Kyushu University Graduate School of Engineering
Kyushu University Graduate School of Engineering
Kyushu University Graduate School of Engineering
Babcock Hitachi K K
Kyushu University Graduate School of Engineering
Kyushu University Graduate School of Engineering
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
巻
46
ページ
295 - 300
発行年
2000-12
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 7-9 Jun. 2000 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 7-9 Jun. 2000 Tokyo Japan
Internal flow fields in low speed axial compressor and transonic compressor (NASA Rotor 37) rotors have been investigated by Navier-Stokes flow simulations. The behavior of vortices inside rotor passages was revealed by visualization techniques for identifying a vortex and an LIC (Line Integral Convolution). The simulations about the low-speed compressor rotor show the unsteady vortex behavior caused by the spiral-type breakdown of the tip leakage vortex. As the flow rate is decreased from the near-stall conditions, the movement of the tip leakage vortex due to the vortex breakdown becomes so larger that the leakage vortex interacts with the suction surface as well as the pressure one. The interaction gives rise to the three dimensional separation of the suction surface boundary layer. Furthermore, it is found that the breakdown of the tip leakage vortex in the transonic compressor rotor is caused by the interaction between the vortex and the shock wave at a near-stall condition. The expansion of the leakage vortex due to its breakdown dominates the blockage near the casing.
軸流圧縮機動翼列における翼端漏れ渦崩壊の数値シミュレーション
nalsp0046053.pdf
(2.37MB)
