Supersonic hybrid enhanced structure with frequency characteristics and rocket-based combined engine

Abstract

The invention provides a supersonic speed mixing enhancement structure with frequency characteristics and a rocket based combined engine. The supersonic speed mixing enhancement structure comprises asupersonic speed incoming flow separation plate, wherein two sides of the supersonic speed incoming flow separation plate are respectively provided with supersonic speed incoming flow channels, the two supersonic speed incoming flow channels are communicated at the tail end of the supersonic incoming flow separation plate to form a supersonic speed incoming flow mixing area, the supersonic speed incoming flow mixing area is communicated with at least one supersonic speed incoming flow channel through at least one drainage tube, the drainage tube is arranged inside the supersonic speed incomingflow separation plate, the drainage tube is internally provided with at least one expansion chamber. There is a pressure difference between two ends of the drainage tube, so that a jet flow can be formed in the supersonic speed incoming flow mixing area without providing an additional air source, thereby realizing mixing enhancement control for the supersonic speed incoming flow mixing area. Meanwhile, the drainage tube is internally provided with the expansion chambers, so that the jet flow ejected by the drainage tube is enabled to have certain frequency characteristics, and the superposition of different frequencies is realized by arranging different numbers of expansion chambers. The supersonic speed mixing enhancement structure is applied to the field of supersonic speed incoming flow mixing control.

Description

technical field [0001] The invention relates to the field of supersonic flow mixing control, in particular to a supersonic mixing enhanced structure with frequency characteristics and a rocket-based combined engine. Background technique [0002] As a key process of Rocket Based Combined Cycle (RBCC), ejection plays the role of mixing rocket gas with incoming air. For RBCC, the free flow passes through the intake port and contacts the nozzle gas at the nozzle trailing edge. When the mixture of the two reaches the molecular level, a chemical reaction occurs, and the purpose of using the oxygen in the air to increase the specific impulse of the engine is achieved. However, due to the high velocity of the incoming flow, the residence time in the combustion chamber is extremely short (less than 1-3ms), how to realize the rapid and efficient mixing of gas and air is the key issue of injection, that is, to enhance the mixing effect, which determines the entire propulsion system pe...

AI Technical Summary

Problems solved by technology

[0005] The passive control scheme based on changing the structure of the trailing edge has a simple structure and obvious control effects, but it is mainly aimed at the thin trailing edge mixed layer abstracted from practical problems. For the actual blunt trailing edge mixed layer, the partition is thicker and difficult Changing the structure of the trailing edge, while adopting a pointed trailing edge configuration is not conducive to heat protection

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