Dynamic distortion vortex simulator and working method thereof
A simulator and vortex technology, applied in special data processing applications, geometric CAD, design optimization/simulation, etc., can solve problems such as deviation of advance matching performance, achieve simple operation, improve experimental efficiency and accuracy, and simple structure. Effect
Pending Publication Date: 2021-05-14
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
This distortion simulation method simplifies the three-dimensional unsteady distorted flow field at the outlet section of the inlet to a two-dimensional steady distortion map, which is different from the real distorted flow field, and the obtained launch matching performance also deviates from the real value.
Method used
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Embodiment 1
[0050] Below in conjunction with accompanying drawing, technical scheme of the present invention is further described
[0051] The invention provides a dynamic distortion vortex simulation device, such as figure 1 As shown, its structure includes a process inlet 1, a slotted bypass column 2, a rotating slot grid 3, a high-speed motor 4, a connecting bolt 5, an air induction channel 6, and a high-pressure air source 7; the slotted bypass column 2 is installed Inside the process inlet 1, it is fixed by connecting bolts 5, and the rotating slit grid 3 is installed in the cavity of the slit around the flow column, and is connected with the high-speed motor 4, and the high-pressure gas source 7 provides high-pressure gas, and passes through the bleed air channel 6 into the cavity around the flow column.
[0052] Such as figure 2 As shown, the process inlet is cylindrical, the inner diameter of the process inlet is d, the length l of the process inlet is selected with reference t...
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The invention relates to a dynamic distortion vortex simulator. The dynamic distortion vortex simulator structurally comprises a process air inlet channel, a slotted streaming column, a rotating slit grid, a high-speed motor, a connecting bolt, an air entraining channel and a high-pressure air source; the slotted streaming column is installed in the process air inlet channel and fixed through a connecting bolt, the rotating slit grid is installed in a cavity of the slotted streaming column and connected with the high-speed motor, the high-speed motor is fixed to the process air inlet channel through a boss, and the air entraining channel introduces a high-pressure air source into the cavity of the slotted streaming column; when incoming flow passes through the streaming column, a series of large-scale vortexes are generated at the downstream of the streaming column, then unsteady pulse jet flow is formed by using the rotating seam grid and a high-pressure air source in a cavity of the streaming column, the scale and the frequency of the downstream vortexes are adjusted, and a dynamic flow structure similar to a distortion flow field at an outlet of a real air inlet channel is formed; the problem that the dynamic distortion intensity simulated by an existing distortion simulator is not enough is solved, and the incoming matching process is simulated more truly.
Description
technical field [0001] The invention relates to a dynamic distortion vortex simulator and a working method thereof, which belong to the technical field of aeroengine inlet / engine matching. Background technique [0002] Modern advanced military aircraft require high maneuverability and high stealth performance. In order to meet the constraints of high maneuverability and high stealth, large-curvature S-curved inlets are generally used. Due to the lip separation of the inlet port and the strong internal reverse pressure gradient, the internal flow of the S-curved inlet deteriorates, forming large-scale separated vortices, resulting in outlet distortion. The distortion of the inlet outlet will affect the stable operation of the downstream fan, and in severe cases, it will cause stall and surge. Therefore, in order to ensure the stable and efficient operation of the engine, it is necessary to conduct a sufficient intake port engine matching test. [0003] At present, the launc...
Claims
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IPC IPC(8): G06F30/15G06F30/28
CPCG06F30/15G06F30/28
Inventor 黄国平刘泽鹏王岩松
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS