attempt to include all physical phenomena but only considers the phenomena related to the generation of noise, and thus there is no problem of incomplete or insufficient models. Also because this method directly models the amount of noise, the magnitude of the degree of calculation is also the magnitude of the amount of noise, and therefore there is no problem of numerical error. The accuracy of the method can generally meet the requirements of engineering design and engineering prediction, including the variation of noise quantity along with design parameters. In some noisy applications, the accuracy can be within the error range of the experimental measurement.
The second strength term is the speed and period of its application and calculation. Establishing the input parameters and other information required is typically on the order of several days from the application cycle point of view. The calculated speed is typically on the order of several minutes for a single operating condition, a single PC application. Therefore, the method is very suitable for engineering application, in particular to multi-working condition and multi-parameter engineering application. This is often required in engineering design and engineering optimization.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.

Claims (2)

1. A multi-scale simulation analysis method for propeller noise is characterized by comprising the following steps:
s1, respectively carrying out dimensional analysis, progressive analysis, statistical analysis and correlation analysis on the noise under a specific coordinate system through Ffowcs Williams/Hawking equation to obtain a noise expression:
Figure FDA0002396948510000011
wherein, Π (x, omega) is noise power spectral density, S (y) is an integral surface, x is a far-field coordinate vector, y is a near-field or sound source coordinate vector, omega is angular frequency, ki is wave number, ni is direction, G0 is a Green function,
Figure FDA0002396948510000012
representing surface power spectral density;
s2, carrying out Fourier transform on the noise expression, and rewriting the noise expression by combining with a Green function to obtain a rewritten noise expression:
Figure FDA0002396948510000013
wherein x is a far-field coordinate vector, y is a near-field or sound source coordinate vector, ω is an angular frequency, ki is a wavenumber, ni is a direction, G0 is a Green's function, l is a sound source reference dimension,
Figure FDA0002396948510000014
representing surface power spectral density;
s3, carrying out physical modeling on the propeller noise based on the rewritten noise expression and the physical process of the propeller noise to obtain a modeling model:
Figure FDA0002396948510000015
s4, for each single blade of the propeller: dividing a single blade into n parts along axial or radial division, wherein the initial value of n is 1;
s5, analyzing the environment medium correlation function in the modeling model corresponding to each divided part of the single blade
Figure FDA0002396948510000021
Mach number correlation function W (M), spherical diffusion effect H (r) r-2Transmitting the amplification effect delta-2Atmospheric absorption effect
Figure FDA0002396948510000022
Directivity function
Figure FDA0002396948510000023
Geometric amplitude function AGFlow amplitude function AFDimension L of sound sourcesBsDoppler shift function fdAnd a spectral function F (M, F)d) Calculating a frequency spectrum function of the far-field noise corresponding to each division part based on a modeling model; calculating a spectrum function of the far-field noise of a single blade based on the spectrum function of the far-field noise corresponding to each divided part;
s6, calculating an error value between the spectrum function of the far-field noise of the single blade in the step S5 and the spectrum function of the far-field noise obtained through the test, if the error value is larger than a set error value, re-dividing the blade area n to be n +1, and executing the steps S5-S6 again, otherwise, taking the modeling division process corresponding to the error value smaller than or equal to the set error value as a propeller noise simulation method of the blade configuration and the blade number of the propeller, and in the future, directly carrying out high-precision noise simulation suitable for the propeller noise with the same/similar blade configuration and the same blade number according to the propeller noise simulation method of the blade configuration and the blade number.
2. The method for multi-scale simulation analysis of propeller noise of claim 1, wherein the directional function is calculated using a formula
Figure FDA0002396948510000024
The formula is as follows:
Figure FDA0002396948510000025
wherein Bs is the span length of the sound source, r2ξ, ξ as the squared distance from the sound source to the far-field noise monitor point locationiRepresenting the local field vector and the component coordinates.
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