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Plasma excitation-based method for restraining separation of boundary layer in air inlet passageway

A boundary layer separation and plasma technology, which is used in ramjet engines, mechanical equipment, etc., can solve the problems of boundary layer separation at the inlet of the air inlet, achieve rapid response, improve performance, and reduce total pressure loss and the effect of flow loss

Inactive Publication Date: 2014-12-17
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a method for suppressing boundary layer separation of the intake port based on plasma excitation, so as to solve the problem of boundary layer separation at the entrance of the intake port when flying at a non-design Mach number

Method used

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  • Plasma excitation-based method for restraining separation of boundary layer in air inlet passageway
  • Plasma excitation-based method for restraining separation of boundary layer in air inlet passageway

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specific Embodiment approach 1

[0014] Specific implementation mode one: combine figure 1 and figure 2 Describe this implementation mode, this implementation mode is realized through the following steps:

[0015] Step 1: Machining a horizontal hole 1-4 parallel to the central line N-N of the engine inlet 1 in the wall thickness of the engine inlet 1, from the inlet to the outlet on the tapered surface A at the entrance of the engine inlet 1 Three radial passages perpendicular to and connected to the horizontal hole 1-4 are sequentially processed, namely the first radial passage 1-1, the second radial passage 1-2 and the third radial passage 1-3, the first The inner surfaces of the radial channel 1-1, the second radial channel 1-2, the third radial channel 1-3 and the horizontal through hole 1-4 are all coated with a ceramic film;

[0016] Step 2, the plasma generating device 4 is arranged in the horizontal hole 1-4, and the input end of the horizontal hole 1-4 is connected to the outlet 4-1 on the plasma ...

specific Embodiment approach 2

[0020] Specific implementation mode two: combination figure 1 Describe this embodiment, the first radial channel 1-1, the second radial channel 1-2, the third radial channel 1-3 and the inner surface of the horizontal through hole 1-4 in step 1 of this embodiment The thickness of the ceramic membrane is 0.1 mm to 0.2 mm. The ceramic film realizes the insulation effect between the plasma and the metal structure of the inlet channel, and the ceramic film can generate secondary electron emission under the collision of the plasma, which is beneficial to the stable propagation of the plasma in the channel. Other steps are the same as in the first embodiment.

specific Embodiment approach 3

[0021] Specific implementation mode three: combination figure 1 Describe this embodiment, the first radial channel 1-1, the second radial channel 1-2, the third radial channel 1-3 and the inner surface of the horizontal through hole 1-4 in step 1 of this embodiment The thickness of the ceramic film is 0.15 mm. The ceramic film realizes the insulation effect between the plasma and the metal structure of the inlet channel, and the ceramic film can generate secondary electron emission under the collision of the plasma, which is beneficial to the stable propagation of the plasma in the channel. Other steps are the same as in the first embodiment.

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Abstract

The invention provides a plasma excitation-based method for restraining the separation of a boundary layer in an air inlet passageway, and relates to a method for restraining the separation of the boundary layer in the air inlet passageway of a scramjet engine to improve the performance of the air inlet passageway, which is designed for solving the problem of the separation of the boundary layer generated at an inlet of the air inlet passageway in the case of flying under non-designed mach number. The method comprises the following steps of: 1, plating a ceramic film on the inner surface of each of a first radial passageway, a second passageway, a third passageway and a horizontal through hole; 2, connecting an input end of the horizontal through hole with an outlet of a plasma generator; 3, arranging two external electrodes on the surface of a conical surface, and embedding two internal electrodes in the conical surface; 4, spraying the plasma generated by the plasma generator at the inlet to generate jet flow type plasma; and 5, accelerating the jet flow of the plasma under the actions of electric fields of the external electrodes and the internal electrodes, accelerating the flowing of the airflow of the boundary layer, and restraining the separation of the boundary layer. The method is used for restraining the separation of the boundary layer in the air inlet passageway of the scramjet engine.

Description

technical field [0001] The invention relates to a method for suppressing the separation of the boundary layer of the intake port of a scramjet engine and improving the performance of the intake port. Background technique [0002] The hypersonic inlet is an important part of the scramjet engine, and its performance directly affects the overall performance and operational reliability of the engine. The scramjet engine operates in the Mach number range, and the performance of the inlet port changes drastically: the performance of the inlet port is optimal at the design Mach number; when the Mach number is lower than the design Mach number, the boundary layer flow on the conical surface of the inlet port is prone to separation , resulting in a decrease in the total pressure recovery coefficient of the inlet and a decrease in the flow capture coefficient; when the Mach number is higher than the design Mach number, separation of the boundary layer in the compression section of the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K7/10
Inventor 唐井峰于达仁鲍文李西鹏刘鹏
Owner HARBIN INST OF TECH
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