A low-resistance and high-efficiency scramjet thrust chamber integrated design method

Abstract

The invention discloses a low-resistance and high-efficiency scramjet thrust chamber integrated design method. The thrust chamber obtained by the design method includes the wall surface of the combustion chamber, the wall surface of the front edge of the cavity, the bottom wall surface of the cavity, the wall surface of the first compression section, The wall surface of the second compression section, the wall surface of the first expansion section and the wall surface of the second expansion section; the profile line of the wall surface of the first compression section and the profile line of the wall surface of the second expansion section are all spline curves, and the profile line of the wall surface of the second compression section and the wall surface of the second expansion section are all spline curves. The profile line of the wall surface of the first expansion section is an arc line with the same radius; the bottom wall surface of the cavity, the wall surface of the first compression section, the wall surface of the second compression section, the wall surface of the first expansion section, and the wall surface of the second expansion section are smoothly connected. In the thrust chamber, the engine combustion chamber and the nozzle are continuously transitioned, and the integrated design realizes the depth matching of the parameters of the combustion chamber and nozzle inlet, effectively improving the thrust performance of the nozzle; effectively optimizing the thrust distribution of thrust chamber components, eliminating shock waves, and reducing Internal flow loss, improving engine performance.

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 technology that achieves high-speed penetration, 2-hour global arrival, and cheap access to space. Its development will change the future of war. It is the new commanding height of aerospace technology in the 21st century. The world's major countries are competing to develop related technologies and pose a new threat to our national security. As the best alternative power plant for hypersonic air-breathing flight, scramjet has become a research hotspot of various aerospace powers. As the core component of the scramjet, 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 usua...

AI Technical Summary

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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