Double-combustion-chamber ramjet and hypersonic aerocraft

Abstract

The invention discloses a double-combustion-chamber ramjet and a hypersonic aerocraft. The double-combustion-chamber ramjet comprises an outer shell; and the outer shell is a hollow cylinder with twocommunicating ends. The double-combustion-chamber ramjet further comprises a center shell; the center shell is arranged in a shaft hole of the outer shell, and is connected with the outer shell; a gapbetween the center shell and the outer shell forms an outer drainage channel; a cavity between the back end surface of the center shell and the inner wall of the outer shell forms a knocking chamber;and a tail spraying pipe communicates with the knocking chamber. The double-combustion-chamber ramjet further comprises a center cone; the back body of the center cone extends into the center shell,and is connected with the center shell; a gap between the center cone and the center shell forms a center drainage channel; a cavity between the back end surface of the center cone and the inner wallof the center shell forms a sub-combustion chamber; and the sub-combustion chamber is connected with a fuel source, and communicates with the knocking chamber. Multiple outer nozzles are formed in theouter wall of the outer shell; and the two ends of the outer nozzles communicate with the fuel source and the outer drainage channel. And / or multiple inner nozzles are formed in the outer wall of thecenter shell; and the two ends of the inner nozzles communicate with the fuel source and the outer drainage channel respectively.

Description

technical field [0001] The invention relates to the field of aeroengines, in particular to a dual-combustion chamber ramjet engine. In addition, the present invention also relates to a hypersonic aircraft comprising the above-mentioned dual-chamber ramjet. Background technique [0002] Scramjet is a kind of hypersonic propulsion device that has been extensively studied at present. It organizes combustion in isobaric mode and is mainly composed of inlet, isolation section, combustion chamber and tail nozzle. Although the structure is simple, its internal The combustion flow mechanism is very complex. The airflow velocity in the scramjet is on the order of kilometers per second, and the residence time of the fuel in the combustion chamber is very short (on the order of milliseconds), which makes it very difficult to ignite and stabilize the flame. [0003] In order to solve the problem of stabilizing the fire of the scramjet engine, a dual combustion chamber ramjet engine is...

AI Technical Summary

Problems solved by technology

[0007] The present invention provides a dual-combustion chamber ramjet and a hypersonic aircraft to solve the existing problems of the existing dual-combustion chamber ramjet, such as the long overall length of the engine and poor thrust performance, and the difficulty in achieving low Technical Problems of Efficient and Stable Combustion of Active Hydrocarbon Fuel Rotating Detonation

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