Integrated afterburner with multi-stage oil injection holes and center cone

Abstract

The invention provides an integrated afterburner with multi-stage oil injection holes and a center cone. The multi-stage oil injection holes are formed in the center cone, and the center cone is hollow and is in a step shape. The heat exchange surface area of high-temperature fuel gas and fuel oil in a fuel oil channel is increased through the step-shaped center cone structure. Impact heat exchange is formed at the step position, and thus heat exchange is enhanced. Due to the multi-stage center cone structure, the high-temperature fuel gas can form a corner vortex between every two stages of sudden expansion when flowing through, and a more obvious backflow area is generated at the downstream position. The preheated fuel oil in the fuel oil channel of the center cone is injected out through the oil injection holes formed in the multi-stage center cone and is combusted at the downstream position, and the fuel oil forms a pre-film on an inclined plane between every two stages. When the fuel oil is injected out of the oil injection hole of the next stage, the liquid film is broken to form secondary atomization, the atomization effect and the oil-gas mixing uniformity are further improved, and therefore the combustion efficiency is improved. The multi-stage center cone structure is also beneficial to forming of the backflow area in the center of the afterburner for stable combustion.

Description

technical field [0001] The invention belongs to the field of gas turbine engines, and in particular relates to an afterburner integrated with central cones of multi-stage fuel injection holes. Background technique [0002] Certain aeroengines may not perform well across the entire thrust range. For example, when an aircraft takes off, it needs a lot more thrust than when it is cruising. If the engine is designed according to the take-off thrust, the mass of the engine will be too large, and the engine will be in a non-design point state during cruising, and the performance will be very poor; If the engine is not designed for thrust, it will cause the aircraft to fail to take off normally. One of the measures to solve the above problems is to add an afterburner between the gas turbine and the nozzle of the engine to greatly increase the engine thrust in a short time. Although the mass of the afterburner is only about 1 / 5 of the engine, the thrust can be increased by more th...

AI Technical Summary

Problems solved by technology

However, since the afterburner uses the gas from the main combustion chamber for fuel injection and reburning, the oxygen content in the gas flow is only about 2 / 3 to 3 / 4 of that of normal air, so its combustion efficiency is low

In addition, since the afterburner mostly uses direct injection nozzles, the fuel is directly injected into the airflow, the atomization effect of the fuel is poor, and the mixing with the airflow is not uniform enough, which further reduces the combustion efficiency

[0004] The working environment of the afterburner is poor, and the gas discharged from the outlet of the turbine has high temperature, low pressure and high velocity, which is not conducive to the ignition and organization of combustion of the gas in the afterburner

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