超音速輸送機用ターボジェットエンジンの低NOx燃焼器の研究 : 高圧燃焼試験結果

概要

論文の詳細を見る
A unique idea of premixture jet swirl combustor (PJSC) was proposed for the ultra low NOx combustor of a Mach 3 turbojet. The combustor installed six simple premixing chambers which were arranged at certain angles to the center axis also to the circumference axis on the combustor dome. This arrangement formed large and strong recirculating flows necessary to stabilize flame at lean fuel air ratio conditions. A single can combustor of PJSC with several fuel injectors was designed and fabricated for the high temperature and high pressure combustion test program in the HYPR project. The combustor showed stable burning for a wide range of FAR also showed combustion efficiency of 99.9% at Mach 3 cruise conditions, namely inlet temperature of 1008 K, inlet pressure of 8.3 bar and air fuel ratio of 45. PJSC-03 combustor, which installed the radiated fuel injectors and had long mixing length, presented the best NOx emissions and achieved emission index of 2 g/kg fuel at that design condition. PJSC met the emission goal of HYPR project.
社団法人日本ガスタービン学会の論文
1997-06-10