CN115221811B - Internal wave-taking air inlet channel design method based on circumferential azimuth pressure gradient correction - Google Patents
Internal wave-taking air inlet channel design method based on circumferential azimuth pressure gradient correction Download PDFInfo
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Abstract
The invention discloses an internal wave-taking air inlet channel design method based on circumferential azimuth pressure gradient correction, which comprises the steps of adopting a concept of intimate axial symmetrical flow to design an internal wave-taking air inlet channel, using an Euler incompressible flow equation to calculate circumferential velocity items among all intimate planes, using the circumferential velocity to represent azimuth pressure gradient, adding the circumferential velocity items to consider the influence of the azimuth pressure gradient in the original design method, then adopting a streamline tracking method to obtain a new molded surface of the internal wave-taking air inlet channel, and finally, smoothing the new surface of the internal wave-taking air inlet channel to avoid molded surface deformity caused by abrupt variation of the azimuth pressure gradient, solving the azimuth pressure gradient problem of the three-dimensional internal wave-taking air inlet channel, and enabling the internal wave-taking air inlet channel after the circumferential pressure gradient correction to show better performance in the aspects of total pressure recovery and flow uniformity.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a supersonic and hypersonic air suction type aircrafts, and specifically relates to an internal wave-taking air inlet channel design method based on circumferential azimuth pressure gradient correction.
Background
Studies have shown that hypersonic air inlets have an important effect on the performance of engines and aircraft, wherein the air inlets play a major role in thrust of engines, directly affecting lift-drag ratio. The design objective of the high efficiency hypersonic air intake is to capture, compress air, properly adjust flow field uniformity, provide thermodynamically efficient air to the combustion chamber at predictable mass flow rates, and minimize degradation of the air intake performance under off-design conditions and work stably.
In the design process of the air inlet, when the shapes of the inlet and the outlet are pre-designated, the concept of cross section transition is adopted to obtain the shape of the REST air inlet. REST inlets, while meeting profile transitions, do not meet aerodynamic transitions. While streamline tracking air inlets such as Busemann air inlets can meet aerodynamic transition, the inlet and outlet shapes can be obtained simultaneously, only one can be selected, and then the other can be formed according to streamline tracking. And the three-dimensional internal wave-taking air inlet SCIW with controllable cross section, also called internal wave-taking air inlet IWI, can meet the complex geometric transition and realize acceptable aerodynamic transition. Although SCIW inlet successfully achieves the goals of cross-sectional geometry transition and complete upstream flow capture, the total pressure recovery is reduced compared to Busemann inlet due to the design approach that ignores the lateral flow effects. Since total pressure recovery plays a vital role in thrust and efficiency of the aircraft, the lower the total pressure recovery, the lower the thrust, and therefore it is the most important parameter in the design of the air intake duct.
The concept of an internal-waverider intake, one of the internal-waverider intake types, is basically a combination of the close axisymmetric flow method and the streamline tracking method. This idea relies on the characteristics provided during the design of a waverider aircraft to attach a shock wave at the inlet of the air intake, the shape riding on the shock wave, and its lower surface fully attached to the shock wave. Although the air inlet is a supercharging part, the inlet of the air inlet is sealed by shock waves, the captured streamline cannot overflow, and the flow capture rate of the air inlet is improved to the maximum extent and is close to 1.
The concept of intimate axisymmetric flow is introduced as a generalization of the concept of intimate cone, wherein the concept of intimate axisymmetric flow is abbreviated as OA, wherein the intimate cone is abbreviated as OC, for flexural shock wave design in waverider design. The concept of intimate axisymmetric flow converts a three-dimensional inlet channel into a series of local two-dimensional slices or intimate planes, while in-plane flow is a local two-dimensional flow, and a streamline tracking method is used to form walls on each intimate plane. Whereas the OA method is an approximation method that ignores the effect of lateral flow between adjacent planes on circumferential direction, introducing the problem of azimuthal pressure gradients that negatively affect port performance.
Disclosure of Invention
The invention provides an internal wave-taking air inlet channel design method based on circumferential azimuth pressure gradient correction, which aims to solve the problem of azimuth pressure gradient of a three-dimensional internal wave-taking air inlet channel.
In order to achieve the above purpose, the invention provides the following technical scheme that the internal wave-taking air inlet channel design method based on circumferential azimuth pressure gradient correction comprises the following steps:
S1, designing an internal wave-taking air inlet channel by adopting an original close axisymmetric flow method, wherein a basic flow field is close along the azimuth direction, generating a three-dimensional geometric shape of the internal wave-taking air inlet channel, and finally obtaining flow information of all points on a close plane;
S2, calculating circumferential velocity terms among all the close planes by using an Euler incompressible flow equation, and expressing an azimuth pressure gradient by using the circumferential velocity, wherein the Euler incompressible flow equation is as follows:
dV2=-2dp/ρ
Wherein p is pressure, ρ is density, and V is speed;
S3, adding a circumferential speed item in the original design method to consider the influence of an azimuth pressure gradient, updating the axial speed U and the speed V R of an ICFC+flow field used in the original close axis symmetrical flow method by using a speed correction vector, and calculating the corrected speeds U, V and w of the point J under XYZ coordinates;
s4, using new speeds u, v and w for each close plane J, and applying a streamline tracking method along the direction of the flow direction i to obtain an internal wave-taking air inlet channel after pressure gradient correction;
S5, the new surface of the internal wave-taking air inlet channel is subjected to smoothing treatment, so that profile deformity caused by abrupt change difference of azimuth pressure gradient is avoided, and a new air inlet channel model is formed.
Preferably, in step S1, the internal-wave-intake flow field includes a streamline extracted from the icfc+ elementary stream, truncated Busemann and ICFA elementary flow fields are generated using a feature line method, and then Busemann compression faces are pushed down by using a streamline function.
Preferably, in step S1, the shapes of the inlet and outlet of the intake duct are specified in advance as a circle and a half rectangle having the same internal contraction ratio.
Preferably, in step S1, a series of local two-dimensional streamline slices extracted from the icfc+ basic flow field are used as the intimate planes, and converted into a three-dimensional inlet channel profile by using a streamline tracking method.
Preferably, the method for calculating the velocity correction vector includes the following steps:
1) After the flow information of all points on the close plane is obtained through the step S1, calculating and considering the speed correction between the directions of two adjacent points J+1 and J-1 of the point J on each close plane slice, wherein the flow direction is the i direction, and the circumferential direction is the J direction;
2) Projecting the velocity correction on ZY and XY planes to calculate a velocity component;
3) The velocity correction vector is projected on the considered plane of closeness J in directions R and R N, where R is normal to the azimuth plane ZY, and the velocity correction vector is calculated.
Preferably, in step S2, an intimate plane is included, wherein the local flow is a two-dimensional flow, and the position of the point and the flow information are known.
Preferably, in step S4, the velocity at the new coordinates is calculated by using an inverse distance weighted interpolation method.
Preferably, in step S5, the origin points of all the close planes in the J direction are updated by using the maximum radius correction and the average angle correction in each azimuth J direction.
Compared with the prior art, the method has the beneficial effects that the Euler incompressible flow equation is adopted to calculate the transverse flow speed, the azimuth pressure gradient is corrected to the original design level, then the three-dimensional streamline is replaced by the two-dimensional streamline of the close plane, in addition, the comparison with the original internal wave-taking air inlet channel shows that the internal wave-taking air inlet channel after the circumferential pressure gradient correction has better performance in the aspects of total pressure recovery and flow uniformity, and the circumferential pressure difference between the close sections can be eliminated through the pressure gradient correction, so that the circumferential migration of the near-wall low-energy flow is avoided, and the internal flow distortion of the air inlet channel is further enhanced.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate the invention and together with the embodiments of the invention, serve to explain the invention.
In the drawings:
FIG. 1 is a schematic diagram of a circumferential pressure gradient modified close-axis symmetric flow method of the present invention;
FIG. 2 is a schematic diagram of the close axisymmetry theory of the internal waverider intake of the present invention;
FIG. 3 is a graph of three local points (i to i+1) on the surface of a shock wave generated by the close-plane of a line segment of the present invention;
FIG. 4 is an close-up plane projection view and a velocity projection view on the ZY plane of the present invention, wherein (a) is the close-up plane projection view and (b) is the velocity projection view;
FIG. 5 is a schematic view of the new surface point after the circumferential pressure gradient correction of the generated occlusal plane J;
FIG. 6 is a flow chart of an algorithm of the present invention for performing the method of the present invention;
FIG. 7 is a flowchart of an algorithm of the method of the present invention;
FIG. 8 is a schematic view of the internal waverider intake of the rectangular inlet and outlet of the present invention;
FIG. 9 is a diagram of a pressure corrected internal waverider intake (PWI) and an original internal waverider intake (OWI) of the three-dimensional structure of the present invention;
FIG. 10 is a diagram of a pressure corrected internal waverider intake (PWI) and an original internal waverider intake (OWI) of the two-dimensional structure of the present invention;
FIG. 11 is a schematic view of the internal waverider intake of the circular port of the present invention;
FIG. 12 is a diagram of a pressure corrected internal waverider intake (PWI) and an original internal waverider intake (OWI) of the three-dimensional structure of the present invention.
Detailed Description
The preferred embodiments of the present invention will be described below with reference to the accompanying drawings, it being understood that the preferred embodiments described herein are for illustration and explanation of the present invention only, and are not intended to limit the present invention.
The invention provides an internal waverider air inlet design method based on circumferential azimuth pressure gradient correction, which is characterized in that an azimuth pressure gradient effect is included in an intimate axisymmetric flow concept of an internal waverider air inlet, and is realized by considering transverse flow between intimate planes caused by pressure difference in azimuth direction and then compensating the transverse flow into a speed for forming a molded surface through a streamline tracking method, and in order to achieve the aim, the influence of the azimuth pressure gradient is converted into the speed by utilizing Euler incompressible flow equation at each point locally, wherein Euler incompressible flow equation is as follows:
dV2=-2dp/ρ
where p is pressure, ρ is density, and V is velocity. Since the ICFC+ basic flow field of the internal waverider inlet is non-viscous, the Euler incompressible flow equation is used. Thus, as shown in fig. 1, the present invention adopts the following technical steps:
1. An internal wave-taking air inlet channel is designed by adopting an original close axisymmetric flow method, a basic flow field is close along the azimuth direction, a three-dimensional geometric shape is generated, and flow information of all points on a close plane is obtained, as shown in figure 2;
2. After the flow information of all points on the close plane is obtained through the step 1, the velocity correction between the two adjacent points j+1 and J-1 azimuth directions of the point J on each close plane slice is calculated and considered, as shown in fig. 3. This figure shows three points on three closely planar slices of a segment of line (i and i+1) in the direction of flow i. These three points lie in the azimuthal direction J, the point considered here being point J on the plane of close proximity J. The invention applies Euler incompressible flow equation dV 2 = -2 dp/p between point J, J+1 and point J, J-1, respectively, and gives the formula:
3. The velocity correction is projected on the ZY and XY planes as shown in fig. 3 using:
4. the velocity correction vector is projected on the considered close plane J in directions R and R N, wherein R is normal;
5. The U and V R speeds for the considered points are updated as:
The speeds U and V R are the speeds of the axial direction and the R direction of the ICFC+ flow field used in the original intimate axis symmetric flow method respectively, and the speeds are updated respectively along with the influence of the pressure gradient and then the new speeds in the XYZ coordinates are obtained, namely U, V and w. The other variables are calculated according to the following relationship:
6. And (3) applying a streamline tracking method to each close plane J along the direction of the flow direction i by using new speeds u, v and w to obtain a new molded surface of the internal wave-taking air inlet channel, wherein as shown in fig. 5, the new y and z coordinates of each point are calculated as follows:
(a) Through this step, new speed u, v, w is assigned to the i-1 point at the original xyz position;
(b) At the new xyz position, inverse distance weighted interpolation is used between points (i-2;i-1 (new) and i-1 (old)) to determine the velocity of point i-1;
Wherein the method comprises the steps of In order to calculate the value of the value,D is the distance of n data points from the estimated n points, p=2, which is a known value.
(C) After the speed u, v and w of the i-1 point is calculated, the flow line equation is usedCalculating the position of the point i;
(d) Repeating the previous steps to calculate all points on the intimate plane J;
(e) For each of the planes of close proximity, the leading edge point is connected to the shock wave, from which point calculation begins, since the intensity of the shock wave is constant, at which point there is no pressure gradient.
7. The entire method is repeated for all the planes of close along the azimuth J direction, and fig. 6 outlines a new internal waverider intake design algorithm.
8. The pressure gradient correction must include some treatment to avoid any abrupt profile changes caused by reflected shock interactions, as well as changes in the subsurface pressure near the throat caused by flow reflections. Therefore, in order to obtain a smooth surface, in each azimuth J direction, the original point positions y and z of all the close planes in the J direction are updated with the maximum radius correction (Δr max) and the average angle correction (Δθ av). This process is repeated for all the intimate planar slices in the downstream direction i. The correction of the directional pressure gradient can generate a transverse velocity component, so that the flow line regenerated by adopting the flow line tracking method has transverse displacement, and the transverse displacement does not occur on the same constant close plane as the original method, thereby forming a three-dimensional flow line.
Wherein the method comprises the steps ofΘ=tan -1 (y/z) is the radius and angle of the point on the close planar slice, as in fig. 4a. The subscripts "old" and "new" denote the value obtained using the original design method and the value obtained using the current method, respectively.
9. Finally, the new surface point of the pressure gradient corrected internal waverider intake is calculated by:
embodiment 1 As shown in FIG. 7, the technical method for designing the hypersonic internal wave-taking air inlet channel adopted by the invention is as follows:
(1) Selecting design conditions, namely, the incoming flow Mach number is 6.0, the static pressure is 1170pa, and the static temperature is 225.25K;
(2) Utilizing a characteristic line method to generate a truncated Busemann flow field and an ICFA basic flow field;
(3) Combining the truncated Busemann flow field with the ICFA base flow field on the basis of matching the angle of the limited truncated Busemann flow field with the angle of a single ray of the ICFA flow field, and creating an ICFC base flow field;
(4) Pushing Busmann the compression surface downwards by using a line function to enable the characteristic line of the ICFC flow field to be converged at an incident point, and improving the ICFC basic flow field into an ICFC+ basic flow field;
(5) After adopting 2D CFD numerical simulation, extracting ICFC+ basic flow field streamline;
(6) The selected inlet and outlet planes are shown in fig. 8;
(7) Obtaining the close plane point and flow information by adopting a close axisymmetric flow method;
(8) Calculating a new velocity component, i.e., a circumferential velocity between the intimate planes in the azimuth direction, using the pressure and density of each point on the intimate planes;
(9) Updating the speed of each point on the oscillometric plane;
(10) Calculating the speed under the new coordinates by using an inverse distance weighted interpolation method;
(11) Determining the geometry of a hypersonic internal wave-taking air inlet channel by adopting a streamline tracking method;
(12) Smoothing the created geometric configuration to avoid geometric deformity;
(13) As shown in fig. 9 and 10, obtaining a hypersonic internal wave-taking air inlet three-dimensional geometric final design;
(14) CFD simulation is carried out on the designed hypersonic internal wave-taking air inlet channel, and the result is shown in the following table:
The average performance parameters of the mass flow of the wave-taking air inlet channel in the outlet section (M e,πe,σe,φ％,and Aσ percent is Mach number, pressure ratio, total pressure recovery, flow coefficient proportion and area proportion that the total pressure recovery sigma of the outlet section is more than 0.7:
example 2 as a verification, the method of the present invention was applied to a round inlet, and it was found that the inlet shape did not undergo the expected change compared to the inlet designed by the original method. Since the circular air inlet channel has no circumferential pressure gradient, the method of the invention is verified, and the technical design method is as follows:
(1) Repeating the steps (1) to (5) of the design in example 1;
(2) The inlet and outlet planes selected by the circular inlet channel are shown in figure 11;
(3) Repeating the steps (7) to (12) of the design in example 1;
(4) And obtaining the three-dimensional geometrical final design of the hypersonic internal wave-taking air inlet channel, as shown in figure 12.
It should be noted that the foregoing description is only a preferred embodiment of the present invention, and the present invention is not limited to the foregoing embodiments, but may be modified or substituted for some of the features described in the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The internal wave-taking air inlet channel design method based on circumferential azimuth pressure gradient correction is characterized by comprising the following steps of:
S1, designing an internal wave-taking air inlet channel by adopting an original close axisymmetric flow method, wherein a basic flow field is close along the azimuth direction, generating a three-dimensional geometric shape of the internal wave-taking air inlet channel, and finally obtaining flow information of all points on a close plane;
S2, calculating circumferential velocity items among all the close planes by using an Euler incompressible flow equation, and expressing azimuth pressure gradient by using the circumferential velocity;
S3, adding a circumferential speed item in the original design method to consider the influence of an azimuth pressure gradient, updating the axial speed U and the speed V R of an ICFC+flow field used in the original close axis symmetrical flow method by using a speed correction vector, and calculating the corrected speeds U, V and w of the point J under XYZ coordinates;
s4, using new speeds u, v and w for each close plane J, and applying a streamline tracking method along the direction of the flow direction i to obtain an internal wave-taking air inlet channel after pressure gradient correction;
S5, the new surface of the internal wave-taking air inlet channel is subjected to smoothing treatment, so that profile deformity caused by abrupt change difference of azimuth pressure gradient is avoided, and a new air inlet channel model is formed.
2. The method of claim 1, wherein in step S1, the internal-wave-intake flow field includes a streamline extracted from the ICFC+ elementary flow, the truncated Busemann and ICFA elementary flow fields are generated by using a feature line method, and then Busemann compression faces are pushed down by using a streamline function.
3. The method for designing an internal waverider intake duct based on correction of circumferential azimuthal pressure gradient of claim 1, wherein in step S1, the shape of the intake duct inlet and outlet are pre-designated as circular and semi-rectangular with the same internal contraction ratio.
4. The method of claim 1, wherein in step S1, a series of local two-dimensional streamline slices extracted from the ICFC+ basic flow field are used as the close planes, and the local two-dimensional streamline slices are converted into the three-dimensional air inlet profile by using a streamline tracking method.
5. The method for designing an internal waverider intake based on correction of a circumferential azimuthal pressure gradient according to claim 1, wherein the method for calculating the velocity correction vector comprises the steps of:
1) After the flow information of all points on the close plane is obtained through the step S1, calculating and considering the speed correction between the directions of two adjacent points J+1 and J-1 of the point J on each close plane slice, wherein the flow direction is the i direction, and the circumferential direction is the J direction;
2) Projecting the velocity correction on ZY and XY planes to calculate a velocity component;
3) The velocity correction vector is projected on the considered plane of closeness J in directions R and R N, where R is normal to the azimuth plane ZY, and the velocity correction vector is calculated.
6. The method of claim 1, wherein in step S2, the method further comprises the step of including an intimate plane, wherein the local flow is a two-dimensional flow, and the position and flow information of the point are known.
7. The method for designing an internal waverider intake duct based on correction of circumferential azimuthal pressure gradient of claim 1, wherein in step S4, velocity at the new coordinate is calculated by using an inverse distance weighted interpolation method.
8. The method for designing an internal waverider intake based on the correction of the circumferential azimuthal pressure gradient of claim 1, wherein in step S5, the original point positions of all the close planes in the J direction are updated by using the maximum radius correction and the average angle correction in each azimuthal J direction.
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| CN103662087A (en) * | 2013-12-11 | 2014-03-26 | 厦门大学 | Hypersonic aerocraft and air inlet internal and external waverider integrated design method |
| WO2022095163A1 (en) * | 2020-11-06 | 2022-05-12 | 南京航空航天大学 | Internal-external flow decoupled dual-waverider high-speed airbreathing aircraft and generation method therefor |
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| CN103174520B (en) * | 2013-04-03 | 2015-02-11 | 南京航空航天大学 | Subsonic outflowing high external pressure internal waverider type air inlet and designing method thereof |
| CN113306740B (en) * | 2021-04-08 | 2023-03-21 | 厦门大学 | Two-stage compression inner waverider air inlet channel inverse design method based on bending shock wave theory |
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| CN103662087A (en) * | 2013-12-11 | 2014-03-26 | 厦门大学 | Hypersonic aerocraft and air inlet internal and external waverider integrated design method |
| WO2022095163A1 (en) * | 2020-11-06 | 2022-05-12 | 南京航空航天大学 | Internal-external flow decoupled dual-waverider high-speed airbreathing aircraft and generation method therefor |
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