基于火焰发射光谱的火箭联合循环燃烧室空腔温度和发射率实验研究

IF 5 Q1 ENGINEERING, MULTIDISCIPLINARY
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引用次数: 0

摘要

火焰温度和光谱发射率是表征火箭联合循环(RBCC)燃烧器中燃料燃烧充分程度和颗粒辐射特性的重要参数。为研究 RBCC 燃烧器中复杂超音速火焰的燃烧特性,提出了一种结合 Levenberg-Marquardt (LM) 算法和最小二乘法的新型辐射测温方法,用于测量基于火焰发射光谱的温度、发射率和光谱辐射特性。在带激光诱导等离子体燃烧增强(LIPCE)和不带激光诱导等离子体燃烧增强的 RBCC 直接连接试验台上对火焰温度、发射率和光谱辐射特性进行了现场测量。在燃料总当量比(α)为 1.0b 和 0.6 时,有 LIPCE 的火焰平均温度比没有 LIPCE 的火焰平均温度分别高出 4.51% 和 2.08%。在激光诱导等离子体的热效应和化学效应作用下,煤油在空腔再循环区的火焰燃烧振荡趋于稳定。有 LIPCE 时,α = 1.0b 和 0.6 时的火焰温度分别为 503 K 和 523 K,比无 LIPCE 时分别低 20.07% 和 42.64%。采用甲烷辅助点火的火焰发射率比不采用甲烷辅助点火的火焰发射率低 80.46%,这是由于煤油的碳氢比高于甲烷。在 α = 1.0a(有甲烷辅助点火)、1.0b(无甲烷辅助点火)和 0.6 时,有 LIPCE 的 600 纳米处光谱发射率分别比无 LIPCE 的低 1.25%、22.2% 和 4.22%。通过归一化处理,消除了发射率中浓度的影响,从而分析了 RBCC 燃烧室中的火焰辐射特性。不使用 LIPCE 时,火焰归一化发射率的最大差异为 50.91%,使用 LIPCE 时为 27.53%。在 α = 0.6 时,火焰辐射特性在激光诱导等离子体的热效应和化学效应下趋于稳定。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Experimental investigation for temperature and emissivity by flame emission spectrum in a cavity of rocket based combined cycle combustor chamber

Flame temperature and spectral emissivity were the important parameters characterizing the sufficient degree of fuel combustion and the particle radiative characteristics in the Rocket Based Combined Cycle (RBCC) combustor. To investigate the combustion characteristics of the complex supersonic flame in the RBCC combustor, a new radiation thermometry combined with Levenberg-Marquardt (LM) algorithm and the least squares method was proposed to measure the temperature, emissivity and spectral radiative properties based on the flame emission spectrum. In-situ measurements of the flame temperature, emissivity and spectral radiative properties were carried out in the RBCC direct-connected test bench with laser-induced plasma combustion enhancement (LIPCE) and without LIPCE. The flame average temperatures at fuel global equivalence ratio (α) of 1.0b and 0.6 with LIPCE were 4.51% and 2.08% higher than those without LIPCE. The flame combustion oscillation of kerosene tended to be stable in the recirculation zone of cavity with the thermal and chemical effects of laser induced plasma. The differences of flame temperature at α = 1.0b and 0.6 were 503 K and 523 K with LIPCE, which were 20.07% and 42.64% lower than those without LIPCE. The flame emissivity with methane assisted ignition was 80.46% lower than that without methane assisted ignition, due to the carbon-hydrogen ratio of kerosene was higher than that of methane. The spectral emissivities at 600 nm with LIPCE were 1.25%, 22.2%, and 4.22% lower than those without LIPCE at α = 1.0a (with methane assisted ignition), 1.0b (without methane assisted ignition) and 0.6. The effect of concentration in the emissivity was removed by normalization to analyze the flame radiative properties in the RBCC combustor chamber. The maximum differences of flame normalized emissivity were 50.91% without LIPCE and 27.53% with LIPCE. The flame radiative properties were stabilized under the thermal and chemical effects of laser induced plasma at α = 0.6.

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来源期刊
Defence Technology(防务技术)
Defence Technology(防务技术) Mechanical Engineering, Control and Systems Engineering, Industrial and Manufacturing Engineering
CiteScore
8.70
自引率
0.00%
发文量
728
审稿时长
25 days
期刊介绍: Defence Technology, a peer reviewed journal, is published monthly and aims to become the best international academic exchange platform for the research related to defence technology. It publishes original research papers having direct bearing on defence, with a balanced coverage on analytical, experimental, numerical simulation and applied investigations. It covers various disciplines of science, technology and engineering.
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