CN107066761B - Method for calculating propeller noise of electric aircraft - Google Patents
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Abstract
The invention provides a method for calculating the noise of a propeller of an electric airplane, which is characterized in that a three-dimensional geometric model of the propeller is established according to the structural parameters of the propeller of the electric airplane; gridding and dividing a flow field area of a three-dimensional geometric model of the propeller by adopting a finite element method to obtain a gridded and divided propeller flow field; carrying out unsteady pressure pulsation solution on the flow region of the gridded propeller flow field by adopting a large vortex simulation calculation model to obtain transient pressure distribution on the surface of the blade; the acoustic boundary element method is adopted to carry out sound field simulation on the acoustic grid model to obtain the radiation noise distribution of the propeller, all influence factors of noise are considered comprehensively, and the calculation result is accurate and reliable; the method can be used for pneumatic noise frequency domain analysis and the like, and can provide theoretical basis and technical guidance for effectively reducing the noise of the propeller.
Description
Technical Field
The invention belongs to the technical field of propeller aerodynamic noise analysis and control, and particularly relates to a propeller noise calculation method of an electric aircraft.
Background
Electric aircraft noise originates primarily from the propeller. The propeller noise not only affects the environment of the region where the airport is located, but also affects the riding comfort of drivers and passengers as the propeller noise is transmitted to the cabin; the sound fatigue and the structure vibration caused by the excessive noise of the propeller have great influence on the flight safety. The propeller noise mainly comes from aerodynamic noise, and the research on the propeller noise from the noise generation mechanism can not only estimate the noise value of the propeller in the preliminary design stage, but also provide theoretical basis and technical guidance for effectively reducing the propeller noise.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a method for calculating the propeller noise of an electric aircraft.
A method for calculating propeller noise of an electric aircraft comprises the following steps:
step 1: establishing a three-dimensional geometric model of the propeller according to the structural parameters of the propeller of the electric airplane;
step 2: gridding and dividing a flow field area of a three-dimensional geometric model of the propeller by adopting a finite element method to obtain a gridded and divided propeller flow field;
and step 3: setting boundary conditions of the gridded propeller flow field, and performing unsteady pressure pulsation solution on a flow region of the gridded propeller flow field by adopting a large vortex simulation calculation model to obtain blade surface transient pressure distribution;
and 4, step 4: mapping transient pressure distribution data of the blade surface to an acoustic grid model, taking an unsteady pressure pulsation grid of the acoustic grid model as a boundary condition of a structure, taking the transient pressure distribution of the blade surface as a boundary condition of an acoustic part of the blade, and performing sound field simulation on the acoustic grid model by adopting an acoustic boundary element method to obtain radiation noise distribution of the propeller.
The structural parameters of the electric airplane propeller comprise: the propeller pitch, the pitch ratio, the disk surface ratio, the hub diameter ratio and the blade type value.
The method is characterized in that a finite element method is adopted to carry out gridding division on a flow field area of a three-dimensional geometric model of the propeller, and the specific process of obtaining a gridded and divided propeller flow field is as follows:
and carrying out grid differentiation on the rotating area of the three-dimensional geometric model of the propeller by adopting a finite element method of an unstructured tetrahedral grid, and carrying out grid differentiation on the flowing area of the three-dimensional geometric model of the propeller by adopting a finite element method of a structured hexahedral grid to obtain a grid-divided propeller flow field.
The boundary conditions of the set gridded and divided propeller flow field comprise:
the inlet pressure boundary condition of the flow-through region is atmospheric pressure;
the boundary type of the propeller outline is a wall surface;
the inlet interface of the flow-through area is set as a pressure inlet;
the outlet interface of the flow-through area is set as a pressure outlet;
the rotating area is integrally set as an interface;
the rotating zone fluid continuous zone type is set as fluid.
The invention has the beneficial effects that:
the invention provides a method for calculating the propeller noise of an electric aircraft, which comprehensively considers all influence factors of the noise and has accurate and reliable calculation results; the method can be used for pneumatic noise frequency domain analysis and the like, and can provide theoretical basis and technical guidance for effectively reducing the noise of the propeller.
Drawings
FIG. 1 is a flow chart of a method for calculating propeller noise of an electric aircraft according to an embodiment of the present invention;
FIG. 2 is a three-dimensional geometric model of a propeller according to an embodiment of the present invention
FIG. 3 is a three-dimensional geometric mesh model of a propeller in accordance with an embodiment of the present invention;
wherein, (a) is a rotating region mesh model of the propeller;
(b) a partial enlarged view of a rotating region mesh model of the propeller;
(c) the method comprises the following steps of (1) forming a whole flow field grid model of a propeller;
FIG. 4 is a graph of the ambient radiation noise distribution at different rotational speeds of the propeller in accordance with an embodiment of the present invention;
wherein, (a) is the noise distribution with the frequency of 33.333Hz when the rotating speed of the front of the propeller is 1000 r/min;
(b) the noise distribution with the frequency of 66.7Hz when the rotating speed of the front surface of the propeller is 2000 r/min;
(c) the noise distribution with the frequency of 33.333Hz when the rotating speed of the side surface of the propeller is 1000 r/min;
(d) the noise distribution is 66.7Hz when the rotating speed of the side surface of the propeller is 2000 r/min.
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings.
A method for calculating propeller noise of an electric aircraft, as shown in fig. 1, comprises the following steps:
step 1: and establishing a three-dimensional geometric model of the propeller according to the structural parameters of the propeller of the electric airplane.
In this embodiment, the structural parameters of the propeller of the electric aircraft include: the propeller pitch, the pitch ratio, the disk surface ratio, the hub diameter ratio and the blade type value.
The number N of blades of the propeller is 2, the diameter D of the propeller is 1.6m, the radius Rh of the hub is 0.06m, and the rated rotating speed N is 1500 r/min.
Fig. 2 shows a three-dimensional geometric model of a propeller obtained in the present embodiment.
Step 2: and gridding the flow field area of the three-dimensional geometric model of the propeller by adopting a finite element method to obtain a gridded propeller flow field.
In the embodiment, an ICEM software is adopted to perform gridding division on the flow field area of the three-dimensional geometric model of the propeller to obtain a gridded and divided propeller flow field:
and (c) carrying out gridding differentiation on the rotating region of the three-dimensional geometric model of the propeller by adopting a finite element method of an unstructured tetrahedral grid, as shown in (a) and (b) in fig. 3, and carrying out gridding differentiation on the flowing region of the three-dimensional geometric model of the propeller by adopting a finite element method of a structured hexahedral grid, so as to obtain a gridded and divided propeller flow field, as shown in (c) in fig. 3.
And step 3: setting boundary conditions of the gridded propeller flow field, and performing unsteady pressure pulsation solution on a flow region of the gridded propeller flow field by adopting a large vortex simulation calculation model to obtain blade surface transient pressure distribution.
In the embodiment, Fluent software is adopted to solve the unsteady pressure pulsation in the flow area of the gridded propeller flow field, so as to obtain the transient pressure distribution on the surface of the blade.
And 4, step 4: mapping transient pressure distribution data of the blade surface to an acoustic grid model, taking an unsteady pressure pulsation grid of the acoustic grid model as a boundary condition of a structure, taking the transient pressure distribution of the blade surface as a boundary condition of an acoustic part of the blade, and performing sound field simulation on the acoustic grid model by adopting an acoustic boundary element method to obtain radiation noise distribution of the propeller.
In this embodiment, the boundary conditions of the determined gridded propeller flow field include:
the boundary condition of the inlet pressure of the circulation area is atmospheric pressure, which is standard atmospheric pressure and atmospheric pressure at 15 ℃ on the sea level.
The propeller contour boundary type is a wall.
The inlet interface of the flow-through area is set as a pressure inlet.
The outlet interface of the flow-through area is set as a pressure outlet.
The entire rotation region is set as an interface.
The rotating zone fluid continuous zone type is set as fluid.
Lab boundary element acoustic tool is adopted to carry out sound field simulation on the acoustic grid model to obtain the radiation noise distribution of the propeller, in the embodiment, the propeller blade frequency conversion calculation formula is as shown in formula (1):
and calculating the noise distribution with the frequency of 33.333Hz when the rotating speed of the front face of the propeller is 1000r/min according to a frequency calculation formula, wherein the noise distribution with the frequency of 33.333Hz when the rotating speed of the front face of the propeller is 2000r/min is shown in figure 4(a), and the equal sound pressure lines of the propeller at the plane field point are annularly distributed along the radial direction, the sound pressure value is maximum at the center of the plane sound field and gradually decreases outwards along the radial direction, as shown in figure 4 (b). When the rotating speed is 1000r/min, the maximum radiation sound pressure of the spherical field point is 93.1 dB; when the rotating speed is 2000r/min, the maximum radiation sound pressure of the spherical field point is 111 dB.
The noise distribution with the frequency of 33.333Hz when the rotating speed of the side surface of the propeller is 1000r/min is shown in fig. 4(c), the noise distribution with the frequency of 66.7Hz when the rotating speed of the side surface of the propeller is 2000r/min is shown in fig. 4(d), the equal sound pressure line of the propeller in the plane sound field is in 8-shaped distribution, the sound pressure is lower at the position close to the cylinder, and the sound pressure is higher at the position close to the inlet and the outlet of the propeller. When the rotating speed is 1000r/min, the maximum radiation sound pressure of the spherical field point is 86.3 dB; when the rotating speed is 2000r/min, the maximum radiation sound pressure of the spherical field point is 104 dB.
Claims (4)
1. A method for calculating propeller noise of an electric aircraft is characterized by comprising the following steps:
step 1: establishing a three-dimensional geometric model of the propeller according to the structural parameters of the propeller of the electric airplane;
step 2: gridding and dividing a flow field area of a three-dimensional geometric model of the propeller by adopting a finite element method to obtain a gridded and divided propeller flow field;
and step 3: setting boundary conditions of the gridded propeller flow field, and performing unsteady pressure pulsation solution on a flow region of the gridded propeller flow field by adopting a large vortex simulation calculation model to obtain blade surface transient pressure distribution;
and 4, step 4: and (3) mapping the transient pressure distribution data of the blade surface to an acoustic grid model, taking the unsteady pressure pulsation grid in the step (3) as a boundary condition of a structure in the acoustic grid model, taking the transient pressure distribution of the blade surface as a boundary condition of an acoustic part of the blade, and performing sound field simulation on the acoustic grid model by adopting an acoustic boundary element method to obtain the radiation noise distribution of the propeller.
2. The method of claim 1, wherein the parameters of the propeller comprise propeller blade number, propeller diameter, propeller pitch, pitch ratio, disk ratio, hub diameter ratio, and blade type value.
3. The method for calculating the propeller noise of the electric aircraft according to claim 1, wherein the flow field area of the three-dimensional geometric model of the propeller is gridded by adopting a finite element method, and the specific process of obtaining the gridded propeller flow field is as follows:
and carrying out grid differentiation on the rotating area of the three-dimensional geometric model of the propeller by adopting a finite element method of an unstructured tetrahedral grid, and carrying out grid differentiation on the flowing area of the three-dimensional geometric model of the propeller by adopting a finite element method of a structured hexahedral grid to obtain a grid-divided propeller flow field.
4. The method of claim 1, wherein the setting boundary conditions for the gridded, divided propeller flow fields comprises:
the inlet pressure boundary condition of the flow-through region is atmospheric pressure;
the boundary type of the propeller outline is a wall surface;
the inlet interface of the flow-through area is set as a pressure inlet;
the outlet interface of the flow-through area is set as a pressure outlet;
the rotating area is integrally set as an interface;
the rotating zone fluid continuous zone type is set as fluid.
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| CN109018397B (en) * | 2018-08-13 | 2020-04-03 | 南京航空航天大学 | Rotor vortex ring state automatic early warning system and method based on pneumatic noise monitoring |
| CN110750854B (en) * | 2019-09-02 | 2022-09-02 | 中国第一汽车股份有限公司 | Method for improving accuracy of solving wind noise of automobile based on SNGR method |
| CN111591458B (en) * | 2020-05-29 | 2023-03-24 | 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 |
| CN112214944B (en) * | 2020-10-27 | 2022-07-15 | 武汉理工大学 | Method for determining load of airplane subjected to wind shear caused by downburst during takeoff and landing |
| CN112270045B (en) * | 2020-10-30 | 2022-08-19 | 中国航空工业集团公司西安飞机设计研究所 | Turboprop aircraft aerodynamic noise calculation method |
| CN112257184B (en) * | 2020-10-30 | 2022-09-06 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating distribution of aerodynamic noise of propeller along surface of machine body |
| CN113221409B (en) * | 2021-05-07 | 2023-04-14 | 香港中文大学(深圳)城市地下空间及能源研究院 | Two-dimensional numerical simulation method and device for acoustic waves with coupled finite elements and boundary elements |
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