Cross-band infrared laser absorption of carbon monoxide for thermometry and species sensing in high-pressure rocket flows
Cross-band infrared laser absorption of carbon monoxide for thermometry and species sensing in high-pressure rocket flows
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DOI：
10.1007/s00340-019-7320-y
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发表时间：
2019-11-01
影响因子：
2.1
通讯作者：
Spearrin, R. Mitchell
中科院分区：
文献类型：
--
作者：
Bendana, Fabio A.;Lee, Daniel D.;Spearrin, R. Mitchell
发展了一种新的跨波段激光吸收光谱技术，用于定量测量高压高温火箭燃烧流中的气体温度和一氧化碳（CO）。该策略使广泛的传感器的可操作性，同时探测振转跃迁的基本和第一泛音带的CO附近4.98 μ m和2.32 μ m，分别维持大的差异，尽管碰撞加宽的温度依赖性。扫描波长调制光谱学方法被集成用于在恶劣的火箭操作环境中的噪声抑制。在压力高达75巴的RP-2/GOx和CH-4/GOx推进剂组合的单元件喷射器火箭燃烧室上进行了使用交叉带测温技术的初步实验。测量的第一泛音带头（2.32 μ m）保持足够的信号噪声在更高的压力（高达105巴），虽然偏离频谱模拟显着。考虑到在高气体密度的碰撞效应，经验模型线混合，通过激波管的研究，开发，使定量解释的测量信号的温度和CO摩尔分数在火箭燃烧室。
A novel cross-band laser absorption spectroscopy technique has been developed for quantitative measurements of gas temperature and carbon monoxide (CO) in high-pressure, high-temperature rocket combustion flows. The strategy enables a broad range of sensor operability by simultaneously probing rovibrational transitions in both the fundamental and first overtone bands of CO near 4.98 mu m and 2.32 mu m, respectively, which sustain large differences in temperature dependence despite collisional broadening. Scanned-wavelength modulation spectroscopy methods are integrated for noise rejection in the harsh rocket operating environment. Initial experiments using the cross-band thermometry technique have been conducted on a single-element-injector rocket combustor with RP-2/GOx and CH4/GOx propellant combinations at pressures up to 75 bar. Measurements of the first overtone bandhead (2.32 mu m) maintained adequate signal-to-noise at even higher pressures (up to 105 bar), although deviating significantly from spectral simulations. To account for collisional effects at high gas densities, empirical models for line mixing, developed via shock tube studies, were employed to enable quantitative interpretation of measured signals for temperature and CO mole fraction in the rocket combustor.