Laminate scramjet engine combustion chamber

Abstract

The invention belongs to an engine combustion chamber technology, and in particular, relates to a laminate scramjet engine combustion chamber. The laminate scramjet engine combustion chamber comprisesa combustion chamber (1), a combustion chamber inlet (5), a combustion chamber outlet (7) and laminates (2), wherein air currents of the combustion chamber inlet (5) are supersonic air currents; multiple laminates (2) are designed in the combustion chamber (1) for dividing the combustion chamber (1) into multiple small combustion chambers; and after the supersonic air currents enter the combustion chamber inlet (5), the air currents are fed into the combustion chamber (1) through multiple channels under the effect of the laminates (2), and flow out from the combustion chamber outlet (7) aftercombustion. The fuel injection, the laminates and the combustion chamber are integrated as a whole, so that the overall structure is simple, the heat protection requirement is low, and the stop timeof the air currents in the combustion chamber is effectively prolonged; and the fuel injection area is large, and the coverage area is wide, so that the full combustion can be realized, and the combustion efficiency is guaranteed.

Description

technical field [0001] The invention belongs to engine combustion chamber technology, in particular to a laminated scramjet combustion chamber. Background technique [0002] The main feature of the scramjet is to realize the stable combustion of fuel in supersonic internal flow. Since the residence time of supersonic air flowing through the combustion chamber of the engine is very short, it is very difficult to efficiently mix and burn the fuel in a very short period of time. At present, the scramjet combustor mainly adopts central combustion or cavity technology to achieve supersonic combustion and flame stability in the scramjet combustor. [0003] US2008 / 0092519A1 and USPat7797943B2 proposed the mechanism and advantages of the central combustion scramjet, and the cavity combustion technology has been applied to the Russian Kholod scramjet. However, the structure of the center-combustion super-combustion engine is complex, and the proportion of the core airflow is relati...

AI Technical Summary

Problems solved by technology

However, the structure of the center-combustion super-combustion engine is complex, and the proportion of the core airflow is relatively small, which will increase the cross-sectional area of ​​the combustion chamber

Cavity combustion will increase the pressure loss during the combustion process, and lead to a heavy burden on the thermal protection of the inner wall of the combustion chamber

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