CN113051670A - RBF network-based three-dimensional inward rotation type air inlet channel flow field distortion suppression method - Google Patents
RBF network-based three-dimensional inward rotation type air inlet channel flow field distortion suppression method Download PDFInfo
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Abstract
The invention discloses a three-dimensional internal rotation type air inlet channel flow field distortion inhibiting method based on a Radial Basis Function (RBF) network, which comprises the steps of preliminarily designing the shape of an air inlet channel based on the osculating flow principle, the low energy flow state is identified to obtain the low energy flow distribution condition on each section, the osculating surface pressure is adjusted based on the RBF network, the original coordinates are replaced by the position coordinates passing through the RBF interpolation points to form a new air inlet channel shape, the extra energy loss and flow field distortion caused by the overlarge circumferential pressure gradient of the air inlet channel can be avoided on the design level, and combines the distance attenuation characteristic of a Radial Basis Function (RBF) network, on the premise of ensuring the second-order conductibility of the contour line of the kiss section and the continuous flow field parameters, and pressure correction is carried out on the distortion generating area, and the internal flow loss of the air inlet channel is reduced, the effective flow area is enlarged and the comprehensive compression efficiency of the air inlet channel is improved by eliminating the circumferential pressure gradient.
Description
Technical Field
The invention relates to the technical field of performance optimization design of high-speed air inlet channels, in particular to a three-dimensional inward rotation type air inlet channel flow field distortion suppression method based on a Radial Basis Function (RBF) network.
Background
The three-dimensional inward rotation type air inlet channel has become a mainstream development direction of a high-speed air inlet channel due to the advantages of high compression efficiency, high flow capture, low external resistance, weakened angle area flow and the like, and the distortion of the air inlet channel is one of important internal flow performance indexes influencing the propulsion efficiency of an aircraft; the effect of distortion on performance is mainly reflected in three aspects: 1) the pressure field generated by distortion drives the near-wall low-energy flow to further develop, so that the total pressure loss is aggravated; 2) the interference of the distorted convection field restrains the effective flow area of the air inlet channel, so that the starting capability of the air inlet channel is reduced; 3) because the low energy flow ratio is increased, the internal flow field of the air inlet channel is damaged, so that the back pressure resistance of the air inlet channel is reduced, and the internal resistance is increased; under the conditions of hypersonic incoming flow and passivation of the front edge, the thickness of low-energy flow is suddenly increased, and more severe distortion is easily caused; therefore, the inhibition of the internal flow distortion of the air inlet is the key for ensuring the efficient work of the down-draft propulsion system in the wide speed range.
The essence of the inlet channel distortion is that low-energy flow is driven by pressure gradient to converge and increase; the existing method for inhibiting distortion mainly comprises boundary layer suction, round/oval air inlet outlet arrangement, inlet speed field improvement and the like: 1) the core of boundary layer suction is to discharge low-energy flow near the wall through pressure difference, but for the condition of thicker low-energy flow, the area of a suction opening is larger, so that the structural complexity is increased, and serious potential intensity hazard is more easily generated; 2) the core of improving the inlet velocity field is that the bulge is used for generating transverse pressure gradient to discharge low-energy flow, the low-energy flow discharge and inlet flow field uniformity can be considered, but the distortion cause can not be eliminated according to the transition of an internal flow field and an external flow field, and the method has limited applicability; 3) the core of arranging the outlet of the circular/elliptical air inlet channel is to increase the pressure of the position where the low-energy flow is located so that the low-energy flow is not converged, but because the method only considers the pressure gradient of the outlet and is purely geometric correction, and the elliptical shape limits the flexibility of the design of the air inlet channel; the above methods suppress the inlet distortion to some extent, but have not fundamentally removed the cause of the distortion.
At present, a three-dimensional internal rotation type air inlet channel is generally designed by adopting a kiss-cut flow principle (a three-dimensional complex curved surface design is simplified to a series of two-dimensional kiss-cut surface designs which are arranged in the circumferential direction), and when a layer is designed, although the equal wave intensity of an inlet (namely no circumferential pressure gradient) is ensured by each kiss-cut surface which is arranged in the circumferential direction, as each kiss-cut surface still has a circumferential pressure gradient and drives low-energy flow to move along the circumferential direction, a three-dimensional internal rotation type air inlet channel flow field distortion suppression method based on an RBF network is urgently needed to solve the problems.
Disclosure of Invention
The invention provides a three-dimensional inward rotation type air inlet channel flow field distortion inhibiting method based on an RBF network, which can carry out pressure correction on a distortion generating area, reduce the inner flow loss of an air inlet channel, enlarge the effective flow area and improve the comprehensive compression efficiency of the air inlet channel by eliminating the circumferential pressure gradient.
In order to achieve the purpose, the invention provides the following technical scheme: a three-dimensional inward rotation type air inlet channel flow field distortion suppression method based on an RBF network comprises the following steps:
s1, identification of low-energy flow areas: preliminarily designing the shape of the air inlet channel based on the osculating flow principle to obtain the low-energy flow distribution condition on each section;
s2, performing pressure gradient adjustment based on the RBF network, wherein the pressure gradient adjustment comprises the following steps:
1) arranging the air inlet channels according to the kiss cut surfaces 1-m based on preliminary design, dispersing the contour lines of the air inlet channels into n points according to equal proportion, correspondingly obtaining pressure values pi of the points, and establishing a mapping pi (theta, h), wherein theta is the installation angle of the kiss cut surfaces, and h is the height of a certain point of the contour of the kiss cut surfaces;
2) given differential pressure threshold value pirThe distance between circumferentially adjacent kiss sections is rRBFThe pressure difference between the two points inside the device is checked;
3) if Δ π > πrAnd then, starting a correction step: preset interpolated radius rRBFBased on rRBFThe inner point pair interpolates the point with the over-limit of delta pi and repeatsAssigning values to finally obtain a new molded surface of the compression section of the air inlet channel;
and S3, replacing the original coordinates with the position coordinates of the RBF interpolation points to form a new air inlet duct model.
Further, in step S1, performing numerical simulation on the preliminarily designed air inlet duct model to obtain an internal flow field performance library of the air inlet duct, and making a velocity cloud chart of each section along the way in flow field post-processing software, wherein the area with the inlet duct outlet profile σ less than or equal to 0.1 is used as a standard to determine that the area is low-energy flow.
Further, defining the low-power flow states comprises a uniform distribution state, a uniform distribution-accumulation state conversion state and a accumulation state transition state, and determining the width W and the central position coordinate Ψ of each low-power flow region.
Further, the criterion of the low energy flow form is as follows: if delta W/W is less than or equal to 5 percent and psi is less than or equal to 3 percent, judging that the section is in a uniform distribution state; if delta W/W is more than 5% and psi is less than or equal to 3%, judging that the section is in a uniform distribution-accumulation state conversion state; if the delta W/W is less than or equal to 5 percent and psi is more than 3 percent, the segment is judged to be in the stacking state transition state.
Further, for the uniform distribution state, the middle section V-X distribution and the low energy flow rate m are calculated1(x1) And maximum value of circumferential pressure difference pim，1Further fitting a curve m of the low energy flow changing with the flow direction of the unit width1(x) (ii) a For the uniform distribution-accumulation state conversion state, the uniform distribution state and the uniform distribution state are the same airflow, and the low-energy flow rate m is calculated2(x2) And a pressure difference of the cross section of the transition pi2(ii) a For the stack state transition state, calculating a low energy flow rate m3(x3) And a pressure difference of the cross section of the transition pi3。
Furthermore, in the RBF network, the flow direction spacing of each point is delta X, the circumferential spacing is delta theta, the discrete spacing ratio is delta X/delta theta, the value range is 1-5, and r isRBFThe value range is delta X-5 delta X.
Further, in step 3), interpolating the point where Δ π is out of limit, wherein the interpolation formula is:
wherein, UjAt any flow field parameter, θijJ is the reciprocal of the interpolation radius, and j is the node number whose distance to the ith point is smaller than the interpolation radius R.
Compared with the prior art, the invention has the beneficial effects that: according to the invention, through the identification of the low-energy flow area and the regulation of the osculating surface pressure based on the RBF network, the extra energy loss and flow field distortion caused by overlarge circumferential pressure gradient of the air inlet channel can be avoided on the design level, and the pressure correction is carried out on the distortion generating area on the premise of ensuring the second-order conductibility of the contour line of the osculating surface and the continuous flow field parameters by combining the distance attenuation characteristic of the Radial Basis (RBF) network, so that the internal flow loss of the air inlet channel is reduced, the effective flow area is enlarged and the comprehensive compression efficiency of the air inlet channel is improved by eliminating the circumferential pressure gradient.
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The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention.
In the drawings:
FIG. 1 is a flow chart of a three-dimensional inward rotation type air inlet channel flow field distortion suppression method based on an RBF network;
FIG. 2 is a schematic illustration of the mechanism of action of the circumferential pressure gradient of the present invention on low energy flow;
FIG. 3 is a flow chart of the low energy flow partitioning of the present invention;
FIG. 4 is a schematic diagram of the RBF interpolation-based pressure gradient trimming method of the present invention.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are described herein for the purpose of illustration and explanation and not limitation.
Example (b): as shown in fig. 1, a flow chart of a three-dimensional inward rotation type air inlet channel flow field distortion suppression method based on an RBF network is shown, wherein the right side of the flow chart is a novel three-dimensional inward rotation type air inlet channel design flow of weak circumferential pressure difference, and the left side of the flow chart is a osculating surface pressure adjustment flow based on the RBF network; the three-dimensional inward rotation type air inlet channel flow field distortion suppression method based on the RBF network comprises two processes of low energy flow partition identification and osculating surface pressure adjustment based on the RBF network;
as shown in fig. 2, for low-energy flow partition identification, firstly, preliminarily designing an air inlet duct model based on the osculating flow principle, performing numerical simulation on the air inlet duct model to obtain an internal flow field performance library of the air inlet duct, making a velocity cloud chart of each section along the way in flow field post-processing software (such as Tecplot), and judging that the air inlet duct model is low-energy flow by taking a region with an outlet profile sigma of the air inlet duct being less than or equal to 0.1 as a standard to obtain the low-energy flow distribution condition on each section; defining the low-energy flow states including an equispaced state, an equispaced-stacked state conversion state and a stacked state transition state, and determining the width W and the central position coordinate psi of each low-energy flow region; the criterion of the low energy flow form is as follows: if delta W/W is less than or equal to 5 percent and psi is less than or equal to 3 percent, judging that the section is in a uniform distribution state; if delta W/W is more than 5% and psi is less than or equal to 3%, judging that the section is in a uniform distribution-accumulation state conversion state; if the delta W/W is less than or equal to 5 percent and psi is more than 3 percent, the segment is judged to be in the stacking state transition state.
Referring to FIG. 3, it is a schematic diagram (incoming flow Mach number 6.0, diameter 5.0mm passivation front edge, half model) of the action mechanism of circumferential pressure gradient to low energy flow, wherein, for the uniform distribution state, as shown in the front end of the lip on the upper surface of the inlet, because the difference of circumferential contraction ratio is small, and the three-dimensional compression effect is not strong, the circumferential pressure gradient in this region is small, the thickness of low energy flow is uniformly increased along the flow direction, and the middle section V-X distribution, low energy flow m and flow m are calculated1(x1) And maximum value of circumferential pressure difference pim，1Further fitting a curve m of the low energy flow changing with the flow direction of the unit width1(x) (ii) a For the uniform distribution-accumulation state conversion state, as shown by the upper surface of the internal pressure section of the air inlet channel, the three-dimensional compression effect is enhanced, the width and the height of low-energy flow are reduced and increased, the center of the low-energy flow moves from two sides to a middle section, the low-energy flow is developed into the accumulation state from the uniform distribution state and is the same as the uniform distribution state, and the low-energy flow rate m is calculated2(x2) And a pressure difference of the cross section of the transition pi2(ii) a For the bulk state transition, as shown by the lower surface of the inlet, where a large front-to-back stretch ratio of the lip is seen, a three-dimensional compressionThe contraction effect is strong, the wave system interference in the corner region is serious, a larger circumferential pressure gradient exists, the low-energy flow rapidly develops into a stacking state from the point A at the most front edge of the lip mouth, then the low-energy flow thickens along the flow direction and migrates from two sides to the middle region, and the low-energy flow m is calculated3(x3) And a pressure difference of the cross section of the transition pi3Thereby obtaining the quantization result in the dotted box in fig. 2.
Referring to the right part in fig. 1, pressure gradient adjustment is performed, firstly, an air inlet channel is designed based on the preliminary design and is arranged according to a kiss section 1-m, the contour line of the air inlet channel is dispersed into n points according to equal proportion, pressure values pi of all the points are correspondingly obtained, a mapping pi is established as f (theta, h), wherein theta is the installation angle of the kiss section, h is the height of a certain point of the contour of the kiss section, RBF interpolation has distance attenuation characteristics, so that the setting of the interpolation radius is a main factor influencing the interpolation result, in an RBF network, the flowing direction interval of each point is delta X, the circumferential interval is delta theta, the dispersion interval ratio is delta X/delta theta, the value range is 1-5, r is equalRBFThe value range is delta X-5 delta X; then a given pressure difference threshold value pirThe distance between circumferentially adjacent kiss sections is rRBFThe pressure difference between the two points inside the device is checked; if Δ π > πrAnd then, starting a correction step: preset interpolated radius rRBFBased on rRBFInterpolating and re-assigning the points with the delta pi overrun to finally obtain a new molded surface of the compression section of the air inlet channel, as shown in fig. 4, wherein the interpolation formula is as follows:
wherein, UjAt any flow field parameter, θijAnd j is the number of the node with the distance from the ith point to the point smaller than the interpolation radius R, and the flow field parameters of all the nodes within the interpolation radius are weighted and averaged by an interpolation formula to obtain the flow field parameter of the ith point. Wherein the weight is the reciprocal of the distance from the node to the ith point; and finally, replacing the original coordinates with the position coordinates of the RBF interpolation points to form a new air inlet duct model.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A three-dimensional inward rotation type air inlet channel flow field distortion suppression method based on an RBF network is characterized by comprising the following steps: the method comprises the following steps:
s1, identification of low-energy flow areas: preliminarily designing the shape of the air inlet channel based on the osculating flow principle to obtain the low-energy flow distribution condition on each section;
s2, performing pressure gradient adjustment based on the RBF network, wherein the pressure gradient adjustment comprises the following steps:
1) arranging the air inlet channels according to the kiss cut surfaces 1-m based on preliminary design, dispersing the contour lines of the air inlet channels into n points according to equal proportion, correspondingly obtaining pressure values pi of the points, and establishing a mapping pi (theta, h), wherein theta is the installation angle of the kiss cut surfaces, and h is the height of a certain point of the contour of the kiss cut surfaces;
2) given differential pressure threshold value pirThe distance between circumferentially adjacent kiss sections is rRBFThe pressure difference between the two points inside the device is checked;
3) if Δ π > πrAnd then, starting a correction step: preset interpolated radius rRBFBased on rRBFInterpolating and re-assigning the points with the delta pi overrun to finally obtain a new molded surface of the compression section of the air inlet channel;
and S3, replacing the original coordinates with the position coordinates of the RBF interpolation points to form a new air inlet duct model.
2. The RBF network-based three-dimensional inward rotation type inlet channel flow field distortion suppression method as claimed in claim 1, wherein: in step S1, performing numerical simulation on the preliminarily designed inlet duct model to obtain an internal flow field performance library of the inlet duct, and performing a velocity cloud chart of each section along the way in flow field post-processing software, wherein the area with the inlet duct outlet profile σ less than or equal to 0.1 is used as a standard to determine that the area is low-energy flow.
3. The RBF network-based three-dimensional inward rotation type inlet channel flow field distortion suppression method as claimed in claim 2, wherein: defining the low-energy flow states comprises a uniform distribution state, a uniform distribution-accumulation state conversion state and a accumulation state transition state, and determining the width W and the central position coordinate psi of each low-energy flow region.
4. The RBF network-based three-dimensional inward rotation type inlet channel flow field distortion suppression method as claimed in claim 3, wherein: the criterion of the low energy flow form is as follows: if delta W/W is less than or equal to 5 percent and psi is less than or equal to 3 percent, judging that the section is in a uniform distribution state; if delta W/W is more than 5% and psi is less than or equal to 3%, judging that the section is in a uniform distribution-accumulation state conversion state; if the delta W/W is less than or equal to 5 percent and psi is more than 3 percent, the segment is judged to be in the stacking state transition state.
5. The RBF network-based three-dimensional inward rotation type inlet channel flow field distortion suppression method as claimed in claim 2 or 3, wherein: for the uniform distribution state, calculating the V-X distribution of the middle section and the low energy flow rate m1(x1) And maximum value of circumferential pressure difference pim，1Further fitting a curve m of the low energy flow changing with the flow direction of the unit width1(x) (ii) a For the uniform distribution-accumulation state conversion state, the uniform distribution state and the uniform distribution state are the same airflow, and the low-energy flow rate m is calculated2(x2) And a pressure difference of the cross section of the transition pi2(ii) a For the stack state transition state, calculating a low energy flow rate m3(x3) And a pressure difference of the cross section of the transition pi3。
6. The RBF network-based three-dimensional inward rotation type inlet channel flow field distortion suppression method as claimed in claim 1, wherein: in the RBF network, the flow direction spacing of each point is delta X, the circumferential spacing is delta theta, the discrete spacing ratio is delta X/delta theta, the value range is 1-5, and r isRBFThe value range is delta X-5 delta X.
7. The RBF network-based three-dimensional inward rotation type inlet channel flow field distortion suppression method as claimed in claim 1, wherein: in step 3), interpolating the point where Δ pi is out of limit, wherein the interpolation formula is:
wherein, UjAt any flow field parameter, θijJ is the reciprocal of the interpolation radius, and j is the node number whose distance to the ith point is smaller than the interpolation radius R.
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| CN115795915A (en) * | 2023-01-09 | 2023-03-14 | 中国人民解放军国防科技大学 | Method, device and equipment for quickly evaluating performance of inward-turning air inlet and storage medium |
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