CN112270044A - Design method of propeller aerodynamic noise wind tunnel model - Google Patents

Design method of propeller aerodynamic noise wind tunnel model Download PDF

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CN112270044A
CN112270044A CN202011196911.8A CN202011196911A CN112270044A CN 112270044 A CN112270044 A CN 112270044A CN 202011196911 A CN202011196911 A CN 202011196911A CN 112270044 A CN112270044 A CN 112270044A
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propeller
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肖乾
顾金桃
高飞
王美燕
胡陈映
刘成玉
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Xian Aircraft Design and Research Institute of AVIC
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Abstract

The application belongs to the technical field of airplane design, and particularly relates to a design method of a propeller aerodynamic noise wind tunnel model. The method comprises the steps of ensuring the geometric similarity, the flow similarity and the power similarity between a propeller aerodynamic noise wind tunnel model and a prototype propeller according to a similarity criterion dimension analysis method, and determining the ratio of the similarity ratio of each parameter between the propeller aerodynamic noise wind tunnel model and the prototype propeller; selecting a driving device of a propeller pneumatic noise wind tunnel model meeting the requirements of size, power and noise; adopting a sectional type cylindrical support model; and selecting the size of the fairing with the minimum influence on the performance of the aerodynamic noise wind tunnel model of the propeller according to the thrust, power and efficiency curves of the fairing and the propeller. The design method of the aerodynamic noise wind tunnel model provided by the application has the advantages that the design consideration of the aircraft wind tunnel model is more detailed, the development period is greatly shortened, and the purpose of test and examination is achieved.

Description

Design method of propeller aerodynamic noise wind tunnel model
Technical Field
The application belongs to the technical field of airplane design, and particularly relates to a design method of a propeller aerodynamic noise wind tunnel model.
Background
The wind tunnel model is a physical experiment model which is designed and produced according to a similar theory on the basis of a three-dimensional digital model of a real airplane in the airplane model development process. The wind tunnel model is used for measuring aerodynamic characteristics of each component of an airplane, and the design of the wind tunnel model must meet the wind tunnel installation requirement, carry out strength check calculation and meet the requirements of machining and assembling precision.
The key points and difficulties of the wind tunnel model test are usually reflected in the design and planning of the wind tunnel model. The design and planning of the wind tunnel model directly influence the data efficiency, quality and cost of the wind tunnel test. Before a propeller is subjected to a pneumatic noise wind tunnel test, a propeller wind tunnel model design method needs to be established urgently, so that the wind tunnel model design consideration is ensured to be more detailed, the development period is greatly shortened, and the purpose of test examination is achieved.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a method for designing a wind tunnel model of propeller aerodynamic noise, comprising:
s1, ensuring the geometric similarity, the flow similarity and the power similarity between the propeller aerodynamic noise wind tunnel model and the prototype propeller according to a similarity criterion dimension analysis method, and determining the ratio of the similarity ratio of each parameter between the propeller aerodynamic noise wind tunnel model and the prototype propeller;
s2, selecting a driving device of the propeller aerodynamic noise wind tunnel model meeting the requirements according to the size, power and noise requirements;
s3, selecting a three-section cylindrical support with the diameter one time, two times or three times that of a propeller hub, wherein the three-section cylindrical support is parallel to a rotating shaft of the propeller;
s4, selecting the size of the fairing with the smallest influence on the performance of the aerodynamic noise wind tunnel model of the propeller according to the thrust, power and efficiency curves of the fairing and the propeller;
and S5, selecting a rigid model manufacturing material or an elastic model manufacturing material to construct the propeller aerodynamic noise wind tunnel model.
Preferably, step S1 is preceded by selecting an open replaceable test segment for acoustic testing, and the test segment comprises a total anechoic chamber with a background noise of less than 77db (a).
Preferably, in step S1, the determining the ratio of the similarity ratio of each parameter between the propeller aerodynamic noise wind tunnel model and the prototype propeller at least includes:
and sequentially determining the length ratio, the rotating speed ratio, the tension ratio and the power ratio between the propeller aerodynamic noise wind tunnel model and the prototype propeller.
Preferably, in step S2, the driving device includes an air motor or an electric motor.
Preferably, in step S5, the rigid mold is made of stainless steel, 7075 aluminum alloy or LC4, and the elastic mold is made of 7050 aluminum alloy or composite material.
Preferably, after step S5, the method further includes:
and S6, performing strength check on each component of the wind tunnel model by adopting a finite element analysis method, and performing structure optimization design on each component of the wind tunnel model according to a finite element analysis result, wherein the optimization target parameters comprise propeller thrust, power and efficiency.
Preferably, the wind tunnel model is processed by adopting a three-dimensional photocuring rapid prototyping technology.
The method starts from wind tunnel model selection, and provides a detailed design method of a propeller aerodynamic noise wind tunnel model by determining the scaling size, model attributes, materials, a processing method, selection of requirements, a driving device meeting performance requirements, a supporting device and a fairing which have minimum influence on the performance of a propeller, checking and optimizing the strength of the model and packing and transporting requirements, so that reliable support is provided for a propeller aerodynamic noise test.
Drawings
FIG. 1 is a flow chart of a propeller aerodynamic noise wind tunnel model design method 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 accompanying 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 design method of the propeller aerodynamic noise wind tunnel model, as shown in fig. 1, mainly comprises the following steps:
the method comprises the following steps: selecting an acoustic wind tunnel: the test section with replaceable opening for acoustic test should be provided, and the test section with opening should include a complete anechoic chamber with background noise less than 77db (a) (reduce noise measurement influence caused by background noise, and simultaneously realize the non-reflection free sound field environment required by acoustic test), and specify the main parameters of the test section cross-sectional size, the test section length, the test section cross-sectional area, the test section average turbulence, the test section maximum wind speed and the like, for example, select a certain type of single-backflow low-speed low-turbulence acoustic wind tunnel. The test device is provided with two replaceable test sections of an opening and a closing, wherein the opening test section of the wind tunnel is mainly used for acoustic tests, the cross section of the opening test section is rectangular, and the area of the opening test section is 20m2A maximum wind speed of 85m/s, including a total anechoic chamber with a background noise of 76dB (A);
step two: according to a similarity criterion dimension analysis method, realizing geometric similarity, flow similarity and power similarity between a propeller aerodynamic noise wind tunnel model and a prototype propeller, further ensuring that the working states of the propeller aerodynamic noise wind tunnel model and the prototype propeller are similar, converting small-size wind tunnel model data of the propeller into a prototype, and sequentially determining a length ratio, a rotating speed ratio, a tension ratio and a power ratio;
wherein, the geometrical similarity condition is as follows:
Figure BDA0002754285580000031
Figure BDA0002754285580000032
θ1＝θ2；
wherein subscript 1 represents a prototype propeller, subscript 2 represents a wind tunnel model, D is the diameter of the propeller, b is the width of the phyllotaxis at the radius r of the propeller blade, theta is the mounting angle of the phyllotaxis, eta isLThe geometric similarity ratio can ensure that the corresponding edges are proportional and the angles are equal.
The application provides a satisfy quick definite screw wind-tunnel model diameter D of above-mentioned requirement2Empirical formula (iv)
Figure BDA0002754285580000033
Wherein A is the cross-sectional area of the pilot section of the wind tunnel in the first step.
Flow-like conditions:
Figure BDA0002754285580000034
wherein V0Is the flow velocity, nsThe rotating speeds of the propellers, namely the speed fields of the air flows bypassing the propellers are similar, the speeds on corresponding points are proportional, and the directions are the same.
Similar conditions of power
1) Reynolds similarity criterion
Figure BDA0002754285580000041
Deducing a similarity ratio formula:
air movement viscosity ratio
Figure BDA0002754285580000042
Density ratio
Figure BDA0002754285580000043
Then the rotational speed ratio
Figure BDA0002754285580000044
Speed ratio
Figure BDA0002754285580000045
Ratio of time
Figure BDA0002754285580000046
Ratio of tensile forces
Figure BDA0002754285580000047
Power ratio
Figure BDA0002754285580000048
2) Strouhal number similarity criterion
Figure BDA0002754285580000049
Deducing a similarity ratio formula:
ratio of rotational speeds
Figure BDA00027542855800000410
Speed ratio
Figure BDA00027542855800000411
Ratio of time
Figure BDA00027542855800000412
Ratio of tensile forces
Figure BDA00027542855800000413
Power ratio
Figure BDA00027542855800000414
In the steps of this example:
the cross-sectional area A of the wind tunnel test section is known to be 20m2Diameter D of propeller25m, flight height h of the turboprop1At 20km, the air density was 0.088kg/m3Air movement viscosity coefficient of 1.61X 10-4m2S, propeller speed n1At 500rpm, power p1Is 1.5kw, tension T1Is 50N, wind speed V1Is 30 m/s; air density rho in wind tunnel test2Is 1.225kg/m3Coefficient of air movement viscosity gamma21.46X 10-5m 2/s;
according to the formula
Figure BDA0002754285580000051
Then D is2＝[2.26m，2.76m]Selecting D22.5m, the length ratio
Figure BDA0002754285580000052
Designing a model according to Reynolds criterion:
air movement viscosity ratio
Figure BDA0002754285580000053
Density ratio
Figure BDA0002754285580000054
Then the rotational speed ratio
Figure BDA0002754285580000055
Speed ratio
Figure BDA0002754285580000056
Ratio of time
Figure BDA0002754285580000057
Ratio of tensile forces
Figure BDA0002754285580000058
Power ratio
Figure BDA0002754285580000059
Similarly, various similarity ratios under the ST criterion design model can be obtained.
Step three: a propeller coordinate system is defined to facilitate positioning and design of a propeller and arrangement of sensors in a test stage, the origin of coordinates is a propeller rotation center (namely a propeller disc center), an x axis is in a forward direction along a course, a y axis is pointed to the right side along the course, and a z axis is determined according to right-hand rules and is in a positive direction.
Step four: according to the size, power and noise requirements, selecting a propeller driving device meeting the requirements: an air powered motor or an electric machine.
The air power motor in the step has the advantages of small size, high power and high noise, and the air power motor is superposed with the frequency of the propeller; the motor has the advantages of low noise and the disadvantage that the power is in direct proportion to the size; therefore, the motor is generally selected as a propeller driving device, a pneumatic noise wind tunnel test is facilitated, and the maximum rotating speed in the motor performance parameters can meet the rotating speed requirement in the step two.
Step five: selecting a supporting device: the diameter of the selected sectional type cylindrical support is 1,2 and 3 times of the diameter of the propeller hub, and the central axis of the sectional type cylindrical support is parallel to the x axis.
Step six: selection of a fairing: and selecting the size of the fairing with the minimum influence on the performance of the propeller according to the thrust, power and efficiency curves of the fairing and the propeller.
The tension T of the propeller is converted into a dimensionless coefficient as follows:
Figure BDA00027542855800000510
wherein the content of the first and second substances,
Figure BDA0002754285580000061
is the coefficient of propeller tension;
Figure BDA0002754285580000062
strouhal number for gas stream;
Figure BDA0002754285580000063
(for air density) is the number of Re;
Figure BDA0002754285580000064
is the Fr number; b is the chord length of the blade;
Figure BDA0002754285580000069
is the total pitch angle;
Figure BDA0002754285580000065
is a geometric torsion angle;
the scalar functional form of the power P of the propeller is:
Figure BDA0002754285580000066
the efficiency of the propeller is:
Figure BDA0002754285580000067
wherein, CPIs the power coefficient of the propeller and is,
Figure BDA0002754285580000068
step seven: the traditional wind tunnel model is regarded as a rigid model, and an elastic model can be selected for researching the vibration or deformation of the propeller wind tunnel model.
Step eight: selecting wind tunnel model materials: the propeller wind tunnel model belongs to a low-speed wind tunnel model, wherein a rigid model is generally made of stainless steel, 7075 or LC4, and an elastic model is generally made of 7050 or a composite material.
Step nine: intensity checking and optimizing of the model: and (3) checking the strength of the main parts of the wind tunnel model by adopting a finite element analysis method, and carrying out structure optimization design on the propeller wind tunnel model according to a finite element analysis result.
When the optimization design is carried out in the step, the objective function optimization of the propeller thrust, the power and the efficiency is carried out by selecting key parameters based on the parametric sensitivity analysis of the propeller parts.
Step ten: selecting a wind tunnel model processing method: besides the traditional manufacturing processes of turning, milling, planing, grinding, drilling and the like, the rapid forming technology of stereo photocuring and the like can be selected.
Step eleven: the wind tunnel model processing generally requires:
the surface roughness Ra of each part of the model is less than or equal to 0.8 mu m, the roughness Ra of the matching surface of each part is less than or equal to 1.6 mu m, and the assembly gap of the part is less than or equal to 0.1 mm;
the pin-hole matching is performed according to H7/H6;
dimensional and form tolerances not specifically noted are performed according to the following criteria: the dimensional tolerance is processed by IT10 grade, and the form and position tolerance is processed by K grade.
Step twelve: packing and transporting requirements:
the wind tunnel model box is made of aluminum alloy, the corners of the box body are reinforced and wrapped, and the bottom of the box body is provided with two square pillows to facilitate the loading and unloading of a forklift;
the wind tunnel model is packaged in a box in parts, and hard foam is filled in the box for keying and fixing;
a packing list and a packing photo are pasted on the inner side of the box cover in each wind tunnel model box;
a metal nameplate is fixed in the wind tunnel model box, characters such as model names, production dates, model proportions, a plurality of boxes and a plurality of boxes are printed on the nameplate, and the nameplate is about 150mm multiplied by 100mm in size;
the exterior of the wind tunnel model box is provided with necessary marks such as upward, damp-proof, fragile and the like;
the outside of the wind tunnel model box is provided with a common x box and a second x box;
a model three-coordinate measurement report and a model qualification certificate are required to be arranged in the wind tunnel model box.
The invention provides a detailed design method of a propeller aerodynamic noise wind tunnel model from wind tunnel model selection, and provides reliable support for a propeller aerodynamic noise test by determining the scaling size, model attributes, materials, a processing method, selection of requirements, a driving device meeting performance requirements, a supporting device and a fairing which have minimum influence on the performance of a propeller, checking and optimizing the strength of the model and packing and transporting requirements.
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 (7)

1. A design method for a propeller aerodynamic noise wind tunnel model is characterized by comprising the following steps:
s1, ensuring the geometric similarity, the flow similarity and the power similarity between the propeller aerodynamic noise wind tunnel model and the prototype propeller according to a similarity criterion dimension analysis method, and determining the ratio of the similarity ratio of each parameter between the propeller aerodynamic noise wind tunnel model and the prototype propeller;
s2, selecting a driving device of the propeller aerodynamic noise wind tunnel model meeting the requirements according to the size, power and noise requirements;
s3, selecting a three-section cylindrical support with the diameter one time, two times or three times that of a propeller hub, wherein the three-section cylindrical support is parallel to a rotating shaft of the propeller;
s4, selecting the size of the fairing with the smallest influence on the performance of the aerodynamic noise wind tunnel model of the propeller according to the thrust, power and efficiency curves of the fairing and the propeller;
and S5, selecting a rigid model manufacturing material or an elastic model manufacturing material to construct the propeller aerodynamic noise wind tunnel model.
2. The method according to claim 1, wherein step S1 is preceded by selecting an open replaceable test section for acoustic testing, wherein the test section comprises a full anechoic chamber with a background noise of less than 77db (a).
3. The method for designing the aerodynamic noise wind tunnel model of the propeller as claimed in claim 2, wherein in step S1, determining the ratio of the similarity ratio of each parameter between the aerodynamic noise wind tunnel model of the propeller and the prototype propeller at least comprises:
and sequentially determining the length ratio, the rotating speed ratio, the tension ratio and the power ratio between the propeller aerodynamic noise wind tunnel model and the prototype propeller.
4. The method for designing the aerodynamic noise wind tunnel model of the propeller as defined in claim 1, wherein in step S2, the driving device comprises an aerodynamic motor or an electric motor.
5. The design method of the propeller aerodynamic noise wind tunnel model according to claim 1, wherein in step S5, the rigid model is made of stainless steel, 7075 aluminum alloy or LC4, and the elastic model is made of 7050 aluminum alloy or composite material.
6. The method for designing the aerodynamic noise wind tunnel model of the propeller as recited in claim 1, further comprising, after the step S5:
and S6, performing strength check on each component of the wind tunnel model by adopting a finite element analysis method, and performing structure optimization design on each component of the wind tunnel model according to a finite element analysis result, wherein the optimization target parameters comprise propeller thrust, power and efficiency.
7. The design method of the wind tunnel model for the aerodynamic noise of the propeller according to claim 1, wherein the wind tunnel model is processed by a three-dimensional photocuring rapid prototyping technology.
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