Detonation combustion chamber, scramjet engine and hypersonic aircraft

Abstract

The invention provides a detonation combustion chamber, a scramjet engine and a hypersonic aircraft. The detonation combustion chamber is characterized in that a slope is arranged in the combustion chamber, the slope is obliquely arranged upwards from the inlet end of the combustion chamber to the outlet end of the combustion chamber, a suction hole is formed in the surface of the slope, the suction hole communicates with a suction device or a vacuum cavity, a suction valve is arranged in the suction hole, and the position of the suction valve is lower than the slope surface; when the suction valve is closed, the suction hole above the suction valve forms a concave cavity in the surface of the slope, and a post-wave product can be sucked when the suction valve is opened. According to the detonation combustion chamber, through the design of the suction hole and the suction valve, the concave cavity and wall surface suction are applied to the slope at the same time, the purposes of promoting oblique detonation wave detonation and restraining oblique detonation wave forward transmission are achieved, and therefore the stationary range of oblique detonation waves can be widened.

Description

technical field [0001] The invention belongs to the technical field of hypersonic propulsion, and more specifically relates to a detonation combustion chamber, a scramjet and a hypersonic aircraft. 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. Especially the obliq...

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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, the initiation and stagnation of the detonation wave under a slope with a small angle is an important issue in the current experimental research

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