文献
J-GLOBAL ID:202002249905144002
整理番号:20A0066313
入口半径方向歪を伴う多段軸流圧縮機の失速マージンを拡大するための先端空気噴射【JST・京大機械翻訳】
Tip air injection to extend stall margin of multi-stage axial flow compressor with inlet radial distortion
著者 (5件):
Li Jichao
(Advanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, CAS, University of Chinese Academy of Sciences, Beijing 100190, China)
,
Du Juan
(Advanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, CAS, University of Chinese Academy of Sciences, Beijing 100190, China)
,
Geng Shaojuan
(Advanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, CAS, University of Chinese Academy of Sciences, Beijing 100190, China)
,
Li Fan
(Advanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, CAS, University of Chinese Academy of Sciences, Beijing 100190, China)
,
Zhang Hongwu
(Advanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, CAS, University of Chinese Academy of Sciences, Beijing 100190, China)
資料名:
Aerospace Science and Technology
(Aerospace Science and Technology)
巻:
96
ページ:
Null
発行年:
2020年
JST資料番号:
W1580A
ISSN:
1270-9638
資料種別:
逐次刊行物 (A)
記事区分:
原著論文
発行国:
オランダ (NLD)
言語:
英語 (EN)