A supersonic angular region flow vortex generator, wind tunnel and supersonic test device

Abstract

This invention provides a supersonic angular region flow vortex generator, a wind tunnel, and a supersonic testing device. The flow vortex generator combines swept-back a-shaped and b-shaped triangular prisms into an inverted L-shaped structure, and positions this inverted L-shaped structure in the angular region. Under supersonic flow fields, it can generate strong, large-scale flow vortices downstream of the angular region. The technical solution of this invention solves the technical problems of existing vortex generators, such as complex structures, inconvenient use, or inability to generate large-scale strong vortices.

Description

Technical Field

[0001] This invention relates to the field of power technology, and in particular to a supersonic angular region flow vortex generator, a wind tunnel, and a supersonic testing device. Background Technology

[0002] Due to the interaction between the internal shock wave and the boundary layer on the sidewalls, supersonic inlets generate strong directional vortices (hereinafter referred to as directional vortices) in the corner region. These vortices move downstream and interact with the shock wave train, resulting in significant non-uniformity in the flow field at the outlet of the isolation section. Studying the interaction between these directional vortices and the shock wave train is an important task in researching the performance of this type of inlet. If a direct-connection test method is used to study the interaction between the directional vortices and the shock wave train in the isolation section, a directional vortex generator is required to generate the directional vortices. Currently, researchers mainly use three types of directional vortex generators: a swivel-blade type, a V-shaped vortex generator, and a wing-blade type. Of these three types, the first type is too complex and inconvenient to use, while the second and third types have a smaller range of influence in supersonic flow fields and cannot form large-scale strong vortex structures. Summary of the Invention

[0003] This invention provides a supersonic angular region flow vortex generator, wind tunnel, and supersonic testing device, which can solve the technical problems of existing vortex generators being complex in structure, inconvenient to use, or unable to generate large-scale strong vortices.

[0004] According to one aspect of the present invention, a supersonic angular region vortex generator is provided, wherein the angular region is formed by a wall A and a wall B arranged at an angle ψ, the wall A and the wall B having a first common edge, the generator including a triangular prism a and a triangular prism b, the triangular prism a having a first prism face, a second prism face, a third prism face, a first base face and a second base face, the first prism face and the first base face having a second common edge, the first prism face and the second prism face having a third common edge, the second prism face and the first base face having a fourth common edge, the first prism face and the second base face having a fifth common edge, the prism b having a fourth prism face, a fifth prism face, a sixth prism face and a third base face, the fourth prism face and the fifth prism face having a sixth common edge, the fourth prism face and the third base face having a seventh common edge, the fifth prism face and the third base face having an eighth common edge;

[0005] The first base of prism a is set on wall B. The first prism surface is parallel to the airflow direction. The second common side coincides with the first common side. The third common side forms a first sweep angle α with the surface perpendicular to the airflow direction. The second common side forms a first preset angle θ with the fourth common side. The second prism surface is the frontal surface and the third prism surface is the backal surface.

[0006] The fourth prism face of prism b is set on the second base face of prism a to form an inverted L shape. The seventh common side coincides with the fifth common side. The sixth common side and the eighth common side form a second sweep angle ε. The sixth common side and the second common side form a second preset angle β. The seventh common side and the eighth common side form a third preset angle γ. The six prism faces are backflow surfaces.

[0007] Furthermore, the angle ψ can be an obtuse angle, a right angle, or an acute angle.

[0008] Furthermore, the first sweep angle α ranges from 0° to 60°.

[0009] Furthermore, the second sweep angle ε ranges from 45° to 90°.

[0010] Furthermore, the second preset angle β ranges from 60° to 120°.

[0011] Furthermore, the first sweep angle α is 45°, the second sweep angle ε is 70°, and the second preset angle β is 104°.

[0012] Furthermore, the first preset angle θ is set to 30°.

[0013] Furthermore, the third preset angle γ is set to 15°.

[0014] According to another aspect of the present invention, a wind tunnel is provided, wherein the wind tunnel is provided with the supersonic angular region vortex generator proposed above.

[0015] According to another aspect of the present invention, a supersonic testing apparatus is provided, comprising the supersonic angular region flow vortex generator proposed above.

[0016] The present invention provides a supersonic angular region stream vortex generator, a wind tunnel, and a supersonic testing apparatus. This stream vortex generator combines swept-back triangular prisms a and b into an inverted L-shaped structure, and positions this inverted L-shaped structure in the corner region. Under supersonic flow fields, it can generate strong, large-scale stream vortices downstream of the corner region, and can be used as a stream vortex generating device in supersonic isolation sections. This generator has a simple structure, is easy to install, and generates strong, large-scale stream vortices, making it applicable to constructing required stream vortices in various supersonic testing apparatuses. Attached Figure Description

[0017] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0018] Figure 1 A schematic diagram of a supersonic angular region flow-oriented vortex generator according to a specific embodiment of the present invention is shown;

[0019] Figure 2 A front view of a supersonic angular region vortex generator according to a specific embodiment of the present invention is shown;

[0020] Figure 3 A top view of a supersonic angular region vortex generator according to a specific embodiment of the present invention is shown;

[0021] Figure 4 A front view of a supersonic angular region vortex generator according to a specific embodiment of the present invention is shown;

[0022] Figure 5 A side view of a supersonic angular region vortex generator provided according to a specific embodiment of the present invention is shown;

[0023] Figure 6 The following are shown the various angle values ​​of the supersonic angular region flow-to-vortex generator provided according to a specific embodiment of the present invention;

[0024] Figure 7 The downstream flow field generated by the supersonic angular region vortex generator according to a specific embodiment of the present invention is shown;

[0025] Figure 8 The flow-direction vortex surface downstream of an angular vortex generator, shown in accordance with the Q criterion, is illustrated according to a specific embodiment of the invention.

[0026] Figure 9 The flow field in the corner region without the corner vortex generator installed is shown. Detailed Implementation

[0027] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0029] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0030] like Figures 1 to 5As shown, according to a specific embodiment of the present invention, a supersonic angular region vortex generator is provided. The angular region is formed by A wall 10 and B wall 20 combined at an angle ψ. A wall 10 and B wall 20 have a first common edge 1. The generator includes a triangular prism 30 and b triangular prism 40. The a triangular prism 30 has a first prism, a second prism, a third prism, a first base and a second base. The first prism and the first base have a second common edge 2. The first prism and the second prism have a third common edge 3. The second prism and the first base have a fourth common edge 4. The first prism and the second base have a fifth common edge 5. The b prism has a fourth prism, a fifth prism, a sixth prism and a third base. The fourth prism and the fifth prism have a sixth common edge 6. The fourth prism and the third base have a seventh common edge. The fifth prism and the third base have an eighth common edge.

[0031] The first base of prism a is set on wall 20 of B. The first prism is parallel to the airflow direction. The second common side 2 coincides with the first common side 1. The third common side 3 forms a first sweep angle α with the surface perpendicular to the airflow direction. The second common side 2 forms a first preset angle θ with the four common sides. The second prism is the frontal surface and the third prism is the backal surface.

[0032] The fourth prism face of prism b is set on the second base of prism a to form an inverted L shape. The seventh common side coincides with the fifth common side 5. The sixth common side 6 and the eighth common side form a second sweep angle ε. The sixth common side 6 and the second common side 2 form a second preset angle β. The seventh common side and the eighth common side form a third preset angle γ. The six prism faces are backflow surfaces.

[0033] This configuration provides a supersonic angular region flow vortex generator. This generator combines swept-back triangular prisms a and b into an inverted L-shaped structure, which is then positioned in the corner region. Under supersonic flow fields, it can generate strong, large-scale flow vortices downstream of the corner region, and can be used as a flow vortex generating device in supersonic isolation sections. This generator has a simple structure, is easy to install, and generates strong, large-scale flow vortices, making it applicable to constructing required flow vortices in various supersonic experimental devices. Compared with existing technologies, the technical solution of this invention solves the technical problems of existing vortex generators being structurally complex, inconvenient to use, or unable to generate large-scale strong vortices.

[0034] In the above embodiments, the angle ψ is an obtuse angle, a right angle, or an acute angle; the first sweep angle α ranges from 0° to 60°; the second sweep angle ε ranges from 45° to 90°; and the second preset angle β ranges from 60° to 120°. As a specific embodiment of the present invention, the first sweep angle α is 45°, the second sweep angle ε is 70°, the second preset angle β is 104°, the first preset angle θ is 30°, and the third preset angle γ is 15°. Figure 1 As shown, triangular prism a30 and triangular prism b40 are actually wedge-shaped prisms. The two swept-back wedge-shaped prisms combine to form an inverted L-shaped structure. When the inverted L-shaped structure is placed on... Figure 1 The corner region shown, and the supersonic airflow at Figure 1 When the airflow flows through the inverted L-shaped structure in the indicated direction, the shock waves generated by triangular prisms a (30) and b (40) raise the pressure inside the L-shaped structure. Furthermore, due to the sweeping effect, the airflow induces an outward-entraining vortex at the end of triangular prism b (40). This vortex detaches from the end of triangular prism b (40) and continues downstream, eventually forming a strong directional vortex. Different intensities of directional vortices can be obtained by adjusting the specific values ​​of each angle and the lengths of triangular prisms a (30) and b (40).

[0035] As a specific embodiment of the present invention, such as Figure 6 As shown, the θ angle of triangular prism a30 is 30°, and the α angle of the sweep is 45°; the γ angle of triangular prism b40 is 15°, and the ε angle of the sweep is 70°; the β angle of the combination of triangular prisms a30 and b40 is 104°. This device is placed in a 90° angle region (ψ = 90°). When the airflow passes through the angle region where the device is installed at Mach 4, it will produce the following... Figure 7 and Figure 8 The downstream vortex shown has a lateral velocity (the velocity perpendicular to the airflow direction) that can reach about 1 / 6 of the mainstream velocity. Figure 9 This is a contrasting flow field without an angular vortex generator installed. As you can see, no obvious flow vortex is generated here.

[0036] According to another aspect of the present invention, a wind tunnel is provided, in which a supersonic angular region directional vortex generator as described above is installed. Since the supersonic angular region directional vortex generator described above can generate high-intensity and large-scale directional vortices, its application in a wind tunnel can improve the testing performance of the wind tunnel.

[0037] According to another aspect of the present invention, a supersonic testing apparatus is provided, comprising the supersonic angular region flow vortex generator described above. Since the supersonic angular region flow vortex generator described above can generate high-intensity and large-scale flow vortices, its application in a supersonic testing apparatus can improve the testing performance of the supersonic testing apparatus.

[0038] In summary, this invention provides a supersonic angular region flow vortex generator, a wind tunnel, and a supersonic testing apparatus. This flow vortex generator combines swept-back a- and b-triangular prisms into an inverted L-shaped structure, and positions this inverted L-shaped structure in the angular region. Under supersonic flow fields, it can generate strong, large-scale flow vortices downstream of the angular region, and can be used as a flow vortex generating device in supersonic isolation sections. This generator has a simple structure, is easy to install, and generates strong, large-scale flow vortices, making it applicable to constructing required flow vortices in various supersonic testing apparatuses. Compared with existing technologies, the technical solution of this invention can solve the technical problems of existing vortex generators being structurally complex, inconvenient to use, or unable to generate large-scale strong vortices.

[0039] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0040] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0041] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A supersonic angular vortex generator, characterized in that, The corner region is formed by the combination of wall A (10) and wall B (20) at an angle ψ. Wall A (10) and wall B (20) have a first common edge (1). The generator includes a triangular prism (30) and b triangular prism (40). The triangular prism (30) has a first prism, a second prism, a third prism, a first base and a second base. The first prism and the first base have a second common edge (2). The first prism and the second prism have a third common edge (3). The second prism and the first base have a fourth common edge (4). The first prism and the second base have a fifth common edge (5). The b prism has a fourth prism, a fifth prism, a sixth prism and a third base. The fourth prism and the fifth prism have a sixth common edge (6). The fourth prism and the third base have a seventh common edge. The fifth prism and the third base have an eighth common edge. The first base of the prism a is set on the wall surface B (20). The first prism surface is parallel to the airflow direction. The second common side (2) coincides with the first common side (1). The third common side (3) forms a first sweep angle α with the surface perpendicular to the airflow direction. The second common side (2) forms a first preset angle θ with the four common sides. The second prism surface is the frontal surface and the third prism surface is the backal surface. The fourth prism face of the b prism is disposed on the second base surface of the a prism to form an inverted L shape. The seventh common side coincides with the fifth common side (5). The sixth common side (6) and the eighth common side form a second sweep angle ε. The sixth common side (6) and the second common side (2) form a second preset angle β. The seventh common side and the eighth common side form a third preset angle γ. The six prism faces are backflow surfaces.

2. The generator according to claim 1, characterized in that, Angle ψ can be obtuse, right, or acute.

3. The generator according to claim 2, characterized in that, The first sweep angle α ranges from 0° to 60°.

4. The generator according to claim 3, characterized in that, The second sweep angle ε ranges from 45° to 90°.

5. The generator according to claim 4, characterized in that, The second preset angle β ranges from 60° to 120°.

6. The generator according to claim 5, characterized in that, The first sweep angle α is 45°, the second sweep angle ε is 70°, and the second preset angle β is 104°.

7. The generator according to claim 6, characterized in that, The first preset angle θ is 30°.

8. The generator according to claim 7, characterized in that, The third preset angle γ is set to 15°.

9. A wind tunnel, characterized in that, The wind tunnel is equipped with a supersonic angular region vortex generator as described in any one of claims 1 to 8.

10. A supersonic testing device, characterized in that, The supersonic testing apparatus includes the supersonic angular region flow vortex generator as described in any one of claims 1 to 8.

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