Stationary detonation engine based on variable wedge angle

Abstract

The invention discloses a stationary detonation engine based on the variable wedge angle. The stationary detonation engine based on the variable wedge angle comprises a gas inlet channel, an oblique detonation combustion chamber, a tail jet pipe, a fuel oil jetting and atomizing system and a wedge angle control system. The gas inlet channel enables an incoming flow to generate an oblique shock wave, and pressurizing for temperature increasing is conducted. The oblique detonation combustion chamber contains the incoming flow to mix the incoming flow and fuel, and through the wedge face on the rear portion of the oblique detonation combustion chamber, an oblique shock wave is induced, and thus mixed gas is ignited to generate the oblique detonation shock wave. Combustion products generated in the combustion chamber are further expanded and accelerated in a tail jetting pipe flow channel. The fuel oil jetting and atomizing system jets the fuel in the front of the combustion chamber to promote mixing of the fuel and the incoming flow, and meanwhile pre-combustion of the incoming flow is prevented. According to the aerodynamic condition of the mixed gas of the combustion chamber, the wedge angle control system adjusts the forms such as the wedge face angle in real time, and thus the oblique detonation wave is at an inlet of the tail jet pipe in a stationary mode. According to the stationary detonation engine based on the variable wedge angle, through a wedge face control device on the rear portion of the combustion chamber, combustion of the mixed gas is controlled at stable theoblique detonation form, thus combustion is basically at an optimum state so as to optimize the thrust performance of the engine, and the effect that the engine can continuously work under the variable work conditions is achieved.

Description

technical field [0001] The invention relates to a stationary detonation engine based on a variable wedge angle, belonging to the technical field of supersonic engines. Background technique [0002] The power solution of the current hypersonic vehicle has always been a difficult problem in the minds of researchers from many countries. One of the more widely recognized solutions is the supersonic combustion ramjet engine. Its working principle is that the total pressure of the supersonic airflow itself is very high. The supersonic airflow is introduced into the engine combustion chamber and mixed with fuel for combustion, and the combustion products are discharged through the tail nozzle at supersonic speed, thereby generating thrust. [0003] This idea of ​​using the nature of the airflow itself to simplify the engine structure is good, but it also has great limitations. The experimental results show that the acceleration obtained by the aircraft after the engine starts to w...

AI Technical Summary

Problems solved by technology

This approach increases the combustion loss and is technically more uncontrollable, which has a greater impact on the overall performance of the system

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