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title希薄予混合ガスタービン燃焼器で発生する振動燃焼の能動制御による抑制
Other TitleSuppression of combustion oscillations in a lean premixed gas turbine combustor by active control
Author(jpn)立花 繁; Zimmer, Laurent; 黒澤 要治; 鈴木 和雄
Author(eng)Tachibana, Shigeru; Zimmer, Laurent; Kurosawa, Yoji; Suzuki, Kazuo
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 航空プログラムグループ; 宇宙航空研究開発機構 総合技術研究本部 事業推進部
Author Affiliation(eng)Japan Aerospace Exploration Agency Institute of Aerospace Technology; Japan Aerospace Exploration Agency Institute of Aerospace Technology; Japan Aerospace Exploration Agency Aviation Program Group; Japan Aerospace Exploration Agency Program Management and Integration Department, Institute of Aerospace Technology
Issue Date2007-03-30
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication date2007-03-30
Languagejpn
AbstractAn active control of combustion driven oscillations occurring in a lean-premixed model combustor is demonstrated by means of a secondary fuel injection. An unstable condition, which leads to self-excited pressure oscillations beyond 170 dB, is chosen as control target. Keeping the inlet air temperature, the air mass flow rate and the overall equivalence ratio, respectively, at 700 K, 78 g/s and 0.50, different secondary fuel injection strategies are examined. First, a series of experiments of steady secondary fuel injection is performed using five types of injectors, with Secondary Fuel Percentage (SFP) varying from 2 to 10 percent. Effects of the angle, location and amount of injection on pressure levels are investigated. A favorable injector is selected from a point of view of control effectiveness, which is evaluated by the reduction in the peak pressure. The degree of phase-coupling between pressure and heat-release rate is visualized by a phase-locked chemiluminescence imaging technique. This information is used to detect local sources of instability. To further improve control effectiveness, a feedback control which was designed by the mixed H(sup 2)/H(sup infinity) control algorithm, is applied with the selected injector. The feedback control with 2.5 percent SFP performs peak pressure reduction of 27.7 dB, which is almost 10 dB larger than that of the steady injection method. On the other hand, little difference exists between the NO(x) emissions of the steady injection and the feedback control. An obvious effectiveness of the feedback control is confirmed without losing the low NO(x) capability.
DescriptionJAXA Research and Development Report
宇宙航空研究開発機構研究開発報告
Keywordslean combustion; combustion vibration; premixed flame; gas turbine; active control; fuel injection; combustor; combustion stability; control algorithm; feedback control; resonant frequency; 希薄燃焼; 燃焼振動; 与混合炎; ガスタービン; 能動制御; 燃料噴射; 燃焼器; 燃焼安定性; 制御アルゴリズム; フィードバック制御; 共鳴周波数
Document TypeTechnical Report
JAXA Category研究開発報告
ISSN1349-1113
SHI-NOAA0063469000
Report NoJAXA-RR-06-034
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/29037


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