Unsteady Flow Field Investigations at Near Stall for a Transonic Compressor Rotor by Proper Orthogonal Decomposition

Abstract

The unsteady numerical simulations are conducted to research the tip clearance flow characteristic at near stall of a transonic compressor rotor. Based on the simulation results, decompose the flow fields by proper orthogonal decomposition (POD). Itsuccessfully captures theoscillation frequency 6.83kHz of the tip flow field with huge scale oscillation structures at blade leading and pressure side reveal the unsteady flow field nature. Through the reconstructed flow fields, it finds that the oscillation behaves as a circumference wave in the blade passages.