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A model governing the stall characteristics of an isolated axial compressor rotor

A model governing the stall characteristics of an isolated axial compressor rotor Purpose – A stall model to predict the performance of a blade row operating under rotating stall conditions, is proposed. Design/methodology/approach – The experiments were carried out on an isolated rotor row of an axial flow compressor of a radius ratio of 0.66 hub/tip. Wall static pressure tappings were used for measurement of blade row pressure rise. The mass flow rate through the machine was determined from the pressure drop at the intake. Detailed flow measurements were made using a hot wire “V” probe and transducers. An online data acquisition system was used in which data sampling was phase‐locked with respect to stall cell trailing edge. Findings – Measurements indicate that a pressure depression occurs in the stalled region. The assumption of uniform static pressure at the exit of a stalled blade row is not supported by the present work. The assumption of uniform static pressure at the exit of a stalled row together with the assumption that flow in unstalled regions operates at fixed point on the unstalled characteristic leads to the conclusion that total‐to‐static pressure rise during stalled operation is independent of blockage. This view is not supported by the experiments carried out on an isolated rotor. Research limitations/implications – Additional experimental studies for axial compressors having different rotor and blade geometries and rotor speeds, are required. Practical implications – The results can be used in the design and operation of axial compressor rotors. Originality/value – A new stall model is presented in which the behavior during stalled operation with large blockage is different from that during, low blockage. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

A model governing the stall characteristics of an isolated axial compressor rotor

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References (9)

Publisher
Emerald Publishing
Copyright
Copyright © 2005 Emerald Group Publishing Limited. All rights reserved.
ISSN
0002-2667
DOI
10.1108/00022660510585974
Publisher site
See Article on Publisher Site

Abstract

Purpose – A stall model to predict the performance of a blade row operating under rotating stall conditions, is proposed. Design/methodology/approach – The experiments were carried out on an isolated rotor row of an axial flow compressor of a radius ratio of 0.66 hub/tip. Wall static pressure tappings were used for measurement of blade row pressure rise. The mass flow rate through the machine was determined from the pressure drop at the intake. Detailed flow measurements were made using a hot wire “V” probe and transducers. An online data acquisition system was used in which data sampling was phase‐locked with respect to stall cell trailing edge. Findings – Measurements indicate that a pressure depression occurs in the stalled region. The assumption of uniform static pressure at the exit of a stalled blade row is not supported by the present work. The assumption of uniform static pressure at the exit of a stalled row together with the assumption that flow in unstalled regions operates at fixed point on the unstalled characteristic leads to the conclusion that total‐to‐static pressure rise during stalled operation is independent of blockage. This view is not supported by the experiments carried out on an isolated rotor. Research limitations/implications – Additional experimental studies for axial compressors having different rotor and blade geometries and rotor speeds, are required. Practical implications – The results can be used in the design and operation of axial compressor rotors. Originality/value – A new stall model is presented in which the behavior during stalled operation with large blockage is different from that during, low blockage.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Apr 1, 2005

Keywords: Compressors; Turbines; Aerodynamics

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