Multi-stage afterburner with outer ring rotating detonation supercharging combustion chamber

Abstract

A multi-stage afterburner with an outer ring rotating detonation supercharging combustion chamber comprises an afterburner body which is provided with an afterburner outer culvert channel, an inner culvert gas channel, an afterburner inner cone, a diffusion mixing section, a flame stabilizer and a center afterburner heat screen. A rotary detonation supercharging combustion chamber device is arranged in the afterburner outer culvert channel. The center afterburner heat screen is composed of multiple cylinder sections, and air inlet circular seam structures are formed between the cylinder sections with different diameters, so that outer culvert flow dividing airflow enters the center afterburner. The rotary detonation supercharging combustion chamber device is sequentially provided with an outer culvert flow dividing section, a rotary detonation diffusion rectification section, an annular array type fuel nozzle, an on-duty pre-exploder and the rotary detonation supercharging combustion chamber in the flow direction. The working service performance of the afterburner under a variable cycle engine or turbine combined power high Mach number can be effectively improved, the afterburner heat efficiency and the fuel specific impulse are improved, the afterburner oil consumption is reduced, the flight range is improved, and the working Mach number range is expanded.

Description

technical field [0001] The invention relates to the technical field of aero-engine afterburner, in particular to a multi-stage afterburner with an outer ring rotating detonation booster combustion chamber. Background technique [0002] The afterburner is located between the turbine outlet of the aero-engine and the tail nozzle structure, so that the inner and outer air are mixed and then injected and burned to provide thrust, which can greatly increase the thrust-to-weight ratio of the engine without changing the engine structure, which is beneficial to the maneuverability of the aircraft. Significant influence. In addition to being used in military turbofan engines, it can be widely used in power plants such as variable cycle engines, air turbine rocket (ATR) engines, and turbine-based combined power in the future. [0003] In the rotary detonation engine, fuel and oxidant are mixed and detonated to generate a detonation wave, which rotates and propagates along the circumf...

AI Technical Summary

Problems solved by technology

With the improvement of the working Mach number of the aero-engine, the high total temperature of the afterburner flow leads to poor reliability of the injection combustion and flame stability structure, low afterburner efficiency, and high fuel consumption. The conventional afterburner solution is difficult to meet the demand

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