An integrated structure of electric drive afterburner and adjustable area tail nozzle

Abstract

The invention relates to an electrically-driven afterburner and area-adjustable exhaust nozzle integrated structure and is applicable to aero-turbine engines. Lever execution mechanisms for controlling an area-adjustable exhaust nozzle are arranged at the front end of the afterburner; one end of each lever execution mechanism is connected with an execution connecting rod of an electric execution steering engine, and the other end is connected with an execution ring of the area-adjustable exhaust nozzle. The two electric execution steering engines are adopted, the opening area of the exhaust nozzle is controlled, and the requirement for area change of the exhaust nozzle during working of the afterburner is met. According to the structural scheme, adjustment of the overall structure of the engines is not involved, the movement fulcrum is fixed to the front-end flange surface of the afterburner, and the driving capability of the electric steering engines is magnified with the lever principle, so that the controllability of the adjustable exhaust nozzle is improved effectively; and the complex hydraulic control structure is cancelled, so that the control execution mechanism is simplified.

Description

technical field [0001] The invention belongs to the technical field of aero-engines, in particular to the technical field of small aero-turbine engines with afterburners, and in particular relates to an integrated structure of an electric drive afterburner and an adjustable-area tail nozzle. Background technique [0002] At present, aero-engines with afterburners have been widely used, but they are mainly used in engines with higher thrust, such as F135 and F101 in the United States. Afterburners can effectively increase the short-term thrust of the engine to meet Take off, climb, accelerate, chase and other work requirements, increase flight maneuverability. The currently widely used afterburning method is to install an afterburner between the turbine and the tail nozzle. Since the air is burned in the main combustion chamber, there is still a large amount of remaining oxygen that is not used, so it can be released after the turbine is injected and burned. Heat, thereby si...

AI Technical Summary

Problems solved by technology

Due to the low pressure ratio of the compressor and the small structural size of the small aviation turbine engine, if the traditional structural scheme is adopted to lay out the afterburner technology, the scheme for the hydraulic mechanism to control the area of ​​the tail nozzle is complicated, and the required hydraulic pumps, control valves, displacement measurement, etc. There are so many components that it is difficult to meet the needs of small aero turbine engines with small structure size and low manufacturing cost. Therefore, there are few small aero turbine engines in the world that work with afterburners

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