CN111783325A - Method for manufacturing cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation - Google Patents
Method for manufacturing cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation Download PDFInfo
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- 238000009530 blood pressure measurement Methods 0.000 title claims abstract description 22
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 22
- 230000003068 static effect Effects 0.000 claims abstract description 11
- 230000001360 synchronised effect Effects 0.000 claims abstract description 6
- 238000009826 distribution Methods 0.000 claims description 25
- 239000000463 material Substances 0.000 claims description 8
- 230000010349 pulsation Effects 0.000 claims description 4
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Abstract
The invention discloses a method for manufacturing a cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation, which comprises the following steps: (1) manufacturing a cooling tower aeroelastic model by using an equivalent beam lattice method; (2) adhering an elastic light film on the surface of the beam grid aeroelastic model, and arranging pressure measuring holes on nodes to obtain a cooling tower aeroelastic pressure measuring model; (3) and simulating the Reynolds number effect on the surface of the cooling tower aeroelastic pressure measurement model by using a dynamic and static wind load synchronous Reynolds number effect simulation method. The method overcomes the defects that the traditional cooling tower pressure measurement model cannot consider the pneumatic self-excitation effect and cannot ensure the simulation accuracy of the dynamic wind effect, combines an equivalent beam lattice aeroelastic model manufacturing method and a dynamic and static wind load synchronous Reynolds number effect simulation method, and accurately reproduces the real dynamic and static flow characteristics of the surface of the cooling tower through a wind tunnel test by using the model.
Description
Technical Field
The invention relates to a method for manufacturing a cooling tower aeroelastic pressure measurement model, in particular to a method for manufacturing a cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation.
Background
Wind load, as a spatial thin-walled structure, is an important controlling factor in the design of cooling towers. Some cooling tower wind damage accidents have occurred historically, which have attracted attention from all parties. In order to ensure the safety of the structure under the action of strong wind, the structural design of a large cooling tower is usually developed based on wind resistance design, and field actual measurement, numerical simulation and wind tunnel test are three means of wind resistance design of the cooling tower. The field actual measurement is troublesome and laborious, and complete wind load information cannot be obtained frequently; numerical simulations are based on simplifications and assumptions about true physical phenomena, which are generally less accurate. Therefore, wind tunnel tests are the most important means for designing the wind resistance of the current cooling tower.
The pressure test is the most basic structural wind tunnel test, and cooling tower structural designers often directly use tower surface wind load obtained by the pressure test to carry out structural design. However, there are currently two problems that directly affect the reliability of the cooling tower pressure test: firstly, the model used in the traditional pressure measurement test is a rigid model, the pneumatic self-excitation effect caused by the self-vibration of the structure cannot be considered, and engineering personnel find that the pneumatic self-excitation effect of the cooling tower structure is usually more remarkable, and the test result is unsafe if the pneumatic self-excitation is neglected. Secondly, the flow-bypassing Reynolds number of the wind tunnel test is about two orders of magnitude lower than the actual situation, and if the problem is not considered, the pressure-measuring wind tunnel test result of the cooling tower can be seriously deviated from the true value. In order to solve this problem, the experimenter makes the static wind effect of the model surface approach the real result by means of a method of vertically sticking a rough tape on the model surface, and the method is called Reynolds number effect simulation. However, the traditional reynolds number effect simulation method only focuses on the accuracy of static wind effect simulation, and neglects the simulation of real dynamic wind effect. If the real dynamic and static streaming characteristics of the surface of the cooling tower are accurately and synchronously reproduced through a wind tunnel test, the two technical problems need to be solved.
Disclosure of Invention
The purpose of the invention is as follows: the invention aims to provide a method for manufacturing a cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation.
The technical scheme is as follows: the invention provides a method for manufacturing a cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation, which comprises the following steps:
(1) manufacturing a cooling tower aeroelastic model by using an equivalent beam lattice method;
(2) adhering an elastic light film on the surface of the beam grid aeroelastic model, and arranging pressure measuring holes on nodes to obtain a cooling tower aeroelastic pressure measuring model;
(3) and simulating the Reynolds number effect on the surface of the cooling tower aeroelastic pressure measurement model by using a dynamic and static wind load synchronous Reynolds number effect simulation method.
Further, the manufacturing method in the step (1) comprises the following steps:
a. establishing a finite element model of the refined cooling tower by using the shell unit, and calculating the structure dynamic characteristics;
b. establishing a simplified cooling tower finite element model by utilizing the beam unit;
c. taking the width of the meridian beam unit and the thickness and the width of the annular beam unit at each height of the simplified model as independent variables, taking the low-order dynamic characteristic of the refined finite element model as a target function, and obtaining the specific size of the beam lattice unit of the aeroelastic model by iterative optimization of the simplified finite element model;
d. and selecting materials to manufacture a cooling tower aeroelastic model.
Further, the simulation method in the step (3) is as follows:
a. sticking a rough belt on the surface of the model along the vertical direction, and obtaining a Reynolds number effect simulation working condition by changing the incoming flow wind speed and the thickness of the rough belt;
b. selecting a Reynolds number effect simulation working condition candidate group by comparing the actually measured surface average wind pressure distribution of the cooling tower with the average wind pressure distribution curves of various Reynolds number effect simulation working conditions;
c. and selecting an optimal Reynolds number effect simulation working condition by comparing the actually measured tower surface pulsation wind pressure distribution with the pulsation wind pressure distribution curves of various working conditions in the candidate group.
Further, the material of the material is a galvanized thin steel sheet.
Has the advantages that: according to the invention, by manufacturing the cooling tower aeroelastic pressure measurement model, the structure pneumatic self-excitation effect is accurately considered in the cooling tower pressure measurement test; by using a dynamic and static wind load synchronous Reynolds number effect simulation method, the real dynamic and static streaming characteristics of the surface of the cooling tower are accurately reproduced in a wind tunnel test. The method is efficient and accurate.
Drawings
FIG. 1 is a diagram of an aeroelastic model of a cooling tower manufactured by an equivalent beam lattice method according to an embodiment of the present invention;
FIG. 2 is a diagram of a model of aeroelastic pressure measurement of a cooling tower made in an embodiment of the present invention;
FIG. 3 is a schematic diagram of relevant parameters for various rough strip thickness conditions in an embodiment of the present invention;
FIG. 4 is a graph of the distribution of the average and pulsating wind pressure of the model surface obtained based on 32 Reynolds number effect simulation conditions in the embodiment of the present invention, in which (a) is a graph of the distribution of the average wind pressure and (b) is a graph of the distribution of the pulsating wind pressure;
FIG. 5 is a graph of the mean and pulsating wind pressure distribution curves and the actual measurement results of the model surface obtained based on 5 operating conditions in the Reynolds number effect simulation candidate set in the embodiment of the present invention, wherein (a) the graph is a mean wind pressure distribution graph, and (b) the graph is a pulsating wind pressure distribution graph;
fig. 6 is a graph of the model surface average and pulsating wind pressure distribution curves and the actual measurement result obtained based on the optimal reynolds number effect simulation condition in the embodiment of the present invention, where (a) is a graph of an average wind pressure distribution, and (b) is a graph of a pulsating wind pressure distribution.
Detailed Description
The cooling tower aeroelastic pressure measurement model adopting Reynolds number effect simulation of the embodiment comprises the following steps:
(1) the method for manufacturing the cooling tower aeroelastic model by using the equivalent beam lattice method comprises the following specific steps:
firstly, the cooling tower drum shell unit is modeled finely, and for the number of the meridional shell units in the embodiment: m132, number of circumferential shell units: n144.
Secondly, modeling is carried out by utilizing space beam units, the number of the meridional beam units is 13, the number of the annular beam units is 36, the maximum adjustable unit size is 2(2m +1) n is 1944, and the radial thickness and width variables are simplified to be D in consideration of the annular symmetry of the cooling tower structurever，i，Wver，i(i ═ 1, m), and the variation in hoop thickness and width is Dcir，j，Wcir，j(j-1, m +1), the number of variables is reduced to 4m + 2-54.
Thirdly, considering the convenient processability of the model, the meridian beam lattice unit adopts a full-length equal-thickness component, Dver，iReduced to a single variable X0Calculating the bending resistance constant matrix C and the axial shrinkage stiffness constant matrix C of the cylinder with different heights and unit sizes according to the bending stiffness and the axial stiffness shrinkage requirements of the cylinder of the cooling towerbending，i，Caxial，i(i ═ 1, m). Assuming that the size of the cooling tower model component and the scale rigidity satisfy the linear combination condition:
Dver，i＝X0E1×m(1)
in the formula, X0～X6For the coefficients to be identified optimally; e1×mThe modulus of elasticity of the material used to make the model; cbending，i，Caxial，iThe bending resistance and the axial scale stiffness of the case per unit dimension width at i height, respectively.
Based on the formula (1) and the formula (2), the number of the variables is further simplified to 6-7. Modeling with cooling tower shell cellsTaking the first 8-order mode as a simulation target according to the dynamic characteristic result, and giving X1～X6And (5) obtaining the specific size of the beam lattice unit of the aeroelastic model by iteratively optimizing and adjusting the variable value at the initial value.
And finally, manufacturing a aeroelastic model by using a galvanized thin steel sheet as a material, wherein the thickness of the standard section is 0.1mm increment, the thickness is 0.1-1.0 mm, the width direction adopts a linear cutting mode, and the machining size precision is 0.01 mm. The cooling tower aeroelastic model thus produced is shown graphically in fig. 1.
(2) And (3) adhering an elastic light film on the surface of the beam grid aeroelastic model, and arranging 36 (annular) multiplied by 12 (meridian) pressure measuring holes at the beam grid nodes to obtain the cooling tower aeroelastic pressure measuring model. The manufactured cooling tower aeroelastic pressure model is graphically shown as figure 2.
(3) The method for simulating the Reynolds number effect on the surface of the cooling tower aeroelastic pressure measurement model by utilizing the dynamic and static wind load Reynolds number effect synchronous simulation method specifically comprises the following steps:
firstly, 36 rough strips are uniformly pasted on the surface of a cooling tower aeroelastic pressure measurement model along the vertical direction, and 32 Reynolds number effect simulation working conditions are obtained by setting 4 incoming flow wind speeds (6m/s, 8m/s, 10m/s and 12m/s) and 8 rough strip thicknesses (detailed parameters of various rough strip thickness working conditions are given in table 1). The distribution curves of the average and pulsating wind pressure of the model surface obtained under the 32 kinds of Reynolds number effect simulation conditions are graphically shown as figure 4.
TABLE 1 detailed parameters for various coarse strip thickness regimes
Secondly, comparing the actually measured average wind pressure distribution of the surface of the cooling tower with the average wind pressure distribution curve of 32 Reynolds number effect simulation working conditions, and selecting 5 Reynolds number effect simulation working conditions with the same height as the actually measured average wind pressure distribution curve as Reynolds number effect simulation working condition candidate groups, wherein the Reynolds number effect simulation working conditions comprise a three-layer paper tape +12m/s wind speed working condition, a four-layer paper tape +6m/s wind speed working condition, a four-layer paper tape +8m/s wind speed working condition, a four-layer paper tape +10m/s wind speed working condition and a four-layer paper tape +12 m/. The model surface average and pulsating wind pressure distribution curves and the actual measurement results obtained based on 5 working conditions in the reynolds number effect simulation working condition candidate group are graphically displayed as figure 5.
And finally, selecting the optimal Reynolds number effect simulation working condition as a four-layer paper tape +10m/s wind speed working condition by comparing the actually measured fluctuation wind pressure distribution of the tower surface with the fluctuation wind pressure distribution curves of 5 working conditions in the Reynolds number effect simulation working condition candidate group. The surface average and pulsating wind pressure distribution curves of the model obtained based on the optimal Reynolds number effect simulation working condition and the actual measurement result are graphically displayed as figure 6.
Claims (4)
1. A method for manufacturing a cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation is characterized by comprising the following steps of: the method comprises the following steps:
(1) manufacturing a cooling tower aeroelastic model by using an equivalent beam lattice method;
(2) adhering an elastic light film on the surface of the beam grid aeroelastic model, and arranging pressure measuring holes on nodes to obtain a cooling tower aeroelastic pressure measuring model;
(3) and simulating the Reynolds number effect on the surface of the cooling tower aeroelastic pressure measurement model by using a dynamic and static wind load synchronous Reynolds number effect simulation method.
2. The method for manufacturing the cooling tower aeroelastic pressure measurement model by adopting Reynolds number effect simulation according to claim 1, is characterized in that: the manufacturing method in the step (1) comprises the following steps:
a. establishing a finite element model of the refined cooling tower by using the shell unit, and calculating the structure dynamic characteristics;
b. establishing a simplified cooling tower finite element model by utilizing the beam unit;
c. taking the width of the meridian beam unit and the thickness and the width of the annular beam unit at each height of the simplified model as independent variables, taking the low-order dynamic characteristic of the refined finite element model as a target function, and obtaining the specific size of the beam lattice unit of the aeroelastic model by iterative optimization of the simplified finite element model;
d. and selecting materials to manufacture a cooling tower aeroelastic model.
3. The method for manufacturing the cooling tower aeroelastic pressure measurement model by the Reynolds number effect simulation according to claim 2, wherein the method comprises the following steps: the simulation method in the step (3) comprises the following steps:
a. sticking a rough belt on the surface of the model along the vertical direction, and obtaining a Reynolds number effect simulation working condition by changing the incoming flow wind speed and the thickness of the rough belt;
b. selecting a Reynolds number effect simulation working condition candidate group by comparing the actually measured surface average wind pressure distribution of the cooling tower with the average wind pressure distribution curves of various Reynolds number effect simulation working conditions;
c. and selecting an optimal Reynolds number effect simulation working condition by comparing the actually measured tower surface pulsation wind pressure distribution with the pulsation wind pressure distribution curves of various working conditions in the candidate group.
4. The method for manufacturing the cooling tower aeroelastic pressure measurement model by the Reynolds number effect simulation according to claim 2, wherein the method comprises the following steps: the material of the material is galvanized thin steel sheet.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113504027A (en) * | 2021-08-13 | 2021-10-15 | 南京航空航天大学 | Method for manufacturing aeroelastic wind tunnel test model of wind turbine blade |
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