周向总压畸变进气下叶片前掠对转子稳定性的影响

史亚锋; 吴虎; 黄健; 杨金广

周向总压畸变进气下叶片前掠对转子稳定性的影响

西北工业大学动力与能源学院, 西安 710072

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出版历程
- 收稿日期: 2011-05-02
- 修回日期: 2011-06-30
- 刊出日期: 2012-03-28

Effect of forward swept blade on rotor stability under inlet circumferential total pressure distortion

School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China

摘要

摘要: 以跨声速压气机NASA转子11为原型进行前掠改进,对得到的前掠转子与原型转子内流场进行了定常数值模拟,结果表明:在设计转速下前掠转子的性能有所提高,尤其是近失速流量有明显的降低.在周向总压畸变进气条件下,对转子11和前掠转子进行了非定常数值模拟,两者的性能较均匀进气条件下都出现了不同程度的下降,但前掠转子的近失速流量仍明显低于转子11,这是因为转子11叶尖区域处气流较前掠转子更易堵塞.
- 前掠转子 /
- 周向总压畸变进气 /
- 静压差 /
- 叶尖 /
- 失速
Abstract: A forward swept rotor was produced on the basis of transonic compressor NASA rotor 11 original geometry.The steady flow fields of this forward swept rotor and rotor 11 have been numerically simulated under design rotation speed,which shows that the performance of forward swept rotor especially the stall margin has been improved.The unsteady simulation of the flow fields of forward swept rotor and rotor 11 indicates that the inlet circumferential total pressure distortion has caused the deterioration of performance.However the forward swept rotor has lower mass flow near stall point compared with the original rotor 11 under the inlet circumferential pressure distortion,because the flow field near the blade tip region benefits from the forward swept rotor.
- forward swept rotor /
- circumferential total pressure distortion inlet /
- static pressure difference /
- blade tip /
- stall

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参考文献(18)

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