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Computations of bladerow stall inception in transonic flows

Published online by Cambridge University Press:  04 July 2016

L. He  and
J. O. Ismael
L. He
Affiliation:
School of Engineering University of Durham, Durham, UK
J. O. Ismael
Affiliation:
Department of Engineering Systems, Brunel University, Uxbridge, UK
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Abstract

A three-dimensional unsteady Navier-Stokes solver has been used to simulate stall inception in a single row ten passage segment of a transonic fan, the NASA rotor-67. At subsonic flow conditions, the 3D results illustrate a rotating stall inception with short scale part-span cells rotating at around 80% rotor speed, similar to that observed in some low speed experiments. However, at a supersonic relative inflow condition, the results show that an isolated blade row tends to stall in a one-dimensional breakdown pattern without first experiencing rotating stall. At near-stall conditions, significant self-excited unsteadiness is generated by the interaction between the tip-leakage vortex and the passage shock wave. Further computations for two-dimensional configurations indicate that it is possible to have a rotating pattern of instability in transonic blade rows associated with circumferential synchronised shock oscillation.

Type
Research Article
Information
The Aeronautical Journal , Volume 103 , Issue 1025 , July 1999 , pp. 317 - 324
Copyright
Copyright © Royal Aeronautical Society 1999 

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