燃烧室减速熄火条件下滑动弧等离子体对火焰演化的影响

During high manoeuvres and rapid acceleration and deceleration of an aircraft, the fuel-gas ratio in the combustor changes rapidly, and sometime will cross the fuel-gas ratio limit in an instant, which can bring out flame instability and flameout issues. To solve these problems, this paper proposes to apply gliding arc discharge to the combustor dome, and improve the combustor deceleration flameout characteristics through plasma combustion technology. Based on the single-dome combustor, the effects of gliding arc plasma on the flame evolution at different fuel reduction rates are studied. The results show that the application of plasma can reduce the lifted flame distance, maintain the flame near the combustor dome and restrain the flame decay rate. When the fuel reduction rate is 8 g/s², the lifted flame distance is shortened from 63.1 mm to 24.8 mm after the plasma is applied. When combustor approaches flameout state, the flame mass central will move towards combustor dome after the application of plasma.Under the condition that the fuel reduction rate is 8 g/s², the flame mass central will move towards combustor dome 41.7 mm after the application of plasma. On the other hand, When the fuel reduction rate is 2 g/s², the maximum flame decay rate is reduced by 9.2% after plasma is applied.