CN112257184B - Method for calculating distribution of aerodynamic noise of propeller along surface of machine body - Google Patents

Method for calculating distribution of aerodynamic noise of propeller along surface of machine body Download PDF

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CN112257184B
CN112257184B CN202011192299.7A CN202011192299A CN112257184B CN 112257184 B CN112257184 B CN 112257184B CN 202011192299 A CN202011192299 A CN 202011192299A CN 112257184 B CN112257184 B CN 112257184B
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肖乾
顾金桃
高飞
王美燕
胡陈映
刘成玉
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AVIC First Aircraft Institute
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Abstract

The application belongs to the field of aeroacoustic design, and particularly relates to a method for calculating distribution of aerodynamic noise of a propeller along the surface of a machine body. The method comprises the following steps: constructing a propeller pneumatic noise source model by taking a propeller as a noise source; constructing a finite element model of the propeller, dividing the position of a propeller blade into a rotation domain, and setting other parts into a static domain; constructing a propeller pneumatic model, and acquiring pneumatic data of the surface pulsating pressure and the speed of propeller blades distributed along with time under the cruising state of the airplane; establishing a geometric model of a fuselage, and performing acoustic meshing; and (3) enabling the propeller aerodynamic noise source to be equivalent to a fan sound source, establishing an acoustic model of the propeller and the machine body, and obtaining the noise distribution of the propeller directly radiating to the outer surface of the machine body. The method for accurately estimating the distribution of the aerodynamic noise of the propeller along the surface of the machine body lays a foundation for predicting the noise level in the cabin and improving the comfort of passengers in the cabin.

Description

Method for calculating distribution of aerodynamic noise of propeller along surface of machine body
Technical Field
The application belongs to the field of aeroacoustic design, and particularly relates to a method for calculating distribution of aerodynamic noise of a propeller along the surface of a machine body.
Background
The propeller aircraft is widely applied to the types of branch passenger planes, transport planes, general aircrafts and the like, and has the advantages of low oil consumption, good low-speed performance, high flying efficiency and the like. However, the high noise level of a propeller aircraft has prevented its further development. The noise in the propeller aircraft cabin is mainly divided into two types, one type is that sound sources such as propellers radiate to the surface of the aircraft body through air propagation to cause the aircraft body to vibrate, so that sound energy is propagated into the aircraft cabin; another is that structural vibrations of the wings or other body parts propagate to the fuselage surface, causing the fuselage to vibrate, thereby propagating acoustic energy into the cabin. Therefore, in order to improve the comfort of passengers in the cabin and predict the noise level in the cabin, it is very important to obtain the distribution of the propeller aerodynamic noise along the surface of the fuselage.
For a propeller-driven aircraft, in order to accurately estimate the aerodynamic noise distribution of the propeller along the surface of the aircraft body, a complete machine complete simulation capable of obtaining a relatively accurate calculation result must be established.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a method for calculating distribution of aerodynamic noise of a propeller along a surface of a fuselage, including:
step S1, constructing a propeller pneumatic noise source model by taking a propeller as a noise source;
step S2, constructing a propeller finite element model, dividing the position of a propeller blade into a rotating domain, setting other parts of the propeller blade into a static domain, and forming a cylindrical calculation domain by the rotating domain and the static domain;
s3, constructing a propeller aerodynamic model, performing steady-state calculation of a flow field in a cruising state based on airplane cruising parameters, and calculating a transient result according to the steady-state calculation result of the flow field to obtain aerodynamic data of the surface pulsating pressure and the surface pulsating speed of propeller blades distributed along with time in the cruising state of the airplane;
step S4, establishing a geometric model of the fuselage, and performing acoustic meshing;
and S5, enabling the propeller aerodynamic noise sound source to be equivalent to a fan sound source, establishing a propeller and fuselage acoustic model, taking the aerodynamic data in the step S3 as input, and acquiring the noise distribution of the propeller directly radiating to the outer surface of the fuselage under the cruise state of the airplane.
Preferably, in step S1, when constructing the propeller aerodynamic noise sound source model, each area element of the propeller is used as a single-stage sub sound source, a dipole sound source, and/or a four-stage sub sound source.
Preferably, in step S3, calculating the transient result includes,
step S31, when the residual error of the lift force and the drag force of the whole aircraft is less than 10 -3 When the calculation result is converged, the steady-state calculation result is given;
and step S32, calculating the transient result by taking the steady-state calculation result as an initial solution.
Preferably, in step S4, when the acoustic mesh division is performed, the mesh size a is set to:
Figure BDA0002753107640000021
λ min ＝c 0 /fmax，
wherein, c 0 Is the speed of sound.
Preferably, the step S5 of acquiring the noise distribution directly radiated from the propeller to the outer surface of the fuselage in the cruising state of the aircraft includes: and calculating the aerodynamic noise of the whole propeller based on a boundary element method.
Preferably, in step S2, the cylindrical radius is 10 times the propeller radius and the axial length is 25 times the propeller radius.
Preferably, step S1 is preceded by:
and constructing a full-machine coordinate system, and acquiring parameters for calculating the propeller aerodynamic model in a cruise state.
According to the method, complete simulation of the complete machine capable of obtaining relatively accurate calculation results is established, a set of method for accurately estimating the distribution of the aerodynamic noise of the propeller along the surface of the machine body is provided, and a foundation is laid for predicting the noise level in the cabin and improving the comfort of passengers in the cabin.
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FIG. 1 is a flow chart of a method for calculating the distribution of aerodynamic noise of a propeller along the surface of a fuselage according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The method for calculating the distribution of the aerodynamic noise of the propeller along the surface of the propeller body mainly comprises the following steps of:
step S1, constructing a propeller pneumatic noise source model by taking a propeller as a noise source;
step S2, constructing a propeller finite element model, dividing the position of a propeller blade into a rotation domain, setting other parts into a static domain, and forming a cylindrical calculation domain by the rotation domain and the static domain;
s3, constructing a propeller aerodynamic model, performing steady-state calculation of a flow field in a cruising state based on airplane cruising parameters, and calculating a transient result according to the steady-state calculation result of the flow field to obtain aerodynamic data of the surface pulsating pressure and the surface pulsating speed of propeller blades distributed along with time in the cruising state of the airplane;
step S4, establishing a geometric model of the fuselage, and performing acoustic meshing;
and S5, enabling the propeller aerodynamic noise sound source to be equivalent to a fan sound source, establishing a propeller and fuselage acoustic model, and taking the aerodynamic data in the step S3 as input to obtain the noise distribution directly radiated from the propeller to the outer surface of the fuselage under the cruise state of the airplane.
In some optional embodiments, step S1 is preceded by:
s0, constructing a full-machine coordinate system, and acquiring parameters for calculating the propeller aerodynamic model in a cruise state, wherein the method specifically comprises the following steps:
s01: establishing a propeller geometric model according to geometric parameters such as blade airfoil, blade angle, blade thickness, blade number, hub radius and the like;
s02: and defining a propeller coordinate system, taking the axis of the propeller as an original point, taking the axis as a z-axis (the positive direction is the course), pointing the x-axis to the right side along the course, and determining the y-axis direction according to a right-hand rule.
In some alternative embodiments, in step S1, when constructing the propeller aerodynamic noise sound source model, each area element of the propeller is used as a single-stage sub sound source, a dipole sound source, and/or a four-stage sub sound source.
In the embodiment, the propeller is the main noise source in the taking-off, landing and cruising phases of the airplane. According to the FW-H equation and the theory of the phyllotas, an infinite number of blade micro-segments (i.e. the phyllotas) on the propeller are defined as a single-stage sub-sound source, a dipole sound source or a four-stage sub-sound source, and for example, a mathematical model formed by the three sub-sound sources is as follows:
Figure BDA0002753107640000041
wherein H (f) is a Heaviside function, and
Figure BDA0002753107640000042
c 0 is the speed of sound, ρ 0 Is the air density, P '(x, t) is the sound pressure, δ (f) represents the distribution of the moving surface-area sound source, P' ij Is the fluid stress tensor, T ij Represents the Lighthill tensor, and T ij ＝-P′ ij +ρu i u j -c 2 ρ′δ ij ，u n And v n The first term on the right side of the equation represents a single-stage sub-source, the second term represents a dipole source, and the third term represents a four-stage sub-source, for the air flow velocity and the motion velocity of the integration plane.
In step S2, a propeller finite element model is established, the position of the propeller blade is divided into a rotation domain, other parts are set as a stationary domain, the two are connected through an Interface and carry out numerical value transfer, and a cylindrical external field with better orthogonality is selected in the overall calculation domain (including the rotation domain and the stationary domain).
In this embodiment, the rotating domain adopts the non-structural grid, and uses the grid adaptive encryption technique to encrypt to the paddle leading-trailing edge, and the static domain adopts the hexahedron structure grid, and cylindrical outfield radius sets up to 10 times of propeller radius, and axis direction length sets up to 25 times of propeller radius.
In step S3, calculating the transient result includes,
step S31, when the residual error of the lift force and the drag force of the whole aircraft is less than 10 -3 When the calculation result is converged, the steady-state calculation result is given; and step S32, calculating the transient result by taking the steady-state calculation result as an initial solution.
It can be understood that a propeller aerodynamic model is established, the steady state calculation of the flow field in the cruising state is carried out according to the conditions of the cruising altitude, the cruising speed, the propeller rotating speed and the like of the airplane, and then the steady state calculation result is used as an initial solution calculation transient state result, so that aerodynamic data of the surface pulsating pressure, the surface pulsating speed and the like of the propeller blade distributed along with time are obtained, and input conditions are provided for the calculation of aerodynamic noise.
Wherein the pneumatic model analysis parameters are set as:
type of parameter Setting conditions
Turbulence model Standard k-epsilon model
Flow field density model Non-compressible ideal gas
Solver type Discrete unsteady state solver
Type of rotary motion Moving Reference Frame
Pressure velocity coupling algorithm SIMPLE algorithm
Pressure discrete format PRESTO
Windward grid Second-order windward grid
In some of the alternative embodiments, the first and second electrodes are,
in step S4, the criteria for acoustic meshing is to ensure that there are at least six mesh cells within one wavelength λ of the sound wave, i.e., to ensure that there are at least six mesh cells within one wavelength λ of the sound wave
Figure BDA0002753107640000051
λ＝c 0 /f, to ensure that the simulation of the sound wave is as accurate as possible.
In some alternative embodiments, the step S5 of obtaining the noise distribution directly radiated from the propeller to the outer surface of the fuselage in the cruising state of the aircraft includes: and calculating the aerodynamic noise of the whole propeller based on a boundary element method.
According to the method, complete simulation of the complete machine capable of obtaining relatively accurate calculation results is established, a set of method for accurately estimating the distribution of the aerodynamic noise of the propeller along the surface of the machine body is provided, and a foundation is laid for predicting the noise level in the cabin and improving the comfort of passengers in the cabin.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (4)

1. A method for calculating the distribution of aerodynamic noise of a propeller along the surface of a machine body is characterized by comprising the following steps:
step S1, constructing a propeller pneumatic noise source model by taking a propeller as a noise source;
step S2, constructing a propeller finite element model, dividing the position of a propeller blade into a rotation domain, setting other parts into a static domain, and forming a cylindrical calculation domain by the rotation domain and the static domain;
s3, constructing a propeller aerodynamic model, performing steady-state calculation of a flow field in a cruising state based on airplane cruising parameters, and calculating a transient result according to the steady-state calculation result of the flow field to obtain aerodynamic data of the surface pulsating pressure and the surface pulsating speed of propeller blades distributed along with time in the cruising state of the airplane;
step S4, establishing a geometric model of the fuselage, and performing acoustic meshing;
s5, enabling the propeller aerodynamic noise source to be equivalent to a fan sound source, establishing a propeller and fuselage acoustic model, taking the aerodynamic data in the S3 as input, and obtaining the noise distribution of the propeller directly radiating to the outer surface of the fuselage under the cruise state of the airplane;
in step S1, when constructing the propeller aerodynamic noise sound source model, each area element of the propeller is used as a single-stage sub sound source, a dipole sound source, and/or a four-stage sub sound source;
in step S3, the calculating the transient result includes:
step S31, when the residual error of the lift force and the drag force of the whole aircraft is less than 10 -3 When the calculation result is converged, the steady-state calculation result is given;
step S32, calculating the transient result by taking the steady-state calculation result as an initial solution;
in step S4, when the acoustic mesh division is performed, the mesh size a is set to:
Figure FDA0003763877790000011
λ min ＝c 0 /f，
wherein f is the calculated frequency, c 0 Is the speed of sound.
2. The method for calculating the distribution of aerodynamic noise of a propeller along the surface of a fuselage according to claim 1, wherein the step S5 of obtaining the distribution of noise radiated directly from the propeller toward the outer surface of the fuselage at cruise conditions of the aircraft comprises: and calculating the aerodynamic noise of the whole propeller based on a boundary element method.
3. The method for calculating the distribution of aerodynamic noise from propellers along a surface of an airframe as recited in claim 1, wherein in step S2, the radius of the cylinder is 10 times the radius of the propellers and the length in the axial direction is 25 times the radius of the propellers.
4. The method for calculating the distribution of aerodynamic noise of a propeller along a surface of a fuselage of claim 1, wherein step S1 is preceded by the step of:
and constructing a full-machine coordinate system, and acquiring parameters for calculating the propeller aerodynamic model in a cruising state.
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Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107066761A (en) * 2017-05-16 2017-08-18 沈阳航空航天大学 A kind of electric airplane propeller noise computational methods
CN111591458A (en) * 2020-05-29 2020-08-28 中国航空工业集团公司西安飞机设计研究所 Design method for noise control in propeller aircraft cabin

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