A multi-stage ladder-tooth type mixer for integrated afterburner

Abstract

A multi-stage ladder-tooth type mixer for an integrated afterburner relates to an aeroengine afterburner. There are two-stage blending sections, each of which is composed of ladder-tooth crown mixers of different sizes, and the blending section is a ring structure. and a second-stage blending section, the first-stage blending section is set inside the second-stage blending section; each stage blending section is composed of an inner wall and a ladder-tooth crown mixer, and the ladder-tooth crown mixer is inwardly inclined with ladder teeth and outwardly inclined. The ladder teeth are alternately and evenly arranged on the outlet end face of the mixing section of each stage. When the gas flows through the inclining ladder teeth and the outward inclination ladder teeth, the staggered distribution of the ladder teeth induces a flow vortex, which forms a stable vortex at the rear end of the ladder-tooth crown mixer. And uniform mixing zone, strengthen the mixing of internal and external bypass airflow. It can effectively suppress the generation of noise, effectively enhance the mixing of the internal and external bypass airflow of the aero-engine, improve the mixing efficiency, reduce the total pressure loss, and thus improve the combustion efficiency of the afterburner.

Description

technical field [0001] The invention relates to an aero-engine afterburner, in particular to a multi-stage ladder-tooth type mixer used for an integrated afterburner. Background technique [0002] Afterburners are generally used in aircraft engines, located between the turbine and the tail nozzle, to increase the thrust of the engine and the flexibility of the aircraft. The main structure of afterburner includes mixing diffuser, oil supply device, flame stabilizer, igniter, anti-vibration heat shield and afterburner cylinder. After fuel injection in the main combustion chamber, there is still a lot of oxygen remaining in the air, so fuel is injected again in the afterburner, and fresh air is introduced through the mixer to burn again, releasing a lot of heat, which greatly improves the thrust performance of the aircraft . [0003] The airflow entering the afterburner generally mixes the connotative gas with the connotative air through the mixer. The effect of mixing will g...

AI Technical Summary

Problems solved by technology

[0003] The airflow entering the afterburner is generally mixed with the internal gas and external air through the mixer. The mixing effect will largely affect the combustion efficiency of the afterburner and thus affect the thrust performance of the engine.

Most of the mixers used in the traditional afterburner are lobe mixers and annular mixers. The lobe mixer has a better mixing effect, but it will cause a large pressure loss and poor structural rigidity, so it is suitable for Engines with high bypass ratio

The total pressure loss of the annular mixer is very small, but the air flow mixing only depends on the shearing action between the inner and outer air streams, and the mixing effect is very unsatisfactory

[0004] In recent years, relevant work on afterburner mixers has been carried out at home and abroad, and the concept of multi-stage mixers has been proposed internationally. The mixing efficiency of internal and external content has been greatly improved, but the problem of high total pressure loss has not been resolved

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