A convergent-divergent nozzle with shock wave bypass structure

Abstract

The invention relates to a retractable nozzle adopting a shock wave bypass structure. , a shock wave is generated at the throat, and shoots to the wall of the expansion section, wherein: the expansion section has a groove on the wall of the shock wave incidence position, the groove is continuous along the circumference of the expansion section, the groove communicates with the bypass channel, and the bypass channel Arranged outside the expansion section, the front end communicates with the channel, and the rear end extends to the outlet of the nozzle. The shock wave enters the bypass channel from the channel and is discharged through the rear end of the bypass channel. In the present invention, a groove is opened on the wall surface of the first incident position of the expansion section after the shock wave is generated, and the main flow is deflated, and the wave and part of the air flow are introduced into the bypass channel to prevent continuous reflection in the main flow channel.

Description

technical field [0001] The invention relates to the field of aero-engine structural design, in particular to a retractable nozzle adopting a shock wave bypass structure. Background technique [0002] With the continuous development of aero-engines, the thrust-to-weight ratio is getting higher and higher, and the tail jet velocity is getting higher and higher. The supersonic nozzle with supersonic exhaust outlet has become an inevitable development direction. For the expansion section of the retractable nozzle, the mainstream flow state is supersonic. Due to its special flow and structural characteristics, multiple oblique shock waves will be generated in the mainstream channel, and the oblique shock waves will continue to reflect downstream when they hit the wall, and finally A series of complex wave systems are formed. When the shock wave intensity is strong, it will have a greater impact on the mainstream, which will increase the flow loss of the nozzle and reduce the thr...

AI Technical Summary

Problems solved by technology

At the same time, when a series of wave systems hit the wall, a reverse pressure gradient will be generated, causing the flow separation of the boundary layer; for the case of air film cooling on the wall, it will also affect the outflow of cold air and the coverage of the air film, thereby reducing the cooling efficiency

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