アクティブ制御による振動燃焼の抑制

Material type: 文書・図像類

Author: 立花, 繁ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2006-11-01

Material Format: Digital

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Note (General)：: An active control of combustion driven oscillations occurring in a lean premixed model combustor is demonstrated by means of a secondary fuel injectio...

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Material Type: 文書・図像類
Title: アクティブ制御による振動燃焼の抑制
Author/Editor: 立花, 繁
Zimmer, Laurent
黒澤, 要治
鈴木, 和雄
Tachibana, Shigeru
Kurosawa, Yoji
Suzuki, Kazuo
Author Heading: 立花, 繁
Zimmer, Laurent
黒澤, 要治
鈴木, 和雄
Tachibana, Shigeru
Kurosawa, Yoji
Suzuki, Kazuo
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2006-11-01
Publication Date (W3CDTF): 2006-11-01
Alternative Title: Active control of combustion-driven oscillations in a gas-turbine combustor
Periodical title: 宇宙航空研究開発機構特別資料: 平成18年度　宇宙航空研究開発機構　総合技術研究本部　宇宙科学研究本部　研究成果報告書 = JAXA Special Publication: Report on Research Achievements for FY2006 Institute of Space and Astronautical Science, Institute of Aerospace Technology, Japan Aerospace Exploration Agency
No. or year of volume/issue: JAXA-SP-06-006
Volume: JAXA-SP-06-006
Pages: 201-206
ISSN (Periodical Title): ISSN : 1349-113X
Text Language Code: jpn
Subject Heading: 燃焼振動
振動燃焼
ガスタービン
燃焼室
与混合炎
希薄燃焼
火炎安定性
燃焼制御
能動制御
combustion vibration
combustion-driven oscillation
gas turbine
combustion chamber
premixed flame
lean combustion
flame stability
combustion control
active control
Target Audience: 一般
Note (General): An 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. One is a steady injection method and the other is a feedback control, which was designed by the mixed H(sup 2)/H(sup infinity) control algorithm. The feedback control with three percent of secondary fuel performs peak pressure reduction of 27 dB, which is almost 10 dB larger than that of the steady injection method.
資料番号: AA0049500044
レポート番号: JAXA-SP-06-006
Access Restrictions: 限定公開
Periodical Title (NCID): AA11984031
https://ci.nii.ac.jp/ncid/AA11984031
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ