Anti-backfire nozzle for rocket engine

Abstract

The invention provides an anti-backfire nozzle for a rocket engine. The anti-backfire nozzle comprises a rotary core body (1), an anti-backfire ring (2) and a shell (3); the anti-backfire ring (2) is arranged between the rotary core body (1) and the shell (3); the inner wall face and the outer wall face of the anti-backfire ring (2) cling to the outer wall face of the rotary core body (1) and the inner wall face of the shell (3) respectively; a liquid propellant storing and distributing cavity (11), a tangential hole (12) and a swirl chamber (13) are formed in the rotary core body (1); the shell (3) is provided with a nozzle exit (31) and a thermal insulation material (32); and a propellant flows along a flowing passage defined by the anti-backfire ring (2), the liquid propellant storing and distributing cavity (11), the tangential hole (12), the swirl chamber (13) and the nozzle exit (31), is uniformly distributed and shunted by the liquid propellant storing and distributing cavity (11), forms uniform conical mist spray at the outlet of the nozzle exit and is atomized. The anti-backfire nozzle has the advantages of simple structure, mature process and the like, has both the functions of backfire resistance and efficient combustion and is suitable for other engines and combustion devices with high requirements on performance and easiness in generating backfire.

Description

technical field [0001] The invention relates to an anti-backfire nozzle for a rocket engine, which takes into account anti-backfire and high-efficiency combustion functions, and is suitable for other engines and combustion devices that have high performance requirements but are prone to backfire. Background technique [0002] The nitrous oxide-fuel unit composite propulsion technology has the advantages of green and non-toxic, high specific impulse and low cost of use, and is a propulsion technology with great development potential. When the nitrous oxide-fuel unit composite propellant is ignited, shut down and burned, it is easy to flash back, causing the supply system to explode, posing a safety hazard. Conventional anti-backfire measures (such as water seals, molecular seals, and micropore heat absorption, etc.) have defects such as bulky structures, failure of the flight environment, and reduced efficiency of the propulsion system, so they are not applicable in the field...

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Problems solved by technology

[0003] At present, there is no description or report of similar technology of the present invention found in China, and similar data at home and abroad have not been collected yet.

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