【摘要】：為研究并聯(lián)凹腔火焰穩(wěn)定器的超聲速燃燒特性,通過在凹腔上游噴注乙烯,采用單邊擴(kuò)張型燃燒室在當(dāng)量比φ=0.43~1.07內(nèi)進(jìn)行了一系列直連式燃燒試驗(yàn)。模型燃燒室入口參數(shù)為Ma=3.46,總溫Tt=1430K�；谌紵冶诿骒o壓分布、推力增益、燃料比沖和燃燒流場(chǎng)的可見光與紋影圖像分析了并聯(lián)凹腔在不同當(dāng)量比下的火焰結(jié)構(gòu)、流場(chǎng)特征和燃燒性能。結(jié)果表明,上、下壁面凹腔附近的流動(dòng)條件差異顯著,燃燒過程與當(dāng)?shù)亓鲃?dòng)條件之間的強(qiáng)烈耦合作用使得燃燒室內(nèi)火焰分布顯著不對(duì)稱。發(fā)動(dòng)機(jī)燃燒性能對(duì)當(dāng)量比十分敏感,壁面靜壓水平和推力增益隨當(dāng)量比增加持續(xù)升高,但φ=0.43~0.62時(shí)的增加速率遠(yuǎn)大于φ=0.76~1.07時(shí)的。φ=0.43~0.62時(shí),燃料比沖和燃燒效率隨當(dāng)量比增加而升高;而φ=0.76~1.07時(shí),燃料比沖和燃燒效率隨當(dāng)量比增加而降低。
[Abstract]:In order to study the supersonic combustion characteristics of the parallel-cavity flame stabilizer, a series of direct-connected combustion experiments were carried out by injecting ethylene upstream of the cavity and using a single-side expandable combustion chamber in the equivalent ratio of 1 = 0.43 to 1.07. The inlet parameter of the model combustion chamber is Ma = 3.46, and the total temperature Tt = 1430K. The flame structure, flow field and combustion performance of the parallel cavity at different equivalent ratios are analyzed based on the static pressure distribution of the combustion chamber wall, the thrust gain, the fuel ratio and the combustion flow field. The results show that there is a significant difference in the flow conditions near the upper and lower wall cavities, and the strong coupling between the combustion process and the local flow conditions makes the flame distribution in the combustion chamber significantly asymmetric. The combustion performance of the engine is very sensitive to the equivalence ratio. The increase of the static pressure level and the thrust gain of the engine increases with the increase of the equivalent ratio, but the increase rate is much greater when the equivalence ratio is 0.43-0.62. When the ratio of fuel ratio and combustion efficiency increases with the increase of the equivalent ratio, the fuel ratio and the combustion efficiency decrease with the increase of the equivalent ratio when the ratio of the fuel ratio is between 0.43 and 0.62.
【作者單位】： 國防科技大學(xué)高超聲速?zèng)_壓發(fā)動(dòng)機(jī)技術(shù)重點(diǎn)實(shí)驗(yàn)室;
【基金】：國家自然科學(xué)基金(91016028;11142010) 全國優(yōu)秀博士學(xué)位論文作者專項(xiàng)資金(201257)
【分類號(hào)】：V231.2

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