Air inlet channel

Abstract

The invention discloses an air inlet channel, which is applied to an engine and comprises a blunt leading edge, wherein the blunt leading edge comprises a smooth transition section located in the center and straight sections connected with the two ends of the smooth transition section; the blunt leading edge is provided with an air inlet and an air outlet, the air inlet and the air outlet are connected through a flow guide channel at the position of the blunt leading edge, and the distance between the air inlet and the center of the smooth transition section is less than the distance between the air outlet and the center of the smooth transition section. In the blunt leading edge provided by the invention, the flow guide channel is formed in the blunt leading edge, static pressure difference between upstream and downstream of a flow field is utilized, flow self-circulation can be achieved without an additional power device and an energy supply system, the structure is simple, the implementation is easy, the airflow at the high pressure position is guided to the low pressure position, the distance between shock waves at the center of the smooth transition section and the wall surface is reduced, the wall pressure of the blunt leading edge and the heat flow load peak value are effectively reduced, and then the performance of the air inlet channel is improved.

Description

technical field [0001] The invention relates to the technical field of high Mach number aerodynamics, in particular to an air inlet. Background technique [0002] High-Mach number aircraft has extremely important military and civilian values. The scramjet engine is one of the most potential power methods to achieve this high-speed flight. As an important part of the scramjet engine, the air inlet is directly related to its performance. Efficiency of the entire propulsion system. In recent years, the inwardly rotating inlet combined with curved surface shock wave and isentropic compression has attracted extensive attention because of its excellent performance such as high airflow compression rate and low total pressure loss. [0003] However, due to the high sweep of the leading edge of the inward-turning inlet, a V-like overflow is formed at the intersection of the root of the leading edge. In the actual design, due to the consideration of aerodynamic thermal protection an...

AI Technical Summary

Problems solved by technology

However, after the leading edge of the inlet is passivated, the shock wave no longer attaches to the body, and the appearance of the detached shock wave leads to a complex wave system structure near the overflow, which may also cause wall pressure, heat flow rise, and unsteady oscillation of the flow , which not only poses a severe challenge to the structural strength of the intake overflow, but also affects the performance of the intake

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