CN115879396B - Flow one-dimensional pneumatic design method for air inlet front chamber of high-altitude simulation test bed - Google Patents
Flow one-dimensional pneumatic design method for air inlet front chamber of high-altitude simulation test bed Download PDFInfo
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Abstract
The invention discloses a one-dimensional pneumatic design method for a flow of an air inlet front chamber of a high-altitude simulation test bed, belongs to the technical field of design of high-altitude simulation test equipment of an aeroengine, and aims to design a set of method which meets the requirements of high uniformity, low turbulence and reasonable pressure loss. Comprising obtaining the designed airflow parameters of the inlet and the outlet of the expansion section and the air flow Wa and the pressure loss limiting value DeltaP of the engine under the condition of atmospheric air intake max And an inner diameter D of the constriction 2 Flow rate limit value V of steady flow section 0 The air flow parameter comprises a flow rate limit value V of the air inlet pipeline 1 Inner diameter D 1 And cross-sectional area A 1 And sequentially determining parameters such as the parameters of the rectifying device, the shrinkage ratio and the like, performing precision adjustment, finally forming a one-dimensional pneumatic design method for the flow of the air inlet front chamber, and outputting the parameters meeting the requirements.
Description
Technical Field
The invention belongs to the technical field of design of aeroengine high-altitude simulation test equipment, and particularly relates to a one-dimensional pneumatic design method for a flow of an air inlet front chamber of a high-altitude simulation test bed.
Background
The high-altitude simulation test bed (called as a high-altitude platform for short) is used as important equipment for the whole machine test of the aeroengine, can simulate the air intake and exhaust conditions of the engine during the air flight operation, and plays a role in identification and assessment in the development process of the engine. The structure of the air inlet front chamber is used as one of important main equipment of the high altitude platform, and mainly comprises an air inlet expansion section, a rectifying section, a steady flow section, a contraction section and the like, is used for receiving air supply incoming flow and a tested engine, is mainly used for stabilizing and homogenizing flow fields, and is used for establishing engine inlet conditions of a high-quality flow field meeting test requirements in various high altitude flight states, so that a design core is developed around a pneumatic scheme, the targets of high flow field uniformity and low turbulence are required to be met, meanwhile, small pressure loss and the like are considered, wherein the high uniformity and the low turbulence can improve air flow measurement precision and accuracy, and the performance assessment of the engine is directly influenced; the small pressure loss mainly considers that the engine can stably work in the test of atmospheric air intake-direct exhaust.
Although the air inlet front chamber of the high-altitude simulation test cabin under construction or demonstration is different from the air inlet front chamber under test objects and test demands, the whole structure is basically similar, the requirements for meeting the quality of an air inlet flow field are consistent, the design method of the air inlet front chamber mainly refers to the use experience of the existing high-altitude platform front chamber and the design method for meeting the test demands, and the design principle of a low-speed wind tunnel pressure stabilizing chamber is partially referred to, and the front chamber design concept and method of a system which is unique to the field of high-altitude model test equipment of an aeroengine are not formed, which is not beneficial to the enhancement and improvement of the design reliability, the design efficiency and the technical maturity of the same type of equipment,
a set of schemes meeting high uniformity, low turbulence and reasonable pressure loss are needed to be designed so as to fill the blank of domestic rapid flow pneumatic design in the air inlet front chamber of the high-altitude platform.
Disclosure of Invention
In view of the above, the invention provides a one-dimensional pneumatic design method for the flow of an air inlet front chamber of a high-altitude simulation test bed, which aims to design a set of method meeting the requirements of high uniformity, low turbulence and reasonable pressure loss, and improves the design reliability, design efficiency and technical maturity of the same type of equipment in the high-altitude bed.
The utility model provides a high altitude simulation test bed air inlet antechamber flow one-dimensional pneumatic design method, the air inlet antechamber is provided with expansion section, rectification section, stationary flow section, shrink section at least along the air inlet direction, and expansion section intercommunication has the admission line, shrink end and engine intercommunication, the method includes:
s101, acquiring airflow parameters from an inlet of an expansion section, air flow Wa and pressure loss limiting value DeltaP under the condition of engine atmospheric air intake max And an inner diameter D of the constriction 2 Flow rate limit value V of steady flow section 0 The airflow parameter comprises a flow rate limit value V of an air inlet pipeline 1 Inner diameter D 1 And cross-sectional area A 1 ；
S102, the flow rate limit value V 0 Flow rate limit value V 1 And cross-sectional area A 1 Calculating the cross-sectional area A of the steady flow section according to the flow conservation principle 0 And pass through the cross-sectional area A 0 Calculating the expansion area ratio As and the inner diameter D of the steady flow section 0 And determining whether the expansion area ratio As is within a preset numerical range;
s103, obtaining the cross-sectional area A of the joint of the contraction section and the engine 2 According to the cross-sectional area A 2 Determining whether the contraction ratio C is within a preset numerical range, if so, calculating the length L of the expansion section 1 If not, the air flow parameters of the S101 are adjusted until the shrinkage ratio C is within a preset numerical range;
s104, determining the maximum size d of the particulate matters in the airflow 0 A rectifying device is arranged in the rectifying section to filter the particles, and the size parameters and the installation positions of the rectifying grids in the rectifying device are determined;
s105, calculating total flow flowing through the rectifying device under the condition of atmospheric air intake according to the size parameters of the rectifying grid in the rectifying deviceAnd determining whether the pressure loss Δp is smaller than the pressure loss limit value Δp max If so, determining the form of the contraction curve according to the actual requirement, and if not, adjusting the size parameter and/or the installation position of the rectifying grid in the rectifying device until the pressure loss DeltaP is less than the pressure loss limiting value DeltaP max ；
S106, after the form of the contraction curve is determined, calculating the turbulence level of the outlet of the current contraction section
And judging the turbulence level +>
If the size parameter is smaller than the design value, generating a one-dimensional aerodynamic force setting diagram, and if the size parameter is smaller than the design value, adjusting the size parameter of the rectification grid until the size parameter is smaller than the design value;
s107, selecting a preset number of working points in a one-dimensional aerodynamic force setting diagram, performing three-dimensional aerodynamic simulation, outputting a three-dimensional simulation result, judging whether the temperature and pressure non-uniformity of a flow field are below a standard design value according to the three-dimensional simulation result, if so, outputting all data or preset number of data in the steps S101-S106, if not, adjusting a flow rate limit value V 0 And a flow rate limit value V 1 Is recalculated in accordance with the steps S101-S106 until a value below the canonical design value is met.
The invention has the beneficial effects that:
on the basis of the existing engineering experience, the invention combines the design target of the air inlet front chamber, more accurately determines the key parameters of the front chamber structure influencing the quality of the air inlet flow field, adjusts the key parameters through repeated iterative solution calculation, ensures the uniformity of pressure and temperature in the flow field, finally determines the pneumatic design scheme of the front chamber, provides the internal association relation and the determination method and principle of each key parameter, builds the complete one-dimensional design method design about the pneumatic design scheme of the air inlet front chamber, forms the design flow of the air inlet front chamber for the first time in the industry, is beneficial to improving the design efficiency of similar test equipment, and adjusts and supplements the blank of the one-dimensional pneumatic design method of the air inlet front chamber.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of an intake front chamber;
FIG. 2 is a flow chart of the design method of the present invention.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present invention will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present invention with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. The invention may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present invention. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
The one-dimensional aerodynamic design method for the flow of the air inlet front chamber of the high-altitude simulation test bed shown in fig. 2 is suitable for testing an engine, and is designed for the one-dimensional aerodynamic of the air inlet front chamber, and as shown in fig. 1, the air inlet front chamber is at least provided with an expansion section, a rectifying section, a steady flow section and a contraction section along the air inlet direction, the expansion section is communicated with an air inlet pipeline, and the contraction end is communicated with the engine, and the method comprises the following steps:
s101, acquiring the designed airflow parameters at the inlet of the expansion section, the air flow Wa and the pressure loss limit value DeltaP under the condition of engine atmospheric air intake max And an inner diameter D of the constriction 2 Flow rate limit value V of steady flow section 0 The air flow parameter comprises a flow rate limit value V of the air inlet pipeline 1 Inner diameter D 1 And cross-sectional area A 1 Specific:
the air inlet pipeline is arranged in an equal-diameter straight pipe structure, and the air flow parameters are generally based on the endmost parameters of the air inlet pipeline. The air flow parameter and the pressure loss limit value delta P can be determined according to the model comparison specification of the engine or the existing test data max And an inner diameter D of the constriction 2 Flow rate limit value V of steady flow section 0 In design, the inner diameter of the tail end of the contraction section is preferably taken as a reference, the inner diameter of the tail end of the contraction section is the same as the maximum inlet diameter of the tested engine, the inner diameters of the steady flow section and the contraction section are the same, and the cross-sectional areas of the steady flow section and the contraction section are not changed;
s102 flow rate limit V 0 Flow rate limit value V 1 And cross-sectional area A 1 Calculating the cross-sectional area A of the steady flow section according to the flow conservation principle 0 And pass through cross-sectional area A 0 Calculating the expansion area ratio As and the inner diameter D of the steady flow section 0 And determining whether the expansion area ratio As is within a preset numerical range (2-4), specifically:
because the Mach number of the airflow in the air inlet equipment of the high-altitude simulation test bed is smaller than 0.3, the airflow is considered to be incompressible flow in one-dimensional design, namely the air inlet pipeline is the same as the air flow density in the air inlet chamber, and the airflow can be obtained according to the principle of flow conservation,
the air flow rate Wa satisfies:
，/>
is the cross-sectional area A 1 Air density of>
Is the cross-sectional area A 0 The air density of (a) can be calculated to obtain the cross-sectional area A 0 ；
The expansion area ratio As satisfies:
judging whether the diameter is in the range of 2-4, if so, calculating the inner diameter D 0 If not, adjust the flow rate limit value V 1 Flow rate limit value V 0 Until the expansion area ratio As is in the range of 2-4;
according to D 1 And the expansion area ratio As is obtained according to the law of conservation of flow,
inner diameter D 0 The method comprises the following steps:
；
s103, obtaining the cross-sectional area A of the joint of the contraction section and the engine 2 According to the cross-sectional area A 2 Determining whether the contraction ratio C is within a preset numerical range, if so, calculating the length L of the expansion section 1 If not, the airflow parameters of S101 are adjusted until the shrinkage ratio C is within a preset numerical range, specifically:
end outlet cross-sectional area A of contraction section considered in design of air inlet front chamber of high-altitude platform 2 The maximum inlet diameter D2 of the engine can be tested according to the vehicle platform. The larger shrinkage ratio is beneficial to the outlet to obtain lower turbulence, but the isotropy and the reality of the turbulenceThere are differences, and too large a shrinkage ratio increases the equipment cost, and the shrinkage ratio C is preferably 7 to 10.
Shrinkage ratio C, satisfying:
the shrinkage ratio C is in the range of 7-10;
length L 1 The method comprises the following steps:
θ is an expansion angle of the expansion section, preferably, 20-40 degrees, and the flow state in the expansion section is controlled more stably by calculating θ by adopting the expansion angle, so that the separation phenomenon that the reverse pressure gradient cannot be overcome due to the air flow momentum is avoided in the expansion section;
s104, determining the maximum size d of the particulate matters in the airflow according to the design specification of the engine 0 And configuring a rectifying device in the rectifying section to filter the particulate matters, and determining the size parameters and the installation positions of the rectifying grids in the rectifying device, wherein the specific steps are as follows:
the rectifying device comprises a coarse rectifying device 21 and a fine rectifying device 22 which are sequentially arranged along the airflow direction, the fine rectifying device 22 comprises a fine rectifying grid, the cross section size of a grid unit is not more than 50mm multiplied by 50mm, the coarse rectifying device 21 comprises a coarse rectifying grid, and the cross section size of the grid unit is not more than 200mm multiplied by 200mm. Distance L of fine rectification grid from end of expansion section 2 The wake shear flow attenuation distance and the installation requirement after the fine rectifying device are met, and the general installation distance is 1m. The fine rectifying grid and the coarse rectifying grid are provided with damping nets (generally 2 layers) with preset layers at the air inlet end. The mesh size w (the maximum mesh size is 0.5mm multiplied by 0.5 mm) of the matched damping net and the wire diameter d are smaller than or equal to the maximum size d of particles in the air flow 0 And calculating the aperture ratio beta of the damping net 1 Coefficient of pressure drop K 1 And turbulence level attenuation coefficient f 1 Wherein:
opening ratio beta 1 The method comprises the following steps:
；
damping net pressure drop coefficient K 1 The method comprises the following steps:
，/>
is a correction factor for sudden expansion of the airflow during the flow process;
turbulence attenuation coefficient f 1 The method comprises the following steps:
；
the aperture ratio of the fine rectification grid is beta 2 Pressure drop coefficient K 2 Length L 3 The size of the airflow cross section is w Thin and fine ×w Thin and fine And the wall thickness d of the grid sheet Thin and fine Opening ratio beta 2 The method meets the following conditions:
，
coefficient of pressure drop K 2 The method meets the following conditions:
，/>
；
the aperture ratio of the coarse rectification grid is beta 3 Pressure drop coefficient K 3 Length L 3 The size of the airflow cross section is w Coarse size ×w Coarse size And the wall thickness d of the grid sheet Coarse size Opening ratio beta 3 The method meets the following conditions:
，
coefficient of pressure drop K 3 The method meets the following conditions:
，/>
。
s105, calculating the atmospheric air intake condition according to the size parameter of the rectifying grid in the rectifying deviceThe total pressure loss delta P of the airflow flowing through the rectifying device is judged whether the pressure loss delta P is smaller than the pressure loss limiting value delta P max If so, determining the form of the contraction curve according to the actual requirement, if not, adjusting the size parameter and/or the mounting position of the rectifying grid in the rectifying device until the pressure loss DeltaP is less than the pressure loss limiting value DeltaP max Specifically, the pressure loss Δp satisfies:
determining the length L of the steady flow section according to the form of the contraction curve 6 The form of the shrinkage curve comprises at least: twisted pair style, hyperbolic and bellmouth, wherein:
when selecting twisted pair, length L 6 =（0.75～1.0）D 0 Length L when selecting a hyperbola or bell mouth 6 =（0.5～0.75）D 0 ；
Length L of the constriction 7 According to the installation form (generally, end socket type), the form of a contraction curve, the installation mode and the like of an air inlet pipe of an engine in a contraction section, searching a design specification and selecting a length L 7 Is a numerical value of (2).
S106, after the form of the contraction curve is determined, calculating the turbulence level of the outlet of the current contraction section
And judging the turbulence level +>
If the size parameter is smaller than the design value (not larger than 1%), if so, generating a one-dimensional aerodynamic force setting diagram, if not, adjusting the size parameter of the rectification grid until the condition smaller than the design value is satisfied, specifically:
calculating turbulence attenuation coefficient f according to contraction ratio C 2 The method comprises the following steps:
；
turbulence level of the outlet of the constriction
2, satisfy: />
，/>
The turbulence level of the flow field is initially set, the flow field is selected according to the type of the engine, and n is the number of layers of the damping net;
s107, selecting a preset number of working points (preferably, typical points) in a one-dimensional aerodynamic force setting diagram, performing three-dimensional aerodynamic simulation through simulation software, outputting a three-dimensional simulation result, judging whether the temperature and pressure unevenness of a flow field are below a standard design value (preferably, the standard design value is 1%) according to the three-dimensional simulation result, if so, outputting all data or preset number of data (output of key point data) in the steps S101-S106, if not, adjusting a flow speed limit value V 0 And a flow rate limit value V 1 Is recalculated in accordance with the steps S101-S106 until a value below the canonical design value is met.
As the specific embodiment provided in the scheme, the interval length of the coarse rectifying device and the fine rectifying device is L 4 ，L 4 Take twice L 2 And a maximum value of 1m.
The whole technical effect is as follows:
1) On the basis of the existing engineering experience, the invention combines the design target of the air inlet front chamber, more accurately determines the key parameters of the front chamber structure influencing the quality of the air inlet flow field, provides the internal association relation of the key parameters, the determination method and the principle, constructs the complete one-dimensional design method design about the pneumatic design scheme of the air inlet front chamber, forms the design flow of the air inlet front chamber for the first time in the industry, and is beneficial to improving the design efficiency of similar test equipment.
2) The method and the principle for determining the structural key parameters of the influence of the flow field quality of the air inlet front chamber are based on the classical theory of incompressible fluid and the design and use experience of the existing equipment, and the reliability are higher through practice, so that the reliability of the design scheme of the similar test equipment is improved, and the technical maturity of the test equipment is enhanced.
3) The method can meet the requirements of the inlet flow field of the engine specified in GJB4879 as follows: pressure field non-uniformity is not more than + -1%, temperature field non-uniformity is not more than + -1%, turbulence is not more than + -1%, and comprises:
1, large angle expansion section flow field stabilization technique
The flow speed of the air flow in the straight section of the front chamber is controlled, so that the pressure loss of the incoming flow can be effectively reduced, and a large-angle expansion section is required to be adopted in engineering design due to double limitation of space layout and maximum flow speed index, so that the area expansion can be realized in a short distance, the air flow speed of an outlet is reduced, and the static pressure is increased; however, as the expansion angle is large, boundary layer separation generally occurs in the flowing process, large-area vortex which is difficult to eliminate is brought, the flow field quality of the front chamber is affected, the expansion angle and the expansion area ratio are comprehensively considered in the overall design, and the anti-separation measure is additionally arranged according to actual needs.
2, stable and uniform rectification technology
In order to effectively and uniformly flow field, a steady flow section is designed at the downstream of the outlet of the expansion section of the front chamber, two groups of rectifying grids and damping nets are installed as main rectifying devices, and the two rectifying devices are installed in the following modes: damping net-rectification grid-damping net-rectification grid. The rectification grid has the functions of guiding and dividing air mass, straightening a streamline, improving the flow velocity distribution of the air flow due to the friction action of the wall facing the air flow, accelerating the attenuation of vortex to a certain extent and reducing the turbulence of the air flow; damping net function: firstly, sundries in a front pipeline are blocked, and the sundries are prevented from entering an engine; secondly, the airflow vortex is attenuated, the turbulence is reduced, and the flow field is uniform; the iterative calculation is carried out by adopting whether the pressure loss meets the requirement, and the shearing interference of the thickness of the grid plate on the airflow at the outlet of the rectifying grid is avoided, and a wake area of a small-scale vortex exists in a downstream flow field.
3 turbulence control technique
The turbulence is the ratio of square root average value of the pulsation velocity in three directions to the main flow average velocity in the flow field, the irregular movement of the fluid micro-clusters is the reason for forming pulsation, the turbulence of the air flow is reduced by arranging a damping net, the opening ratio and the pressure drop coefficient are configured, and the aim of reducing the turbulence is achieved by consuming time-sharing flow energy when the air flow flows through the damping net.
4, designing the contraction ratio C to achieve the purpose of turbulence reduction, and when the air flows along the contraction section, compressing, bending, turning and the like can be performed on small-scale vortexes in the air flow due to continuous contraction of the inner molded surface, and according to the Helmholtz vortex tube strength maintenance theorem, when the vortex tube is compressed, the cross section area of the vortex tube is increased, the vortex quantity is weakened, so that the turbulence in the flow field is attenuated; the merits of shrink section performance depend mainly on two factors: the first is the shrinkage ratio, and the second is the shrinkage curve, so that the proper shrinkage curve should be selected and the reasonable shrinkage ratio should be determined according to the actual use condition during the overall design.
In summary, in order to meet the requirement of the quality of the air inlet flow field specified by the national army standard, the overall pneumatic design of the front chamber needs to comprehensively analyze key structural parameters such as expansion area ratio, expansion angle, damping net parameters, static flow section length, shrinkage curve, shrinkage ratio and the like which influence the quality of the flow field.
The present invention is not limited to the above embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention. Therefore, the protection scope of the invention is subject to the protection scope of the claims.
Claims (7)
1. The utility model provides a one-dimensional pneumatic design method of high altitude simulation test bed air inlet antechamber flow, its characterized in that, the air inlet antechamber is provided with expansion section, rectification section, stationary flow section, shrink section at least along the air inlet direction, expansion section intercommunication has the admission line, shrink section and engine intercommunication, the method includes:
s101, acquiring airflow parameters at the inlet of the expansion section, air flow Wa and pressure loss limiting value DeltaP under the condition of engine atmospheric air intake max And an inner diameter D of the constriction 2 Flow rate limit value V of steady flow section 0 The airflow parameter comprises a flow rate limit value V of an air inlet pipeline 1 Inner diameter D 1 And cross-sectional area A 1 ；
S102, the flow rate limit value V 0 Flow rate limit value V 1 And cross-sectional area A 1 Calculating the cross-sectional area A of the steady flow section according to the flow conservation principle 0 And pass through the cross-sectional area A 0 Calculating the expansion area ratio As and the inner diameter D of the steady flow section 0 And determining whether the expansion area ratio As is within a preset numerical range;
s103, obtaining the cross-sectional area A of the joint of the contraction section and the engine 2 According to the cross-sectional area A 2 Determining whether the contraction ratio C is within a preset numerical range, if so, calculating the length L of the expansion section 1 If not, the air flow parameters of the S101 are adjusted until the shrinkage ratio C is within a preset numerical range;
s104, determining the maximum size d of the particulate matters in the airflow 0 A rectifying device is arranged in the rectifying section to filter the particles, and the size parameters and the installation positions of the rectifying grids in the rectifying device are determined;
s105, calculating the total pressure loss delta P of the airflow flowing through the rectifying device under the air intake condition according to the size parameters of the rectifying grid in the rectifying device, and judging whether the pressure loss delta P is smaller than the pressure loss limiting value delta P max If so, determining the form of the contraction curve according to the actual requirement, and if not, adjusting the size parameter and/or the installation position of the rectifying grid in the rectifying device until the pressure loss DeltaP is less than the pressure loss limiting value DeltaP max ；
S106, after the form of the contraction curve is determined, calculating the turbulence level of the outlet of the current contraction section
And judging the turbulence level +>
If the size parameter is smaller than the design value, generating a one-dimensional aerodynamic force setting diagram, and if the size parameter is smaller than the design value, adjusting the size parameter of the rectification grid until the size parameter is smaller than the design value;
s107, selecting a preset number of working points in a one-dimensional aerodynamic force setting diagram, performing three-dimensional aerodynamic simulation, outputting a three-dimensional simulation result, judging whether the temperature and pressure non-uniformity of a flow field are below a standard design value according to the three-dimensional simulation result, if so, outputting all data or preset number of data in the steps S101-S106, if not, adjusting a flow rate limit value V 0 And a flow rate limit value V 1 Is recalculated in accordance with the steps S101-S106 until a value below the canonical design value is met.
2. The design method according to claim 1, wherein S102 includes:
the air flow rate Wa satisfies:
，/>
is the cross-sectional area A 1 Air density of>
Is the cross-sectional area A 0 Is a gas density of (1);
the expansion area ratio As satisfies:
wherein A is 0 For the cross-sectional area of the steady flow section, V 1 Limiting value V for flow rate of air inlet pipeline 1 ，A 1 To expand the cross-sectional area at the inlet of the segment, V 0 A flow rate limit value for the steady flow section;
the inner diameter D 0 The method comprises the following steps:
。
3. the design method according to claim 1, wherein S103 includes:
the shrinkage ratio C satisfies:
the shrinkage ratio C is in the range of 7-10;
the length L 1 The method comprises the following steps:
θ is the expansion angle of the expansion section.
4. The design method according to claim 1, wherein S104 includes:
the rectifying device comprises a coarse rectifying device and a fine rectifying device which are sequentially arranged along the airflow direction, wherein the fine rectifying device comprises a fine rectifying grid, and the fine rectifying grid is away from the distance L of the tail end of the expansion section 2 The wake shear flow attenuation distance and the installation requirement after the fine rectifying device are met, the coarse rectifying device is provided with a coarse rectifying grid, the fine rectifying grid and the coarse rectifying grid are provided with damping nets with preset layers at the air inlet ends, the mesh size w and the wire diameter d of the damping nets are matched, and the mesh size w is smaller than or equal to the maximum size d of particles in the air flow 0 And calculating the aperture ratio beta of the damping net 1 Coefficient of pressure drop K 1 And turbulence level attenuation coefficient f 1 Wherein:
the aperture ratio beta 1 The method comprises the following steps:
；
the damping net pressure drop coefficient K 1 The method comprises the following steps:
，/>
is a correction factor for sudden expansion of the airflow during the flow process;
the turbulence degree attenuation coefficient f 1 The method comprises the following steps:
；
the aperture ratio of the fine rectification grid is beta 2 Pressure drop coefficient K 2 Length L 3 The size of the airflow cross section is w Thin and fine ×w Thin and fine And the wall thickness d of the grid sheet Thin and fine Opening ratio beta 2 The method meets the following conditions:
，
coefficient of pressure drop K 2 The method meets the following conditions:
length->
；
The aperture ratio of the coarse rectification grid is beta 3 Pressure drop coefficient K 3 Length L 5 The size of the airflow cross section is w Coarse size ×w Coarse size And the wall thickness d of the grid sheet Coarse size Opening ratio beta 3 The method meets the following conditions:
，
coefficient of pressure drop K 3 The method meets the following conditions:
length->
。
5. The design method according to claim 4, wherein S105 comprises:
the pressure loss Δp satisfies:
determining the length L of the steady flow section according to the form of the contraction curve 6 The form of the shrinkage curve comprises at least: twisted pair style, hyperbolic and bellmouth, wherein:
when selecting twisted pair, length L 6 =（0.75～1.0）D 0 Length L when hyperbolic curve or bellmouth is selected 6 =（0.5～0.75）D 0 。
6. The design method according to claim 5, wherein S106 comprises:
calculating a turbulence level attenuation coefficient f according to the contraction ratio C 2 The method comprises the following steps:
；
turbulence level of the outlet of the constriction
2, satisfy: />
N is the number of layers of the damping net, +.>
The flow field is initially given a turbulence level.
7. The method of claim 6, wherein the pitch length of the coarse and fine rectifying devices is L 4 ，L 4 Take twice L 2 And a maximum value of 1m.
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