Dual combustion chamber ramjet and hypersonic vehicle

Abstract

The invention discloses a double-combustion chamber ramjet engine and a hypersonic vehicle, comprising: a shell, the shell is in the shape of a hollow cylinder whose two ends are connected. It also includes a center shell, which is arranged in the shaft hole of the shell and connected with the shell. The gap between the center shell and the shell forms an external drainage channel, and the cavity between the rear end surface of the center shell and the inner wall of the shell forms a detonation chamber. And the tail nozzle communicated with the detonation chamber. Also includes a central cone, the rear body of the central cone extends into the central shell and is connected with the central shell, the gap between the central cone and the central shell forms a central drainage channel, the rear end surface of the central cone and the inner wall of the central shell The cavity in between forms a sub-combustion chamber connected to a fuel source and in communication with the detonation chamber. A plurality of outer nozzles are processed on the outer wall of the shell, and the two ends of the outer nozzles communicate with the fuel source and the outer drainage channel respectively. And / or the outer wall of the central housing is processed with a plurality of inner nozzles, 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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