Adaptive rocket nozzle for rocket-based combined cycle engines

Abstract

The invention discloses a self-adaptive rocket spray tube applied to a rocket based combined circulating engine. The self-adaptive rocket spray tube comprises a spray tube body, wherein a flow-supplementing sucking channel and a pneumatic tab channel are arranged on the spray tube body; when the rocket based combined circulating engine works in an ejector mode, the rocket engine sprays high-speedgas flow to the outer side of the spray tube body along a pneumatic tab channel, and high-speed gas flow mutually acts with gas flow on the outer part of the spray tube body to form streamwise vortex,so that mixing between rocket jet flow and outer gas flow is strengthened; and moreover, along with different working conditions of the rocket engine, penetrating depth of a pneumatic tab generates changes. When the rocket based combined circulating engine is in a sub-combustion or super-combustion mode, the rocket engine is switched off; and gas flow on the outer part of the spray tube body automatically flows into the spray tube body from the outer side of the spray tube body along the flow-supplementing sucking channel as a result of internal and external pressure difference, so that bottom resistance generated by the spray tube is reduced. The self-adaptive rocket spray tube has certain self-adaptive regulating ability, and facilitates integral pneumatic performance.

Description

technical field [0001] The invention relates to an adaptive rocket nozzle applied to rocket-based combined cycle engines, and is mainly used in power systems such as air-breathing combined engines that require mixing of internal and external flows. Background technique [0002] With the advancement of science and technology, aerospace engines have higher and higher requirements for injection blending. How to effectively strengthen the air mixing of internal and external flows, shorten the length of the engine, and reduce the resistance is a hot spot in the research of various countries. [0003] Conventional means of strengthening blending is blending through lobes, small solid tabs, etc., which will cause 5%-15% thrust loss to the engine, and the structure is complicated, heat protection is difficult, and the manufacturing cost is high. [0004] Therefore, it is of great practical value to develop a rocket nozzle with simple structure and self-adaptive and adjustable effec...

AI Technical Summary

Problems solved by technology

[0003] Conventional means of strengthening blending is blending through lobes, small solid tabs, etc., which will cause 5%-15% thrust loss to the engine, and the structure is complex, heat protection is difficult, and the manufacturing cost is high

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