CN115875132A - Inner rotation type air inlet channel based on vane type vortex generator - Google Patents
Inner rotation type air inlet channel based on vane type vortex generator Download PDFInfo
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- CN115875132A CN115875132A CN202211459126.6A CN202211459126A CN115875132A CN 115875132 A CN115875132 A CN 115875132A CN 202211459126 A CN202211459126 A CN 202211459126A CN 115875132 A CN115875132 A CN 115875132A
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Abstract
The invention provides an inward rotation type air inlet channel based on a vane type vortex generator, which comprises a compression surface, an isolation section and an inner channel positioned between the compression surface and the isolation section; the side walls at two sides of the inner channel are respectively provided with a vane type vortex generator; the vane type vortex generator is arranged in a cone-like main vortex induced by the interference of a swept shock wave of the inner rotary type inlet lip cover and a boundary layer of a side wall. The reverse flow direction vortex formed by interaction of the vortex generator and incoming flow divides the lip cover sweeping shock wave and the similar cone flow direction vortex generated by interference of the side wall boundary layer into two new vortices, and the migration accumulation of low-energy flow direction to one side of the compression surface is slowed down, so that the outlet flow field structure of the air inlet channel is effectively improved, the uniformity of outlet flow field parameter distribution is improved, and the performance of the air inlet channel is improved. Compared with the air inlet prototype scheme, the control measure provided by the invention does not need to provide extra energy, has simple structure and good economy, and plays an important role in the wide-speed-range and high-performance design of the convertible air inlet.
Description
Technical Field
The invention belongs to the field of supersonic aircraft flow control, and particularly relates to the field of inward rotation type air inlet flow control.
Background
The three-dimensional inward rotation type air inlet designed according to the streamline tracing method gradually becomes a research hotspot of various researchers by virtue of the advantages of good flow capturing characteristic, high compression efficiency, small axial size and the like. However, the inward turning type air inlet channel is influenced by flow direction vortexes induced by lip cover shock waves/side wall boundary layer interference, and a flow phenomenon that flow field parameters are unevenly distributed exists, so that the air inlet channel is difficult to start under low Mach number, and the anti-back pressure capability is poor. Therefore, it is necessary to develop a method for controlling the flow in the internal rotation type intake passage.
The current widely used flow control methods include boundary layer suction, addition of a miniature vortex generator, variable geometry profile and the like. However, these flow control methods also have certain limitations, and for the boundary layer suction method, partial flow can be lost, flow resistance can be increased, and the like while shock wave/boundary layer interference is controlled; for the control method of additionally installing the micro vortex generator, the control effect on the swept shock wave/boundary layer is poor; the flow control method of the variable geometry profile needs to install an adjusting control mechanism, and the structural complexity and weight are increased.
Disclosure of Invention
The invention provides an inward turning type air inlet based on a blade type vortex generator, aiming at better organizing complex flow induced by swept shock waves/boundary layer interference in the inward turning type air inlet, improving the aerodynamic performance of the inward turning type air inlet, improving the flow field parameter distribution and improving the total pressure recovery coefficient of the air inlet.
In order to achieve the purpose, the internal rotation type air inlet channel based on the vane type vortex generator can adopt the following technical scheme:
an inward rotation type air inlet channel based on a vane type vortex generator comprises a compression surface, an isolation section, a vane type air inlet channel positioned on the compression surface and the isolation sectionAn inner channel therebetween; the side walls at two sides of the inner channel are respectively provided with a vane type vortex generator, the two vane type vortex generators have the same structure and are bilaterally symmetrical, and the vane type vortex generators are arranged in a main vortex region induced by interference of the shock wave of the lip cover of the inner rotary type air inlet channel and a boundary layer of the side wall; the vane type vortex generator is arranged at the following positions in the flow direction: taking the central point as a reference, the horizontal length from the central point to the front edge cone-like vortex separation line accounts for 35% of the horizontal length of the cone-like vortex at the central point; the vane type vortex generator is arranged in the spanwise direction, and the height of the central point from the top of the isolation section accounts for 45% of the diameter of the isolation section by taking the central point as a reference; the installation angle of the vane type vortex generator and the horizontal direction is 10 degrees; the vane type vortex generator has the length of 7.5 delta 0 A height of 1.125 delta 0 A thickness of 0.125. Delta 0 Wherein δ 0 Is the local boundary layer thickness.
Further, the air inlet channel is a supersonic internal rotation type air inlet channel.
Furthermore, the Mach number M of the inward rotation type air inlet channel design d =6.0 and is obtained using a streamline tracing technique based on the inner shrinkage reference flow field.
Furthermore, the throat and the outlet of the inner rotary type air inlet are circular in cross section, the diameter of the cross section of the throat is 56.8mm, the total contraction ratio of the air inlet is 6.4, the inner contraction ratio is 1.9, the length-diameter ratio of the isolation section is 8.8, and the expansion ratio is 1.24.
Furthermore, the vane type vortex generator adopts an equal-thickness flat plate structure, and the front edge and the rear edge of the vane type vortex generator are subjected to arc passivation treatment.
Has the advantages that: compared with the traditional flow control technology, the vane type vortex generator provided by the invention has the advantages that the induced reverse flow vortex promotes momentum mixing of the boundary layer and the main flow, the similar cone flow vortex is divided into two parts, and the migration accumulation of low-energy flow to one side of the compression surface is slowed down, so that the anti-reverse pressure gradient capability of the boundary layer is improved, and the total pressure recovery coefficient of the air inlet channel is improved. The control method has the advantages of simple structure, good economy, simple processing technology and good control effect without additional energy, so that the blade type vortex generator is used for controlling the complex shock wave/boundary layer interference in the inward turning type air inlet channel, and the flow field quality is improved.
Drawings
Fig. 1 is a three-dimensional schematic diagram of an arrangement scheme of an internal rotation type air inlet based on a vane type vortex generator.
Fig. 2 is a partially enlarged view of the installation position of the vane type vortex generator in fig. 1.
Fig. 3 is a schematic cross-sectional view of the center plane of the air scoop of the present invention.
Fig. 4 is a perspective view of a vane type vortex generator.
Fig. 5 is a schematic view of the installation position of the vane type vortex generator of the present invention.
FIG. 6 is a numerical simulation of the wall streamline of the vortex generator without blades.
FIG. 7 is a graph comparing the inlet exit Mach number and total pressure recovery for an un-vaned vortex generator and a vaned vortex generator according to the present invention.
Detailed Description
Referring to fig. 1 to 5, an embodiment of an internal rotation type inlet based on a vane type vortex generator is shown. The adversion formula intake duct includes outer compression face 1, vane type vortex generator 2, intake duct lip 3, and the dissection is imported 4, and dissection 5, dissection export 6, parting line 7, attaches line 8 again.
The blade type vortex generator is selected as the first key of the invention. The vane type vortex generator 2 has the advantages of simple structure, good economy, simple processing technology and the like, and can obtain better control effect without additional energy. The vane type vortex generator has the length of 7.5 delta 0 A height of 1.125 delta 0 A thickness of 0.125 delta 0 Wherein δ 0 Is the local boundary layer thickness. The definition of the thickness of the local boundary layer is the wall-to-wall distance when the local flow velocity reaches 0.99 times of the main flow velocity, and the thickness can be measured according to the numerical simulation flow field result when no vane type vortex generator is added.
The installation of the vane type vortex generator 2 in the main vortex region induced by the interference of the rotating inlet lip shock wave and the side wall boundary layer is the second key point of the invention. The main vortex area is an area where vortices appear in the air inlet channel under the flight working condition and is obtained according to a simulation result. As in this embodiment, the region between the line 7 and the reattachment line 8 in fig. 5 and 6 is the primary vortex region. The reverse flow vortex induced by the vane type vortex generator 2 installed in the region divides the conical flow vortex generated by the interference of the lip cover shock wave and the side wall boundary layer into two new vortices, the vortex generator 2 hinders the development of the flow vortex to one side of a compression surface, the migration accumulation of low-energy flow to one side of the compression surface is slowed down, and the uniformity of the flow field parameter distribution of the flow channel in the air inlet channel is improved.
The mounting position of the vane type vortex generator 2 in the spanwise direction takes a central point as a reference, and the height of the central point from the top of the isolation section accounts for 45 percent of the diameter of the isolation section 5. I.e. W in FIG. 5 1 =0.45W, W is the diameter of the isolation segment 5, W 1 The height of the center point from the top of the isolation section 5.
The fourth key of the present invention is that the horizontal length of the blade type vortex generator 2 from the center point to the leading edge cone-like vortex separation line 7 accounts for 35% of the horizontal length of the cone-like vortex at the center point, based on the center point. I.e. L in FIG. 3 1 ＝0.35L 2 ，L 1 Is the horizontal length from the center point to the leading edge of the separation line of cone-like vortex, L 2 Is the length in the horizontal direction of the cone-like vortex passing through the central point of the vane type vortex generator.
The installation angle of the vane type vortex generator 2 to the horizontal direction is 10 degrees, which is the fifth key of the invention. Namely in fig. 5
The five key points are all absent, and a complete technical scheme is formed. The technical scheme can improve the pneumatic performance of the inward rotation type air inlet channel, improve the flow field parameter distribution and improve the total pressure recovery coefficient of the air inlet channel. The technical effect is verified by an application example applied to a specific inward turning type air inlet.
Examples
At a certain placeMach number M of meter d =6.0, the inward turning type air inlet is designed by direct streamline tracing, the throat and outlet cross sections of the inward turning type air inlet are circular, the diameter of the throat cross section is 56.8mm, the total contraction ratio of the air inlet is 6.4, the inner contraction ratio is 1.9, the length-diameter ratio of the isolation section is 8.8, and the expansion ratio is 1.24. The vane type vortex generator adopts a flat plate structure with equal thickness, the front edge and the rear edge are subjected to arc passivation treatment, and the vane type vortex generator is ensured to be basically vertical to the local molded surface. Local boundary layer delta 0 8mm, blade vortex generator size in delta 0 Dimensionless is performed for the reference. The vane type vortex generator has the length of 7.5 delta 0 A height of 1.125 delta 0 A thickness of 0.125. Delta 0 . Fig. 7 compares the distribution of the mach number and the total pressure recovery coefficient of the front and rear inlet duct isolation sections of the vane-type vortex generator, and the result shows that: compared with the scheme without the blade type vortex generator, the large-scale low-speed low-total pressure area on the compression surface side disappears, and the crescent high-speed high-total pressure area becomes full, which shows that the uniformity of the parameter distribution of the outlet flow field of the isolation section is better improved, and the pneumatic performance of the air inlet channel is improved.
The invention embodies a number of methods and approaches to this solution and the foregoing is only a preferred embodiment of the invention. It should be noted that modifications and adaptations can be made by those skilled in the art without departing from the principle of the present invention, and should be considered as within the scope of the present invention. All the components not specified in the present embodiment can be realized by the prior art.
Claims (5)
1. An inner rotary type air inlet channel based on a vane type vortex generator comprises a compression surface, an isolation section and an inner channel positioned between the compression surface and the isolation section; the method is characterized in that: the side walls at two sides of the inner channel are respectively provided with a vane type vortex generator, the two vane type vortex generators have the same structure and are symmetrical left and right, and the vane type vortex generators are arranged in a main vortex area induced by interference of an inner rotary type air inlet lip cover shock wave and a side wall boundary layer;
the vane type vortex generator is arranged at the following positions in the flow direction: taking the central point as a reference, the horizontal length from the central point to the front edge cone-like vortex separation line accounts for 35% of the horizontal length of the cone-like vortex at the central point; the vane type vortex generator is arranged in the spanwise direction, and the height of the central point from the top of the isolation section accounts for 45% of the diameter of the isolation section by taking the central point as a reference; the installation angle of the vane type vortex generator and the horizontal direction is 10 degrees;
the vane type vortex generator has the length of 7.5 delta 0 A height of 1.125 delta 0 A thickness of 0.125 delta 0 Wherein δ 0 Is the local boundary layer thickness.
2. The internal turning intake duct based on a vane-type vortex generator as claimed in claim 1, wherein: the air inlet channel is a supersonic speed inward rotation type air inlet channel.
3. The internal turning intake duct based on a vane-type vortex generator as claimed in claim 2, wherein: the designed Mach number M of the inward rotation type air inlet d =6.0 and is obtained using a streamline tracing technique based on the inner shrinkage reference flow field.
4. The internal turning intake duct based on a vane-type vortex generator as claimed in claim 3, wherein: the inner rotation type air inlet channel is circular in throat and outlet cross section, the diameter of the throat cross section is 56.8mm, the total contraction ratio of the air inlet channel is 6.4, the inner contraction ratio is 1.9, the length-diameter ratio of the isolation section is 8.8, and the expansion ratio is 1.24.
5. The internal turning inlet duct based on a vane type vortex generator as claimed in claim 4, wherein: the vane type vortex generator adopts an equal-thickness flat plate structure, and circular arc passivation treatment is carried out on the front edge and the rear edge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202211459126.6A CN115875132A (en) | 2022-11-17 | 2022-11-17 | Inner rotation type air inlet channel based on vane type vortex generator |
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| CN202211459126.6A CN115875132A (en) | 2022-11-17 | 2022-11-17 | Inner rotation type air inlet channel based on vane type vortex generator |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117874929A (en) * | 2024-03-12 | 2024-04-12 | 中国航发四川燃气涡轮研究院 | Design method for profile of swirler vane with flow stability |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117874929A (en) * | 2024-03-12 | 2024-04-12 | 中国航发四川燃气涡轮研究院 | Design method for profile of swirler vane with flow stability |
| CN117874929B (en) * | 2024-03-12 | 2024-06-04 | 中国航发四川燃气涡轮研究院 | Design method for profile of swirler vane with flow stability |
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