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Bulge air inlet based on plasma synthetic jet and boundary layer control method

A technology of synthesizing jet and plasma, which is applied to the combustion, fluid flow, mechanical equipment and other directions of the intake port of the power plant, can solve the problems of weakening the weight and structure of the bulge, increasing the weight of the bulge, and consuming the flow rate captured by the intake port. The effect of eliminating additional mass to optimize structure, enhance boundary layer capabilities, and improve performance

Active Publication Date: 2019-06-18
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, because the boundary layer deflation technology is an active control technology, it will consume the capture flow of the intake port, and setting a complex deflation structure will increase the weight of the bulge and generate deflation resistance, thereby weakening the weight and weight of the bulge. Structural advantages

Method used

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  • Bulge air inlet based on plasma synthetic jet and boundary layer control method
  • Bulge air inlet based on plasma synthetic jet and boundary layer control method
  • Bulge air inlet based on plasma synthetic jet and boundary layer control method

Examples

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Effect test

Embodiment 1

[0033] Please combine figure 1 and figure 2 As shown, it is an embodiment of a bulge inlet channel based on plasma synthetic jet provided by the present invention. The bulge air intake includes an inner channel surface 4 , a lip cover 3 , a bulge profile 2 , and a body plane 5 . The lip cover 3 is located outside the inner channel surface 4 , and the inner channel of the air inlet is formed between the lip cover 3 and the inner channel surface 4 . The bulge surface 2 serves as a connection surface between the inner channel surface 4 and the body plane 5 , and the bulge surface 2 forms a bulge outward relative to the body plane 5 . In this embodiment, several fluidic actuators 1 are also provided, and the fluidic actuators 1 are arranged below the bulge profile and below the body plane. in:

[0034] If the jet actuator 1 is arranged under the bulge surface 2, the jet outlet of the jet actuator 1 is arranged on the bulge surface and / or the front edge of the bulge; if the je...

Embodiment 2

[0045] Please combine image 3 and Figure 4 As shown, it is the second embodiment of the bulging air inlet based on the plasma synthetic jet of the present invention. This embodiment has roughly the same structure as the first embodiment, and also includes the inner channel surface 4, the lip cover 3, and the bulging surface 2. , Body plane 5, and is provided with a number of jet actuators 1, and the difference from Embodiment 1 is that the jet actuators 1 are only arranged below the bulge profile. The jet outlet of the jet actuator 1 is arranged on the bulge surface and / or the front edge of the bulge; if the jet outlet is arranged on the bulge surface, the direction of the jet outlet is set along the bulge line, and the spanwise position of the jet actuator 1 does not exceed the edge of the lip cover 3 ; If the jet outlet is arranged on the front edge of the bulge, the jet direction is set along the exciter outlet profile.

[0046] The method for controlling the boundary l...

Embodiment 3

[0051] Please combine Figure 5 and Image 6 As shown, it is the third embodiment of the bulging air inlet based on the plasma synthetic jet of the present invention, which has roughly the same structure as the first embodiment, and also includes the inner channel surface 4, the lip cover 3, and the bulging surface 2 , the body plane 5, and is provided with a number of jet actuators 1, and the difference from Embodiment 1 and Embodiment 2 is that the jet actuators 1 are only arranged below the body plane. And the angle between the jet outlet direction and the incoming airflow is 90°, and the spanwise position of the jet actuator 1 does not exceed the edge of the lip cover 3.

[0052] The method for controlling the boundary layer of the bulging air inlet of the above embodiment is:

[0053] (1) Arrange the position and angle of the jet actuator according to the flow field of the bulging inlet.

[0054] (2) When the inlet works at the design Mach number, the jet exciter is co...

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Abstract

The invention discloses a bulge air inlet based on a plasma synthetic jet and a boundary layer control method. The bulge air inlet is capable of, through using the momentum effect of a high-speed jetgenerated by a jet exciter, replenishing energy to a low energy flow accumulated in a shock wave / boundary layer interference section induced by a bulge and promoting the low energy flow to be reattached, and enabling the jet to drive the low energy flow at a front edge of the bulge to be displaced to two sides, thereby reinforcing displacement boundary layer capacity of the bulge air inlet, and realizing active control to the bulge air inlet. The exciter is arranged below the bulge or arranged below a machine body. A jet outlet direction is along a bulge molded line, or along an exciter outletmolded line. The bulge air inlet is capable of solving problems of a traditional bulge air inlet active control method that a jet speed is low, a control force is not strong, and an additional air source is needed, and providing a general source-free active flow control method for efficient wide-envelope work of this type of the air inlet.

Description

technical field [0001] The invention belongs to the field of supersonic flow control, and in particular relates to a method for controlling a supersonic bulging inlet and an inlet boundary layer based on a plasma synthetic jet. Background technique [0002] The bump inlet is a new type of inlet, and the bump inlet can obtain good performance without adopting boundary layer separation and blowing / suction measures. The key component of the bump inlet is its bulging compression surface, which is usually obtained by streamline tracing design through the supersonic inviscid single-stage conical flow field. Although the Bump inlet has many advantages compared with the traditional inlet, in the actual working process, the shock wave / body boundary layer interference induced by the bulge inevitably exists at the leading edge of the inlet, and the existence of this interference will As a result, a large amount of low-energy flow accumulates on the front edge of the bulge, which chang...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02F15D1/00
Inventor 张悦高婉宁谭慧俊王超陈亮马志明
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS