静叶时序对压气机叶片附面层流动影响的数值研究

ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2007, Vol. 28 ›› Issue (增): 62-69.

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Numerical Investigation of the Effect of Stator Clocking on Blade Boundary Layer Flow in Compressor

LI Shao-bin¹,CHEN Fu²,YAN Pei-gang²,WANG Zhong-qi²

1 National Key Laboratory of Aircraft Engine, School of Jet Propulsion, Beijing University ofAeronautics and Astronautics 2 Research Institute of Propulsion Theory and Technology, School of Energy Science and Engineering

Received:2006-10-25 Revised:2007-07-04 Online:2007-08-10 Published:2007-08-10
Contact: CHEN Fu²

Abstract

Abstract:

Numerical simulation is applied to investigate the unsteady flow fields at the midspan of a two-stage low-speed compressor. Detailed analysis of blade unsteady boundary layer flow of rotor-stator interaction condition is presented by the analysis model of rotor wake and stator boundary layer interaction under typical clocking positions of the second stator row.

Key words: rotorstator , interaction, , clocking, , boundary , layer , transition, , wake, , compressor

CLC Number:

LI Shao-bin;CHEN Fu;YAN Pei-gang;WANG Zhong-qi. Numerical Investigation of the Effect of Stator Clocking on Blade Boundary Layer Flow in Compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2007, 28(增): 62-69.

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Numerical Investigation of the Effect of Stator Clocking on Blade Boundary Layer Flow in Compressor

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