In this paper, we describe the structures that produce a spike-type route to rotating stall and explain the physical mechanism for their formation. The descriptions and explanations are based on numerical simulations, complemented and corroborated by experiments. It is found that spikes are caused by a separation at the leading edge due to high incidence. The separation gives rise to shedding of vorticity from the leading edge and the consequent formation of vortices that span between the suction surface and the casing. As seen in the rotor frame of reference, near the casing the vortex convects toward the pressure surface of the adjacent blade. The approach of the vortex to the adjacent blade triggers a separation on that blade so the structure propagates. The above sequence of events constitutes a spike. The computed structure of the spike is shown to be consistent with rotor leading edge pressure measurements from the casing of several compressors: the centre of the vortex is responsible for a pressure drop and the partially blocked passages associated with leading edge separations produce a pressure rise. The simulations show leading edge separation and shed vortices over a range of tip clearances including zero. The implication, in accord with recent experimental findings, is that they are not part of the tip clearance vortex. Although the computations always show high incidence to be the cause of the spike, the conditions that give rise to this incidence (e.g., blockage from a corner separation or the tip leakage jet from the adjacent blade) do depend on the details of the compressor.
Skip Nav Destination
Article navigation
Research-Article
Origins and Structure of Spike-Type Rotating Stall
G. Pullan,
G. Pullan
1
Visiting Associate Professor
Gas Turbine Laboratory,
Gas Turbine Laboratory,
Massachusetts Institute of Technology
,77 Massachusetts Avenue
,Cambridge, MA 02139
1Present address: Whittle Laboratory, University of Cambridge, 1 JJ Thomson Avenue, Cambridge CB3 0DY, UK.
Search for other works by this author on:
A. M. Young,
A. M. Young
Whittle Laboratory,
University of Cambridge
,1 JJ Thomson Avenue
,Cambridge CB3 0DY
, UK
Search for other works by this author on:
I. J. Day,
I. J. Day
Whittle Laboratory,
University of Cambridge
,1 JJ Thomson Avenue
,Cambridge CB3 0DY
, UK
Search for other works by this author on:
E. M. Greitzer,
E. M. Greitzer
Gas Turbine Laboratory,
Massachusetts Institute of Technology
,77 Massachusetts Avenue
,Cambridge, MA 02139
Search for other works by this author on:
Z. S. Spakovszky
Z. S. Spakovszky
Gas Turbine Laboratory,
Massachusetts Institute of Technology
,77 Massachusetts Avenue
,Cambridge, MA 02139
Search for other works by this author on:
G. Pullan
Visiting Associate Professor
Gas Turbine Laboratory,
Gas Turbine Laboratory,
Massachusetts Institute of Technology
,77 Massachusetts Avenue
,Cambridge, MA 02139
A. M. Young
Whittle Laboratory,
University of Cambridge
,1 JJ Thomson Avenue
,Cambridge CB3 0DY
, UK
I. J. Day
Whittle Laboratory,
University of Cambridge
,1 JJ Thomson Avenue
,Cambridge CB3 0DY
, UK
E. M. Greitzer
Gas Turbine Laboratory,
Massachusetts Institute of Technology
,77 Massachusetts Avenue
,Cambridge, MA 02139
Z. S. Spakovszky
Gas Turbine Laboratory,
Massachusetts Institute of Technology
,77 Massachusetts Avenue
,Cambridge, MA 02139
1Present address: Whittle Laboratory, University of Cambridge, 1 JJ Thomson Avenue, Cambridge CB3 0DY, UK.
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 9, 2014; final manuscript received August 11, 2014; published online November 18, 2014. Editor: Ronald Bunker.
J. Turbomach. May 2015, 137(5): 051007 (11 pages)
Published Online: May 1, 2015
Article history
Received:
August 9, 2014
Revision Received:
August 11, 2014
Online:
November 18, 2014
Citation
Pullan, G., Young, A. M., Day, I. J., Greitzer, E. M., and Spakovszky, Z. S. (May 1, 2015). "Origins and Structure of Spike-Type Rotating Stall." ASME. J. Turbomach. May 2015; 137(5): 051007. https://doi.org/10.1115/1.4028494
Download citation file:
Get Email Alerts
Related Articles
Large-Scale Detached-Eddy Simulation Analysis of Stall Inception Process in a Multistage Axial Flow Compressor
J. Turbomach (July,2017)
Prestall Behavior of a Transonic Axial Compressor Stage via Time-Accurate Numerical Simulation
J. Turbomach (October,2008)
Calculation of Flow Instability Inception in High Speed Axial Compressors Based on an Eigenvalue Theory
J. Turbomach (June,2015)
Visualizations of Flow Structures in the Rotor Passage of an Axial Compressor at the Onset of Stall
J. Turbomach (April,2017)
Related Proceedings Papers
Related Chapters
Aerodynamic Performance Analysis
Axial-Flow Compressors
Other Components and Variations
Axial-Flow Compressors
Pulsation and Vibration Analysis of Compression and Pumping Systems
Pipeline Pumping and Compression Systems: A Practical Approach, Second Edition