A stationary detonation engine based on variable wedge angle

Abstract

The invention discloses a stationary detonation engine based on a variable wedge angle, which includes: an intake port, which causes the incoming flow to generate an oblique shock wave to increase the pressure and temperature; an oblique detonation combustion chamber, which accommodates the incoming flow and fuel mixing, And an oblique shock wave is induced by the inclined wedge surface at the rear to ignite the mixed gas to generate an oblique detonation shock wave; the tail nozzle, the combustion products generated in the combustion chamber further expand and accelerate in the tail nozzle flow channel; the fuel injection and atomization system, The fuel is injected at the front of the combustion chamber to promote the mixing of the fuel and the incoming flow, and at the same time prevent the incoming flow from pre-combustion; the wedge angle control system adjusts the angle of the wedge surface in real time according to the aerodynamic state of the gas mixture in the combustion chamber to make the oblique detonation shock wave Right at the inlet of the tailpipe. The present invention controls the combustion of the mixed gas to stabilize in the oblique detonation state through the inclined wedge surface control device at the rear of the combustion chamber, so that the combustion is basically in the optimal state, so as to optimize the thrust performance of the engine and achieve the engine's performance under variable working conditions. The effect of continuous work.

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

Images