Side plate with overflow gap binary hypersonic air inlet channel

An air inlet and supersonic technology, which is applied to the air inlet of the turbine/propulsion device, engine components, combustion air/combustion-air processing, etc. Flow coefficient, improve performance, improve the effect of flow field

Active Publication Date: 2019-12-20
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, in recent years, there are few related studies on the sidewall boundary la

Method used

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  • Side plate with overflow gap binary hypersonic air inlet channel
  • Side plate with overflow gap binary hypersonic air inlet channel
  • Side plate with overflow gap binary hypersonic air inlet channel

Examples

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[0030] Next, the present invention will be further explained in conjunction with the drawings.

[0031] Such as figure 1 As shown, a supersonic dual air inlet of a side plate includes two symmetrical side plates 2, a compression surface 3, and a lip cover 7; an inner channel is formed between the side plate 2, the lip cover 7 and the compression surface 3 5. The side plate 2 includes a front edge 1 of the front edge of the side plate 2. One end of the front edge 1 is connected to the front edge of the lip cover 7, and the other end is connected to any point on the front edge of the compression surface 3. Connected. In the case of the present invention, preferably, both ends of the front edge edge 1 are tangent to the front edge of the compression surface 3 and connected to the front edge of the lip cover 7 respectively.

[0032] In order to reduce the influence of the supersonic dual inlet angle zone and the boundary layer of the sidewall surface on the flow field in the inlet, i...

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Abstract

The present invention discloses a side plate with an overflow gap binary hypersonic air inlet channel. The air inlet passage body includes a lip cover, a compression surface, two symmetrical side plates; the lip cover, the two symmetrical side plates and the compression surface form an air flow inner channel; the two side plates are symmetrically provided with an overflow gap, and the overflow gapalong the compression surface direction; and the supersonic binary air inlet channel arranged on the side plate through the overflow gap, using airflow air inlet internal and external pressure difference, the side plates and the compression surface boundary of the corner region, a boundary layer of the side plate of the low-speed flow discharge port the outer side plate. The side plate with the overflow gap binary hypersonic air inlet channel increasing the total pressure recovery coefficient of the air inlet channel and the flow coefficient, improving the structure of the internal flow fieldof the air inlet channel.

Description

technical field [0001] The invention relates to the field of aircraft design, and relates to a supersonic binary air inlet. Background technique [0002] The supersonic inlet uses the shock wave to decelerate and pressurize the high-speed airflow. It converts part of the kinetic energy of the high-speed incoming flow into the pressure energy of the gas, and provides low-speed high-pressure gas that meets the flow requirements and flow field requirements for the subsequent components of the engine. When designing a supersonic inlet, it is required to provide high-quality air that meets certain flow field quality and flow requirements to downstream components with the smallest possible total pressure loss. Usually, supersonic inlets are evaluated by performance parameters such as total pressure recovery coefficient and flow coefficient. Road performance is good or bad. [0003] When the airflow flows along the wall surface, due to the viscous effect, a boundary layer is gener...

Claims

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Application Information

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IPC IPC(8): F02C7/04
CPCF02C7/04
Inventor 谢旅荣李晓驰郭金默赵有喜汪昆张兵
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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