CN115879396A - 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 flow one-dimensional pneumatic design method for an air inlet front chamber of an aerial simulation test bed, belongs to the technical field of design of aerial engine aerial simulation test equipment, and aims to design a set of method meeting the requirements of high uniformity, small turbulence and reasonable pressure loss. Comprises the steps of obtaining designed air flow parameters at the inlet of the expansion section, and obtaining the air flow Wa and the pressure loss limit value delta P under the atmospheric air inlet condition of the engine max And the inner diameter D of the constriction 2 And 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 part ofDiameter D 1 And cross-sectional area A 1 And parameters such as parameters of the rectifying device, contraction ratio and the like are sequentially determined, precision adjustment is carried out, finally, an air inlet front chamber flow one-dimensional pneumatic design method is formed, and parameters meeting requirements are output.
Description
Technical Field
The invention belongs to the technical field of design of high-altitude simulation test equipment of an aero-engine, and particularly relates to a flow one-dimensional pneumatic design method for 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 aircraft engine test, can simulate air intake and exhaust conditions of the engine during air flight work, and plays a role in identification and assessment in the development process of the engine. The air inlet front chamber is one of important main devices of the high-altitude platform, and the structure of the air inlet front chamber mainly comprises an air inlet expansion section, a rectification section, a steady flow section, a contraction section and the like, receives air supply incoming flow and an engine to be tested, is mainly used for stabilizing and homogenizing a flow field, and establishes engine inlet conditions of a high-quality flow field meeting test requirements under various high-altitude flight states, so that a design core needs to be developed around a pneumatic scheme, the targets of high flow field uniformity and low turbulence are required to be met, and meanwhile, the lower pressure loss and the like are considered, wherein the high uniformity and the low turbulence can improve the air flow measurement precision and accuracy, and directly influence the engine performance evaluation; the pressure loss is small, and the stable operation of the engine can be mainly considered during the atmospheric air intake-direct exhaust atmospheric test.
Although the air inlet front chamber of the high-altitude simulation test cabin used in construction or demonstration in China at present is different from the difference of test objects and test requirements, the whole structure is basically similar, the requirement for meeting the quality of an air inlet flow field is consistent, the design method mainly refers to the use experience of the existing high-altitude platform front chamber and the design method for meeting the test requirements at present, and partially refers to the design principle of a low-speed wind tunnel pressure stabilizing chamber, and a front chamber design concept and a method which are suitable for a unique system in the field of high-altitude model test equipment of an aeroengine are not formed, so that the design reliability, the design efficiency and the technical maturity of the equipment of the same type are not enhanced and improved,
a set of scheme meeting the requirements of high uniformity, small turbulence and reasonable pressure loss needs to be designed to fill the blank of the domestic rapid flow pneumatic design of the air inlet front chamber of the high-altitude platform.
Disclosure of Invention
In view of the above, the invention provides a flow one-dimensional pneumatic design method for an air inlet front chamber of an overhead simulation test bed, and aims to design a set of method meeting the requirements of high uniformity, small turbulence and reasonable pressure loss and improving the design reliability, design efficiency and technical maturity of the same type of equipment in the overhead simulation test bed.
The method for the flow-process one-dimensional pneumatic design of the air inlet front chamber of the high-altitude simulation test bed is provided, the air inlet front chamber is at least provided with an expansion section, a rectification 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 an engine, and the method comprises the following steps:
s101, obtaining air flow parameters at an inlet of an expansion section, and air flow Wa and a pressure loss limiting value delta P of an engine under the atmospheric air inlet condition max And the inner diameter D of the constriction 2 And 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 ；
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 passing through said blockArea of surface A 0 Calculating the expansion area ratio As and the inner diameter D of the steady flow section 0 Determining whether the expansion area ratio As is within a preset numerical range;
s103, acquiring the section 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 predetermined range of values, and if so, calculating the length L of the dilating segment 1 If not, adjusting the airflow parameter of S101 until the contraction ratio C is within a preset numerical range;
s104, determining the maximum size d of the particles in the airflow 0 A rectifying device is arranged on the rectifying section to filter particles and determine the size parameters and the installation position of a rectifying grid in the rectifying device;
s105, calculating the total pressure loss delta P of airflow flowing through the rectifying device under the condition of atmospheric air inlet according to the size parameters of the rectifying grids in the rectifying device, and judging whether the pressure loss delta P is smaller than the pressure loss limit value delta P or not max If so, the form of the contraction curve is determined according to actual requirements, if not, the size parameters and/or the installation position of the rectifying grids in the rectifying device are adjusted until the pressure loss delta P is smaller than the pressure loss limit value delta P max ；
S106, after the form of the contraction curve is determined, the turbulence degree of the current contraction section outlet is calculated
And judging the degree of turbulence>
If the size of the rectification grid is smaller than the design value, generating a one-dimensional aerodynamic force setting diagram, and if the size of the rectification grid is not smaller than the design value, adjusting the size parameter of the rectification grid until the condition that the size of the rectification grid is smaller than the design value is met;
s107, selecting a preset number of working condition points in the one-dimensional aerodynamic force setting diagram, performing three-dimensional aerodynamic simulation, outputting a three-dimensional simulation result, judging whether the temperature and pressure unevenness of the flow field is below a standard design value or not according to the three-dimensional simulation result, if so, outputting all data or preset number of data in the S101-S106 steps, and if not, adjusting a flow speed limit value V 0 And flowSpeed limit value V 1 Is recalculated according to the steps of S101-S106 until the value of (A) is below the specification design value.
The invention has the beneficial effects that:
the invention combines the design target of the air inlet front chamber on the basis of the existing engineering experience, more accurately determines the key parameters of the front chamber structure which affect the quality of the air inlet flow field, adjusts the key parameters through multiple iterative solution calculations, ensures the uniformity of pressure and temperature in the flow field, finally determines the pneumatic design scheme of the front chamber, provides the internal incidence relation of each key parameter, the determination method and the principle, constructs the complete one-dimensional design method design related to 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 the similar test equipment, and accordingly adjusts and compensates the blank of the one-dimensional pneumatic design method of the air inlet flow of the front chamber.
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In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used 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 it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic structural view of an intake antechamber;
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.
The following embodiments of the present invention are provided by way of specific examples, and other advantages and effects of the present invention will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that various aspects of the embodiments are described below within the scope of the appended 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 disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects 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. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
As shown in fig. 1, the air inlet front chamber is at least provided with an expansion section, a rectification 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 designed air flow parameters at the inlet of the expansion section, and air flow Wa and pressure loss limiting value delta P under the atmospheric air inlet condition of the engine max And the inner diameter D of the constriction 2 And 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 Specifically, the method comprises the following steps:
the air inlet pipeline is arranged in an equal-diameter straight pipe structure, and the air flow parameters are generally based on the parameters at the tail end of the air inlet pipeline. According to the model comparison specification of the engine or the existing test dataCan determine the air flow parameter and the pressure loss limit value delta P max And the inner diameter D of the constriction 2 And flow rate limit value V of steady flow section 0 Preferably, in the design, the inner diameter of the tail end of the contraction section is 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 flow stabilizing section and the contraction section are the same, and the cross-sectional areas of the flow stabilizing section and the contraction section are not changed;
s102 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 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 (2-4), specifically:
as the Mach numbers of the air flow in the air inlet equipment of the high-altitude simulation test bed are all less than 0.3, the air flow is considered to be incompressible flow during one-dimensional design, namely, the air flow density in the air inlet pipeline and the air inlet front chamber is the same, and the air flow can be obtained according to the flow conservation principle,
an air flow rate Wa satisfying:
，
is a cross-sectional area A 1 The density of the air of (a) is,
is a cross-sectional area A 0 The cross-sectional area A can be calculated from the air density 0 ；
The expansion area ratio As satisfies the following conditions:
judging whether the inner diameter D is within the range of 2-4, if so, calculating the inner diameter D 0 If not, adjusting 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 can be obtained according to the law of conservation of flux,
inner diameter D 0 And satisfies the following conditions:
；
s103, acquiring the section 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 predetermined range of values, and if so, calculating the length L of the dilating segment 1 If not, adjusting the airflow parameter of S101 until the contraction ratio C is within a preset numerical range, specifically:
sectional area A of outlet at tail end of contraction section considered in design of air inlet front chamber of high-altitude platform 2 Calculated as the maximum inlet diameter D2 of the bench-ready engine. The larger contraction ratio is favorable for obtaining lower turbulence degree of the outlet, but the isotropy of the turbulence degree is different from the real condition, the equipment cost is increased due to the overlarge contraction ratio, and the contraction ratio C is preferably 7-10.
The shrinkage ratio C satisfies:
the contraction ratio C ranges from 7 to 10;
length L 1 Satisfies the following conditions:
theta is an expansion angle of the expansion section, preferably, the range of 20-40 degrees, and the expansion angle is adopted to calculate theta, so that the flow state in the expansion section is more stably controlled, and the separation phenomenon caused by the fact that the airflow momentum cannot overcome the adverse pressure gradient is avoided in the expansion section;
s104, determining the maximum size d of the particles in the airflow according to the design specification of the engine 0 And a rectifying device is arranged on the rectifying section to filter particles, and the size parameters and the installation position of a rectifying grid in the rectifying device are determined, specifically:
the rectifying device comprises a thick rectifying device 21 and a thin rectifying device 22 which are sequentially installed along the airflow direction, the thin rectifying device 22 comprises a thin rectifying grid, the cross section size of a grid unit is not more than 50mm multiplied by 50mm, the thick rectifying device 21 comprises a thick rectifying grid, and the cross section size of the grid unit is not more than 200mm multiplied by 200mm. Thin and thinDistance L of the rectifying grid from the end of the expansion section 2 The trail shear flow attenuation distance and the installation requirement after the fine rectifying device are met, and the general installation distance is 1m. The fine rectification grids and the coarse rectification grids are provided with damping nets (generally 2 layers) with preset layers at the air inlet ends. Mesh size w (the maximum mesh size is 0.5mm multiplied by 0.5 mm) and wire diameter d of the damping mesh are matched, and the mesh size w is not more than the maximum size d of particles in the airflow 0 And calculating the aperture ratio beta of the damping net 1 Coefficient of pressure drop K 1 And the turbulence attenuation coefficient f 1 Wherein:
open porosity beta 1 And satisfies the following conditions:
；
damping net pressure drop coefficient K 1 And satisfies the following conditions:
，
a correction factor for sudden expansion of the gas flow during the flow;
turbulence attenuation coefficient f 1 Satisfies the following conditions:
；
the fine rectification grid has an opening ratio of beta 2 Coefficient of pressure drop K 2 Length L 3 The size of the flow cross section of the air flow is w Thin and thin ×w Thin and thin And the wall thickness d of the grid sheet Thin and thin Open porosity beta 2 Satisfies the following conditions:
，
coefficient of pressure drop K 2 Satisfies the following conditions:
，
；
the coarse rectification grid has an opening ratio of beta 3 Coefficient of pressure drop K 3 Length L 3 The size of the flow cross section of the air flow is w Coarse ×w Coarse And wall thickness d of the grid sheet Coarse Opening ratio beta 3 Satisfies the following conditions:
，
coefficient of pressure drop K 3 Satisfies the following conditions:
，
。
s105, calculating the total pressure loss delta P of airflow flowing through the rectifying device under the condition of atmospheric air inlet according to the size parameters of the rectifying grids in the rectifying device, and judging whether the pressure loss delta P is smaller than a pressure loss limit value delta P or not max If so, the form of the contraction curve is determined according to actual requirements, if not, the size parameters and/or the installation position of the rectification grids in the rectification device are adjusted until the pressure loss delta P is smaller than the pressure loss limit value delta P max Specifically, the pressure loss Δ P satisfies:
determining the length L of the constant flow section from the shrinkage curve pattern 6 The form of the shrinkage curve at least comprises: a twisted pair pattern, a bicubic curve, and a bell mouth, wherein:
length L when twisted pairs are selected 6 =（0.75～1.0）D 0 Length L when choosing bicubic curve or bell mouth 6 =（0.5～0.75）D 0 ；
Length L of the constriction 7 According to the installation form (generally, end enclosure type) of the air inlet pipe of the engine in the contraction section, the form and installation form of the contraction curve and the like, the length L is selected by searching the design specification 7 The numerical value of (c).
S106, after the form of the contraction curve is determined, the turbulence degree of the current contraction section outlet is calculated
And judging the degree of turbulence>
If the size of the rectification grid is smaller than the design value (not larger than 1%), if yes, generating a one-dimensional aerodynamic force setting map, and if not, adjusting the size parameters of the rectification grid until the condition that the size of the rectification grid is smaller than the design value is met, specifically:
calculating the turbulence attenuation coefficient f according to the shrinkage ratio C 2 And satisfies the following conditions:
；
turbulence at the exit of the convergent section
2, satisfying:
，
The initial given turbulence degree of 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 condition points (preferably, selecting typical points) on a one-dimensional aerodynamic force setting diagram, performing three-dimensional aerodynamic simulation through simulation software, outputting a three-dimensional simulation result, judging whether the flow field temperature and pressure unevenness 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 a preset number of data (outputting key point data) in the steps S101-S106, and if not, adjusting a flow speed limit value V 0 And a flow rate limit value V 1 Is recalculated according to the steps of S101-S106 until the value of (A) is below the specification design value.
As a specific embodiment provided by the scheme, the distance between the coarse rectifying device and the fine rectifying device is L 4 ，L 4 Take twice L 2 And maximum of 1m.
The whole technical effect is as follows:
1) The invention combines the design target of the air inlet antechamber on the basis of the prior engineering experience, more accurately determines the key parameters of the antechamber structure influencing the quality of the air inlet flow field, provides the internal incidence relation of each key parameter, a determination method and a principle, constructs the complete one-dimensional design method design related to the pneumatic design scheme of the air inlet antechamber, forms the design flow of the air inlet antechamber for the first time in the industry, and is favorable for improving the design efficiency of similar test equipment.
2) The method and the principle for determining the structural key parameters influenced by the flow field quality of the air inlet front chamber are based on the classic theory of incompressible fluid and the design and use experience of the existing equipment, and the reliability of the equipment 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 GJB4879 on the engine inlet flow field: the pressure field nonuniformity is not more than +/-1%, the temperature field nonuniformity is not more than +/-1%, the turbulence degree is not more than +/-1%, and the material comprises:
1, large angle expansion section flow field stabilizing technology
The flow velocity of the air flow in the straight section of the front chamber can be controlled to effectively reduce the pressure loss of the incoming flow, and a large-angle expansion section is required to be adopted in the engineering design due to the double limitations of the space layout and the maximum flow velocity index, so that the area expansion can be realized in a short distance, the air flow velocity at the outlet is reduced, and the static pressure is increased; however, because the expansion angle is large, boundary layer separation generally occurs in the flow process, large-area eddy which is difficult to eliminate is brought, the quality of the flow field of the front chamber is influenced, the expansion angle and the expansion area ratio are comprehensively considered in the overall design, and anti-separation measures are additionally arranged according to actual needs.
2, stable and uniform rectification technology
In order to be capable of effectively homogenizing a flow field, a steady flow section is designed at the downstream of an outlet of a front chamber expansion section, two groups of rectifying grids and damping nets are installed as main rectifying devices, and the installation form of the two rectifying devices is as follows: damping net-rectifying grid-damping net-rectifying grid. The rectification grid has the functions of guiding and dividing the air mass and straightening the streamline, and simultaneously, due to the friction effect of the wall surface on the airflow, the flow velocity distribution of the airflow is favorably improved, the attenuation of the vortex is accelerated to a certain degree, and the turbulence degree of the airflow is reduced; the function of the damping net is as follows: 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 degree is reduced, and the flow field is uniform; the method comprises the steps of carrying out iterative calculation by adopting whether pressure loss meets requirements or not, avoiding shear interference of the outlet of the rectifying grating on airflow due to the thickness of the grid plate, and reserving a certain attenuation distance of the wake vortex of the grid plate in order to effectively eliminate airflow pulsation generated by the wake and reduce turbulence in order to avoid small-scale vortex wake regions in a downstream flow field.
3, turbulence control technique
The turbulence degree is substantially the ratio of the square root average value of the pulsating speed in three directions in the flow field to the main flow average speed, the irregular movement of fluid micro-clusters is the reason of forming pulsation, the turbulence degree of the airflow is reduced by arranging a damping net, the aperture ratio and the pressure drop coefficient are configured, and the purpose of reducing the turbulence is achieved by the flow equalizing energy when the airflow flows through the damping net and is consumed.
4, designing a contraction ratio C to achieve the purpose of turbulence reduction, wherein when the airflow flows along the contraction section, the inner profile surface is continuously contracted, so that the small-scale vortex in the airflow can be compressed, bent, turned and the like, and the theorem is kept according to the intensity of the Helmholtz vortex tube; the quality of the shrink section performance depends mainly on two factors: the shrinkage ratio is the first shrinkage ratio, and the shrinkage curve is the second shrinkage ratio, so that a proper shrinkage curve is selected and a reasonable shrinkage ratio is determined according to actual use working conditions during the overall design.
In conclusion, it can be known from analysis that, in order to meet the quality requirement of the air intake flow field specified by the national military standard, the overall pneumatic design of the antechamber needs to comprehensively analyze key structural parameters influencing the flow field quality, such as expansion area ratio, expansion angle, damping network parameters, length of a static flow segment, shrinkage curve, shrinkage ratio and the like.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention 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 invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (7)
1. A flow one-dimensional pneumatic design method for an air inlet front chamber of a high-altitude simulation test bed is characterized in that the air inlet front chamber is at least provided with an expansion section, a rectification 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 an engine, and the method comprises the following steps:
s101, acquiring air flow parameters at the inlet of the expansion section, and air flow Wa and pressure loss limiting value delta P of the engine under the atmospheric air inlet condition max And the inner diameter D of the constriction 2 And 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 ；
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 through said cross-sectional area A 0 Calculating the expansion area ratio As and the inner diameter D of the steady flow section 0 Determining whether the expansion area ratio As is within a preset numerical range;
s103, acquiring the section 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 predetermined range of values, and if so, calculating the length L of the dilating segment 1 If not, adjusting the airflow parameter of S101 until the contraction ratio C is within a preset numerical range;
s104, determining the maximum size d of the particles in the airflow 0 And a rectifying device is arranged at the rectifying section to filter the particlesDetermining the size parameters and the installation position of a rectifying grid in the rectifying device;
s105, calculating the total pressure loss delta P of airflow flowing through the rectifying device under the condition of atmospheric air intake according to the size parameters of the rectifying grids in the rectifying device, and judging whether the pressure loss delta P is smaller than the pressure loss limit value delta P or not max If yes, determining the form of a contraction curve according to actual requirements, and if not, adjusting the size parameters and/or the installation position of the rectifying grids in the rectifying device until the pressure loss delta P is smaller than the pressure loss limit value delta P max ；
S106, after the form of the contraction curve is determined, the turbulence degree of the current contraction section outlet is calculated
And judging the degree of turbulence
Whether the size of the rectification grid is smaller than the design value or not, if so, generating a one-dimensional aerodynamic force setting map, and if not, 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 condition points in the one-dimensional aerodynamic force setting diagram, performing three-dimensional aerodynamic simulation, outputting a three-dimensional simulation result, judging whether the temperature and pressure unevenness of the flow field is below a standard design value or not according to the three-dimensional simulation result, if so, outputting all data or preset number of data in the S101-S106 steps, and if not, adjusting a flow speed limit value V 0 And a flow rate limit value V 1 Is recalculated according to the steps of S101-S106 until the value of (A) is below the specification design value.
2. The design method according to claim 1, wherein S102 comprises:
an air flow rate Wa satisfying:
，
is a cross-sectional area A 1 Is greater than or equal to>
Is a cross-sectional area A 0 The air density of (a);
the expanded area ratio As satisfies:
；
the inner diameter D 0 And satisfies the following conditions:
。
3. the design method according to claim 1, wherein S103 comprises:
the shrinkage ratio C satisfies:
the contraction ratio C is in the range of 7-10;
the length L 1 And satisfies the following conditions:
and theta is the expansion angle of the expansion section. />
4. The design method according to claim 1, wherein S104 comprises:
the rectifying device comprises a thick rectifying device and a thin rectifying device which are sequentially installed along the airflow direction, the thin rectifying device comprises a thin rectifying grid, and the distance L between the thin rectifying grid and the tail end of the expansion section 2 The fine rectifying device and the coarse rectifying device are provided with a coarse rectifying grid, damping nets with preset layers are mounted at air inlet ends of the fine rectifying grid and the coarse rectifying grid, mesh sizes w and wire diameters d of the damping nets are matched, and the mesh sizes w are smaller than or equal to the maximum size d of particles in air flow 0 And calculating the aperture ratio beta of the damping net 1 Coefficient of pressure drop K 1 And the turbulence attenuation coefficient f 1 Wherein:
the opening ratio beta 1 And satisfies the following conditions:
；
the damping network pressure drop coefficient K 1 Satisfies the following conditions:
，
a correction factor for sudden expansion of the gas flow during the flow;
the turbulence attenuation coefficient f 1 Satisfies the following conditions:
；
the fine rectification grid has an aperture ratio of beta 2 Coefficient of pressure drop K 2 Length L of 3 The size of the flow cross section of the air flow is w Thin and thin ×w Thin and thin And the wall thickness d of the grid sheet Thin and thin Opening ratio beta 2 Satisfies the following conditions:
，
coefficient of pressure drop K 2 Satisfies the following conditions:
，
；
the coarse rectification grid has an aperture ratio of beta 3 Coefficient of pressure drop K 3 Length L of 3 The size of the flow cross section of the air flow is w Coarse ×w Coarse And the wall thickness d of the grid sheet Coarse Open porosity beta 3 Satisfies the following conditions:
，
coefficient of pressure drop K 3 Satisfies the following conditions:
，
。
5. the design method according to claim 4, wherein S105 comprises:
the pressure loss Δ P satisfies:
determining the length L of the constant flow section from the shrinkage curve pattern 6 The form of the shrinkage curve comprises at least: a twisted pair pattern, a bicubic curve, and a bell mouth, wherein:
length L when twisted pairs are selected 6 =（0.75～1.0）D 0 Length L when choosing bicubic or bell mouth 6 =（0.5～0.75）D 0 。
6. The design method according to claim 5, wherein S106 comprises:
calculating the turbulence attenuation coefficient f according to the shrinkage ratio C 2 Satisfies the following conditions:
；
turbulence at the exit of the convergent section
2, satisfying:
And n is the number of layers of the damping net.
7. The design method of claim 6The method is characterized in that the distance between the coarse rectifying device and the fine rectifying device is L 4 ，L 4 Take twice L 2 And maximum of 1m.
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