接力喷嘴不同径向高度和方位角对加力燃烧室 热射流点火性能的影响

为了研究不同热射流点火状态下的燃烧性能,针对采用波瓣混合器的某型航空发动机加力燃烧室,基于N-S方程建立了3维数值计算模型,得到了接力喷嘴径向高度和方位角对加力燃烧室流场、燃烧特性和流阻特性的影响规律。结果表明:随着径向高度增加,热射流火焰传播距离逐渐减小,传播到稳定器下游区域从内涵逐渐向外涵移动,且稳定器壁面高温分布区域逐渐减小;随着方位角增大,热射流火焰径向穿透深度逐渐增大,且稳定器壁面高温区域逐渐减小,在方位角α=0°和α=5°时稳定器壁温最高,为1450 K左右;在加力燃烧室出口截面上,径向高度和方位角对无量纲总压影响不大,整体小于0.005。

Performance Analysis of Different Radial Height and Azimuth of the Relay Nozzle on the Hot Jet Igniting of the Afterburner

In order to study the combustion performance of different hot jet ignition states,a three-dimensional numerical simulation model was established for an aeroengine afterburner with a wave-lobe mixer based on N-S equation. The effects of the radial height and azimuth of the relay nozzle on the flow field,combustion characteristics and flow resistance characteristics of the afterburner were obtained. The results show that with the increase of radial height,the flame propagation distance of the hot jet decreases gradually,and the propagation to the downstream region of the stabilizer moves gradually from the connotation to the culvert,and the high temperature distribution region of the stabilizer wall decreases gradually. With the increase of azimuth angle,the radial penetration depth of the hot jet flame increases gradually,and the high temperature region of the stabilizer wall decreases gradually. The maximum wall temperature of the stabilizer is about 1450 K at the azimuth angles of 0°and 5°. The radial height and azimuth angle have little effect on the dimensionless total pressure at the outlet section of the afterburner,and are less than 0.005 as a whole.