Air-breathing pulse detonation engine and detonation method thereof

Abstract

The invention discloses an air-breathing pulse detonation engine and a detonation method thereof. An air inlet channel, a mixed evaporator, a detonation chamber and a tailpipe are connected along an air inlet direction in turn, and a leaf valve, a main fuel nozzle and an air discharge cavity are arranged in an air inlet ring cavity along the air inlet direction in turn, wherein the fuel radially injects through the main fuel nozzle; the air discharge cavity and an air discharge tube are communicated through a through hole of a central body bracket to the exterior of an outer wall of the air inlet channel; the leaf valve maintains a forward normally opened state; a detonation tube is arranged in the detonation chamber through a mounting bracket; a drainage tube, an igniter and a heat exchanger are arranged on the detonation tube; a plurality of jet holes are formed on a tail side wall or a tail end face; the igniter is positioned on the front section of the detonation tube; and the drainage tube is gapped in the detonation chamber and near the igniter inside the detonation tube respectively. The air-breathing pulse detonation engine has the advantages of capabilities of reliably working under severe condition, realizing lower forward flow resistance, simultaneously suppressing and using reverse flow and improving the engine thrust, along with simple structure and wide flight range.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to an air-breathing pulse detonation engine and its detonation method. Background technique [0002] The pulse detonation engine is a new concept engine that uses intermittent or pulse detonation waves to generate thrust. Unlike the deflagration combustion in conventional engines (such as turbojet engines and piston engines, etc.), the combustion process in pulse detonation engines is detonation combustion. Compared with the deflagration cycle, the detonation cycle has higher thermal efficiency. The pulse detonation engine has low unit fuel consumption rate, wide operating range, simple structure, high thrust-to-weight ratio, can adapt to high-speed flight conditions, and the maximum flight Mach number can reach 5. It is recognized as the most promising aerospace power system at home and abroad. [0003] The difference between detonation and deflagration is that it has a high supe...

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Problems solved by technology

[0006] To sum up, the pulse detonation engine has a simple structure and a high thrust-to-weight ratio, but both the existing valved and valveless pulse detonation engines have disadvantages that cannot be ignored: the valve closure of the valved pulse de

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