A continuously rotating detonation combustion chamber and ramjet

Abstract

In order to further improve the combustion organization capability and thrust performance of the rotary detonation combustion chamber, the present invention provides a continuous rotary detonation combustion chamber and a ramjet, comprising an outer casing and a cylinder located in the inner cavity of the outer casing, and the cylinder is penetrating front and rear. Empty cylinder, an annular flow channel is formed between the cylinder body and the inner wall of the casing, the front end of the annular flow channel is set as an intake channel, and an isolation section, a detonation combustion chamber and a tail nozzle are sequentially arranged on the annular flow channel after the intake channel to isolate the The junction between the detonation combustion chamber and the detonation combustion chamber is a stepped sudden expansion transition, forming a backward step, which can stabilize the flame and enhance the combustion; the annular flow passage in the rear section of the detonation combustion chamber is linearly reduced to form an inclination connecting the tail nozzle. Transition. The invention can enhance the stability of continuous rotation knocking and widen the continuous rotation working boundary.

Description

technical field [0001] The invention relates to the technical field of ramjets, in particular to a continuously rotating detonation combustion chamber and a ramjet. Background technique [0002] At present, heat engines such as aero-engines, rocket engines, and ramjet engines convert the chemical energy of fuel into heat energy by isobaric combustion. , the combustion performance of this type of engine is close to the theoretical limit, and it is difficult to greatly improve it. In addition, the internal combustion process of these engines has a common feature, that is, the combustion is organized along the gas flow direction, that is, the combustion is completed in the process of the gas flowing downstream. In order to ensure that the fuel and the oxidant can be fully burned, the combustion chamber of the engine must have a sufficient length. Generally, the faster the flow rate in the combustion chamber, the longer the length of the combustion chamber. [0003] Compared w...

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Problems solved by technology

[0007] Compared with the circular combustion chamber, the cylindrical combustion chamber has stronger combustion organization ability, but the average pressure of the combustion chamber is lower, which is not conducive to improving the thrust performance, but the working boundary of the circular combustion chamber is limited, which is not conducive to Low equivalence ratio work, but the ability to work at low equivalence ratio is required during flight work

At the same time, there are inner columns in the above two schemes. When the engine works for a long time, both the detonation chamber jacket and the inner column need thermal protection. The thermal protection area and difficulty are large, and the space utilization rate of the inner column is low. Bring greater difficulty to the design of the intake

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