超声速气流中点火、火焰传播实验与数值模拟研究
摘要
本文以带凹腔火焰稳定器的超声速燃烧室为研究对象,通过仿真与实验方法研究了超声速燃烧室流场特性以及超声速气流中点火过程初始火焰的形成与发展过程。
对于超声速燃烧室内预混气体强迫点火过程,火花塞首先在凹腔内形成初始火焰,初始火焰进入凹腔剪切层,并在对流作用下迅速传播至凹腔下游,并点燃凹腔内驻留的可燃气体;对于高总温来流自点火过程,初始火焰在凹腔后部形成。驻留于凹腔内的可燃气体燃烧产生的热膨胀作用对点过程主流区域火焰的发展具有重要作用。对于单凹腔燃烧室,当驻留于凹腔内的气体消耗完后,主流区域的燃烧反应也无法维持;对于多凹腔燃烧室,凹腔结构形成的激波交汇于火焰锋面可能在燃烧室内形成爆轰,并以爆轰波的形式逆流传播。
当燃料在壁面横向喷注时,对于强迫点火,初始火焰首先形成于凹腔内火花塞附近,随后穿透剪切层并在剪切层内高速对流作用下迅速点燃剪切层下游可燃气体;对于自点火过程,初始火焰首先出现于凹腔后壁面附近的剪切层,随后剪切层内初始火焰也在凹腔下游壁面附近形成剧烈反应区,另一方面剪切层内火焰前锋逆流扩张直至凹腔前沿位置。两种条件下,当剪切层内初始火焰形成后,都不断发展壮大,并逐步点燃燃料喷流柱。
结合实验与仿真结果分析了带凹腔超声速燃烧室内点火过程两种不同的点火机制:一种是着火点不断提前的自动着火机制,认为凹腔回流区为剪切层上、下游间建立了一个能量反馈回路,通过上下游之间的能量反馈实现着火点的前移;另一种是湍流火焰逆流传播机制,认为初始火焰在剪切层内偏凹腔侧满足的低速区逆流传播。这两种点火方式存在着竞争的关系,其决定因素在于剪切层内燃料的分布。
The ignition processes of the ignition in a scramjet combustor with cavities were studied in this paper. The attention was focused on the formation and propagation of the initial flame.
Numerical simulations of ignition in the pre-mixed flow show that: when the flame was initialed by a spark igniter, the initial flame format near the igniter which in the cavity and propagate into the cavity shear layer. Then the initial flame spreads along the cavity shear layer and ignites downstream gas very quickly by the convection of the shear layer. When the total temperature of the flow is high enough to auto-ignite, the initial flame format in the rump of the cavity. The expansion by the burning gas in the cavity is important for the spreading of the combustion in the main flow. To the combustor with single cavity, when the initial gas in the cavity is exhausted, the combustion in the main flow couldn’t be maintained, while to the combustor with several cavities, when the shock waves meet on the flame front, a detonation may generate and spread to the upstream.
Numerical and experimental investigations on the ignition of fuel transverse Jet into Supersonic flow show that, for the forced ignition, the spark generates near the igniter, and grows to form flame in the cavity. The initial flame spreads along the cavity shear layer and ignites the fuel distributed downstream very quickly. With the pressure downstream rises up, the pre-combustion shock and the flame go against the stream and finally the whole fuel jet flame is ignited and stabilized. For the auto-ignition, the initial flame generate in tail of the shear layer, then the flame ignite the gas downstream the cavity on one way, and spread opposite the shear layer on the other way. When the whole shear layer is burning, the process of the flame spread is similar to the one of forced ignition.
Two different flame spread mechanisms were discussed based the numerical and experimental data. One called the the sustaining auto-igniting mechanism consider that the cavity establish a feedback between the tail and head of the shear layer, while there is a another feedback between heat release from combustion and the upstream shock train. The other one is called the turbulent flame propagating mechanism, which consider that a banding zone in which the turbulent flame speed is higher than the gas velocity may extent in the shear layer. These two mechanism types have a competition-relation on the ignition.
对于超声速燃烧室内预混气体强迫点火过程,火花塞首先在凹腔内形成初始火焰,初始火焰进入凹腔剪切层,并在对流作用下迅速传播至凹腔下游,并点燃凹腔内驻留的可燃气体;对于高总温来流自点火过程,初始火焰在凹腔后部形成。驻留于凹腔内的可燃气体燃烧产生的热膨胀作用对点过程主流区域火焰的发展具有重要作用。对于单凹腔燃烧室,当驻留于凹腔内的气体消耗完后,主流区域的燃烧反应也无法维持;对于多凹腔燃烧室,凹腔结构形成的激波交汇于火焰锋面可能在燃烧室内形成爆轰,并以爆轰波的形式逆流传播。
当燃料在壁面横向喷注时,对于强迫点火,初始火焰首先形成于凹腔内火花塞附近,随后穿透剪切层并在剪切层内高速对流作用下迅速点燃剪切层下游可燃气体;对于自点火过程,初始火焰首先出现于凹腔后壁面附近的剪切层,随后剪切层内初始火焰也在凹腔下游壁面附近形成剧烈反应区,另一方面剪切层内火焰前锋逆流扩张直至凹腔前沿位置。两种条件下,当剪切层内初始火焰形成后,都不断发展壮大,并逐步点燃燃料喷流柱。
结合实验与仿真结果分析了带凹腔超声速燃烧室内点火过程两种不同的点火机制:一种是着火点不断提前的自动着火机制,认为凹腔回流区为剪切层上、下游间建立了一个能量反馈回路,通过上下游之间的能量反馈实现着火点的前移;另一种是湍流火焰逆流传播机制,认为初始火焰在剪切层内偏凹腔侧满足的低速区逆流传播。这两种点火方式存在着竞争的关系,其决定因素在于剪切层内燃料的分布。
The ignition processes of the ignition in a scramjet combustor with cavities were studied in this paper. The attention was focused on the formation and propagation of the initial flame.
Numerical simulations of ignition in the pre-mixed flow show that: when the flame was initialed by a spark igniter, the initial flame format near the igniter which in the cavity and propagate into the cavity shear layer. Then the initial flame spreads along the cavity shear layer and ignites downstream gas very quickly by the convection of the shear layer. When the total temperature of the flow is high enough to auto-ignite, the initial flame format in the rump of the cavity. The expansion by the burning gas in the cavity is important for the spreading of the combustion in the main flow. To the combustor with single cavity, when the initial gas in the cavity is exhausted, the combustion in the main flow couldn’t be maintained, while to the combustor with several cavities, when the shock waves meet on the flame front, a detonation may generate and spread to the upstream.
Numerical and experimental investigations on the ignition of fuel transverse Jet into Supersonic flow show that, for the forced ignition, the spark generates near the igniter, and grows to form flame in the cavity. The initial flame spreads along the cavity shear layer and ignites the fuel distributed downstream very quickly. With the pressure downstream rises up, the pre-combustion shock and the flame go against the stream and finally the whole fuel jet flame is ignited and stabilized. For the auto-ignition, the initial flame generate in tail of the shear layer, then the flame ignite the gas downstream the cavity on one way, and spread opposite the shear layer on the other way. When the whole shear layer is burning, the process of the flame spread is similar to the one of forced ignition.
Two different flame spread mechanisms were discussed based the numerical and experimental data. One called the the sustaining auto-igniting mechanism consider that the cavity establish a feedback between the tail and head of the shear layer, while there is a another feedback between heat release from combustion and the upstream shock train. The other one is called the turbulent flame propagating mechanism, which consider that a banding zone in which the turbulent flame speed is higher than the gas velocity may extent in the shear layer. These two mechanism types have a competition-relation on the ignition.
引文
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