タイトル（掲載誌）JAXA Research and Development Memorandum
一般注記出版タイプ： VoR
Preliminary investigation on the roles of spray response to pressure oscillations in combustion instability was carried out for a combustor with a lean-burn coaxially-staged fuel injector for aero-engines. In this first report, two relevant attempts, still in progress, are presented, focusing on fuel flow rate response among fuel spray physical properties. Firstly, numerical experiments by LES on artificial response delay introduced as a modification to an original quasi-steady response model were performed in a similar approach to Pillai et al. (2020). Good agreement with an “optical-burner” experiment similar to Matsuura et al. (2015) was obtained at the time delays of 0.08~0.16ms, which corresponded to the phase delays of roughly 15~30deg at the frequencies of 430~500 Hz. Secondly, a newly developed response model was employed, based on the unsteady Bernoulli’s equation with adjustable coefficients. They were determined from experimental data of PIV inside the injection hole of simple cross-flow liquid jet where the air flow rate and back pressure of the injector were modulated by a siren. The model could physically explain the origin of response delay, but at the current stage, the LES result based on the model with these coefficients did not show good agreement with that of the combustion experiment. Thus, further improvements should be carried out to capture the phenomena in the experiment. This report also supplementarily includes explanation on the “optical burner” experiment and PIV of oscillating fuel flow inside the injection hole, both of which are unique features of the present experimental/numerical joint approach.
Physical characteristics: Original contains color illustrations
形態: カラー図版あり
レポート番号: JAXA-RM-24-003E
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース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