Combustion chamber, engine and aircraft based on supersonic speed ramjet oblique detonation

Abstract

The invention discloses a combustion chamber, an engine and an aircraft based on supersonic speed ramjet oblique detonation. The combustion chamber is internally provided with a slope, the slope is obliquely arranged upwards from the inlet end of the combustion chamber to the outlet end of the combustion chamber, and one side wall face, opposite to the slope, of the combustion chamber is provided with a high-energy laser emitting device; the high-energy laser emitting device can emit laser and focus lasers after inducing oblique shock waves above the slope, the focused laser serves as a high-energy ignition source, energy is injected into a flow field, premixed gas is ignited, and therefore oblique detonation wave detonation is promoted. According to the combustion chamber, high-energy lasers and a small-angle physical slope are combined, high-energy laser focusing is utilized under the condition of slope induction, ignition is carried out after oblique shock wave induction, and therefore oblique detonation wave detonation can be effectively promoted.

Description

technical field [0001] The invention belongs to the technical field of hypersonic propulsion, and more specifically relates to a combustion chamber, an engine and an aircraft based on supersonic ram oblique detonation. Background technique [0002] In recent years, the field of hypersonic propulsion has become a new field that is being pursued at home and abroad, and hypersonic vehicles have great development potential in the field of national defense and military affairs. At present, the scramjet engine based on the Brayton isobaric combustion cycle can achieve high Mach flight within a certain range, and great progress has been made in technology. However, due to the limitations of the combustion method itself, it is difficult to improve the efficiency of the thermodynamic cycle. The detonation engine has higher thermal cycle efficiency and faster heat release efficiency than the traditional scramjet engine, and also has the advantages of simple structure and small size. ...

AI Technical Summary

Problems solved by technology

[0004] Existing oblique detonation engine schemes generally use a slope with a fixed angle to induce oblique detonation wave initiation in the supersonic incoming flow. It is difficult to detonate at a small angle, and it is easy to cause the forward propagation of the oblique detonation wave at a large angle, especially at present. In the case of Mach flow, it is even more difficult to achieve the stagnation of the detonation wave

Even if the oblique detonation wave can stagnate at a large angle, it will significantly increase the total pressure loss and significantly reduce the thermodynamic cycle efficiency of the oblique detonation engine. Therefore, the detonation initiation and stagnation of the detonation wave at a small angle slope are important in the current experimental research. question

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