二段燃焼型インジェクタを用いた超小型水素ガスタービン用試験燃焼器の燃焼特性に及ぼす二次空気噴流の影響

概要

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A two-staged combustion-type injector used in advanced high temperature combustors for hydrogen-fueled micro gas turbines was built. The concept of the injector aimed to achieve ultra-low NOx combustion by impinging the secondary air jets from the small round orifices perpendicularly on the first-stage premixed flame of φ=2.0. The combustion performance of the combustor of 40cm^3 in volume with the injector was examined varying the number of secondary air orifices, N, the injection heights, h, the overall equivalence ratio, φt, and the total air flow rate m_<at>. The findings showed that high combustion efficiencies and low NOx emissions were attained in the combustor and were insensitive to N and h. But the total pressure loss was strongly influenced by N and h. The injector of N=10 and h=10mm selected for the practical combustors was confirmed the flame formed to be quite stable having the excellent performance for combustion efficiencies over 99.7%, NOx emissions below 4ppm @O_215% and total pressure losses below 4% in the wide range of m_<at> at high φt of 0.7. In addition, the air flow rate and the volume of the practical two-staged combustor with the injectors for a micro gas turbine generationg a 3-kW output were estimated.
社団法人日本ガスタービン学会の論文
2005-09-20