An integrated afterburner with dual oil passages at the end of a support plate

Abstract

The invention provides an integrated afterburner of supporting plate tail dual oil channels. Fuel oil is supplied to the integrated afterburner through a hollow thrust augmentation inner cone, two supporting plates are installed on the two sides, close to the tail portion, of a whole flow supporting plate, and fuel oil channels are formed in the middles of the whole flow plate and the supporting plates on the two sides of the tail portion of the whole flow supporting plate correspondingly; and the fuel oil is sprayed out of the tail portion of the whole flow supporting plate and fuel oil spraying holes formed in the supporting plates on the two sides of the whole flow supporting plate. The integrated afterburner of the supporting plate tail dual oil channels has the advantages that by installing the hollow fuel oil channels of the thrust augmentation inner cone, the fuel oil in the thrust augmentation inner cone is preheated, and thus the fuel oil is subjected to pre-evaporation; by forming inclined-spraying fuel oil holes in the supporting plates on the two sides of the whole flow supporting plate, the fuel oil can reach the process of fuel oil primary atomization by hitting against the outer wall of the whole flow supporting plate; the pre-heated fuel oil is sprayed out of a spraying opening, and after hitting against the wall face, and the fuel oil basically is gas or a supercritical body; and viscidity is reduced, diffusivity is reinforced, the flowing ability is greatly improved, thus the fuel oil can be more evenly mixed with surrounding air, and burning efficiency of the afterburner is improved.

Description

technical field [0001] The invention belongs to the field of afterburner, and in particular relates to an arrangement of rectifying branch oil passages in the afterburner, which can provide dual oil passages for fuel supply and enhance the degree of fuel atomization. Background technique [0002] For fighter jets, the engine is required to provide the maximum thrust in a short period of time to meet the work requirements of take-off, climb, acceleration, pursuit, etc., and enhance the maneuverability of the aircraft. power combustion chamber. The afterburner is located between the turbine and the tail nozzle. Since the air passes through the main combustion chamber, there is still a large amount of remaining oxygen (about 2 / 3~3 / 4) that is not used, so it can be injected after the turbine to burn and release heat. , significantly increased the gas temperature and exhaust velocity, thereby increasing the engine's unit thrust and total thrust. [0003] Due to the harsh air fl...

AI Technical Summary

Problems solved by technology

However, the integrated structural design cannot effectively solve the problem of fuel atomization. Therefore, when the integrated design is adopted, the combustion efficiency of the afterburner cannot be effectively improved.

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