A cavity structure capable of reducing drag in internal flow and scramjet engine

Abstract

The invention discloses a cavity structure capable of internal flow and drag reduction and a scramjet engine. The cavity structure includes a cavity front wall surface, a cavity bottom wall surface and a cavity rear edge wall surface, the cavity front edge wall surface, The bottom wall of the concave cavity and the rear edge wall of the concave cavity are connected in sequence and arranged on the wall of the combustion chamber along the direction of the incoming flow of the engine. It is smoothly connected with the bottom wall of the concave cavity and the wall of the combustion chamber. The concave cavity structure optimizes the concave cavity rear edge curved wall structure based on the flow field structure and pressure distribution in the concave cavity, which can not only optimize the negative thrust distribution on the concave cavity rear edge wall, effectively reduce the internal resistance of the engine, but also weaken the transonic shock wave , effectively reduce the internal flow loss of the engine, and at the same time, due to the smooth transition of the wall of the rear edge of the cavity, the thermal stress on the wall of the rear edge of the cavity is concentrated, and the existing active cooling thermal protection and passive thermal protection technologies can be well applied.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a cavity structure capable of internal flow and drag reduction and a scramjet engine. Background technique [0002] Hypersonic aircraft is a strategic high-tech that can achieve high-speed defense penetration, 2-hour global reach, and low-cost space entry. Its development will change the shape of future warfare. pose a new threat to our national security. As the best alternative power plant for hypersonic air-breathing flight, the scramjet has become a research hotspot in various aerospace powers. As the core component of the scramjet engine, the performance of the supersonic combustion chamber directly determines the success or failure of the entire engine development. Due to the high incoming flow velocity and short residence time, the successful design of a supersonic combustor must rely on reliable flame stabilization technology. The wall cavity can effectively stabilize t...

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Problems solved by technology

[0004] However, the existing wall design of the rear edge of the concave cavity does not consider the internal flow characteristics of the engine and the pressure distribution in the cavity, and strong shock waves will be introduced into the flow channel, resulting in a large total pressure loss. The negative thrust generated is still large

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