Low-resistance and high-efficiency scramjet engine thrust chamber integrated design method

Abstract

The invention discloses a low-resistance and high-efficiency scramjet engine thrust chamber integrated design method. A thrust chamber obtained through the design method comprises a combustion chamberwall face, a concave cavity front edge wall face, a concave cavity bottom wall face, a first compression section wall face, a second compression section wall face, a first expansion section wall faceand a second expansion section wall face. The molded line of the first compression section wall face and the molded line of the second expansion section wall face are spline curves, and the molded line of the second compression section wall face and the molded line of the first expansion section wall face are arc lines with equal radiuses. The concave cavity bottom wall face, the first compression section wall face, the second compression section wall face, the first expansion section wall face and the second expansion section wall face are smoothly connected. In the thrust chamber, an enginecombustion chamber and a spray pipe are in continuous transition and are integrally designed, deep matching of inlet parameters of the combustion chamber and the spray pipe is achieved, and the thrust performance of the spray pipe is effectively improved; and thrust distribution of thrust chamber components is effectively optimized, shock waves are eliminated, internal flow losses are reduced, and engine performance is improved.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a low-resistance and high-efficiency scramjet thrust chamber integrated design method. 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 flow velocity and short residence time, the scramjet usually adopts a concave cavity structure to stabilize the flame and organize the combustion. The high-temperature gas generated by the comb...

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Problems solved by technology

[0003] In the current design of the scramjet engine, the combustion chamber and the nozzle are designed in separate segments, and there is a problem of mismatching flow parameters, which is not conducive to the improvement of the combustion efficiency and thrust efficiency of the engine; the cavity placed in the supersonic airflow is the The high-pressure combustion zone in the cavity directly forms a force opposite to the direction of propulsion on the wall of the trailing edge, and the negative thrust formed on the wall of the trailing edge is the main source of resistance in the combustion chamber

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