Axial symmetry plug type spray pipe having afterburning function

Abstract

An axial symmetry plug type spray pipe having an afterburning function is characterized by comprising a spray pipe outer wall barrel, a spray pipe outer wall convergent section, a spray pipe outer wall convergent section, a spray pipe inner wall barrel, an oil spraying ring, an ignition device, a flame stabilizer, a spray pipe inner wall convergent section, a spray pipe inner wall expansion section and a plug body. The spray pipe outer wall barrel, the spray pipe outer wall convergent section and the spray pipe outer wall convergent section are connected with each other through flange mounting edges to form an annular outer wall channel wall; and the spray pipe inner wall barrel, the spray pipe inner wall convergent section and the spray pipe inner wall expansion section are connected through flange mounting edges to form an annular inner wall channel wall. The oil spraying ring, the ignition device and the flame stabilizer are positioned in an annular channel I defined by the outer wall channel wall and the inner wall channel wall. The axial symmetry plug type spray pipe has the advantages that an engine has a good thrust coefficient when at a high altitude state and has a certain attenuation effect on radar waves.

Description

technical field [0001] The invention relates to the technical field of aeroengine nozzle and afterburner design, in particular to an axisymmetric plug nozzle with afterburner function. Background technique [0002] The axisymmetric plug nozzle and the afterburner of the existing aero-engine are two parts, the afterburner is at the front of the nozzle, and the exhaust system of the engine is composed of the afterburner and the nozzle, but such The engine will cause large airflow resistance and large thrust loss when the engine does not work after the afterburner. Through the axisymmetric plug nozzle with afterburner function designed in this patent, the engine can be realized in non-afterburner. The state thrust loss is less, and the length of the engine exhaust system can be shortened by more than 40%, and the weight can be reduced by more than 40%. At the same time, the engine can have a good thrust coefficient at high altitude and have a certain attenuation effect on radar...

AI Technical Summary

Problems solved by technology

[0002] The axisymmetric plug nozzle and the afterburner of the existing aero-engine are two parts, the afterburner is at the front of the nozzle, and the exhaust system of the engine is formed by the afterburner and the nozzle, but such The engine will cause large airflow resistance and large thrust loss when the engine does not work after the afterburner. Through the axisymmetric plug nozzle with afterburner function designed in this patent, the engine can be realized in non-afterburner. The state thrust loss is less, and the length of the engine exhaust system can be shortened by more than 40%, and the weight can be reduced by more than 40%. At the same time, the engine can have a good thrust coefficient at high altitude and have a certain attenuation effect on radar waves.

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