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本文对双管头部进气旋流-突扩燃烧室模型进行了冷态流场试验研究,以探索进气方式(全旋型或部分旋型)、旋流强度(旋流数S或旋流角(?))、旋流室出口扩张角2α、旋流室长径比l/d、内通道相对面积F等参数对燃烧室流场结构的影响规律.结果表明,适当选择燃烧室结构参数可以在燃烧室中形成稳定的中心回流区和头部旋涡回流区.当(?)=45°、α=15°、l/d=1.3、F=0.41时,除了形成旋流室回流区外,在其尾部还形成了一个较大的、切向分速较低的中心回流区,两者“联串”在一起.部分旋的中心回流区长度与相同旋流角全旋进气时的回流区长度几乎相等,但总压损失却降低63.4%.
In this paper, a cold flow field experiment was carried out on a double-headed inlet swirl-to-expansion combustor model to explore the effects of the inlet mode (full or partial swirl), swirling intensity (swirl number S or swirl (Φ), the expansion angle of the outlet of swirl chamber 2α, the aspect ratio l / d of the swirl chamber, the relative area F of the inner channel, etc. The results show that the proper choice of the structure parameters of the combustion chamber (?) = 45 °, α = 15 °, l / d = 1.3, F = 0.41, in addition to forming a swirl chamber reflux zone , In its tail also formed a larger, tangential velocity lower central reflux zone, the two “together.” Part of the rotation of the center of the reflux zone length and the same swirl angle when the total rotation into the air Reflow zone length is almost equal, but the total pressure loss is reduced by 63.4%.