A small perturbation theory is presented for the prediction of the decay of steady circumferential pressure, temperature and velocity distortions in multistage axial flow compressors. The mathematical model which is employed replaces the blade rows of the compressor by actuator disks. A closed solution for the linearized equations describing the two-dimensional, inviscid and compressible flow between the disks is derived and appropriate matching conditions at the disks (assuming a quasi-steady blade response) are determined. An efficient calculation procedure is presented which allows the rapid computation of the distortion development through any compressor configuration, i.e., through any combination of rotors, stators and axial clearances including the core engine compression system. The theory can be applied to the mean section of the compressor or separately from stream surface to stream surface. Due to the assumption of a two-dimensional flow, however, it is restricted to purely circumferential distortions in compressors with sufficiently high hub-to-tip ratios where radial flow redistributions can be expected to be small. The validity of the small perturbation theory is demonstrated by comparing the theoretical results with experimental data. In addition, the theory is used to study the effect of Mach-number and flow rate on the decay of the distortions through two compressor configurations. Suggestions are made how to utilize the theory for the design of distortion-tolerant compressors.
Skip Nav Destination
Article navigation
April 1980
This article was originally published in
Journal of Engineering for Power
Research Papers
The Prediction of Steady, Circumferential Pressure and Temperature Distortions in Multistage Axial Flow Compressors
H. Mokelke
H. Mokelke
Motoren- und Turbinen-Union Mu¨nchen GmbH, Postfach 50 06 40, 8000 Mu¨nchen 50, Germany
Search for other works by this author on:
H. Mokelke
Motoren- und Turbinen-Union Mu¨nchen GmbH, Postfach 50 06 40, 8000 Mu¨nchen 50, Germany
J. Eng. Power. Apr 1980, 102(2): 448-458 (11 pages)
Published Online: April 1, 1980
Article history
Received:
January 11, 1979
Online:
September 28, 2009
Citation
Mokelke, H. (April 1, 1980). "The Prediction of Steady, Circumferential Pressure and Temperature Distortions in Multistage Axial Flow Compressors." ASME. J. Eng. Power. April 1980; 102(2): 448–458. https://doi.org/10.1115/1.3230277
Download citation file:
Get Email Alerts
Cited By
Accelerating Chemical Kinetics Calculations with Physics Informed Neural Networks
J. Eng. Gas Turbines Power
Fully Coupled Analysis of Flutter Induced Limit Cycles: Frequency Versus Time Domain Methods
J. Eng. Gas Turbines Power (July 2023)
Impact of Ignition Assistant on Combustion of Cetane 30 and 35 Jet-Fuel Blends in a Compression-Ignition Engine at Moderate Load and Speed
J. Eng. Gas Turbines Power (July 2023)
Related Articles
Modeling Shrouded Stator Cavity Flows in Axial-Flow Compressors
J. Turbomach (January,2000)
Experimental Investigation of the Effects of a Moving Shock Wave on Compressor Stator Flow
J. Turbomach (January,2007)
Supersonic Stall Flutter of High-Speed Fans
J. Eng. Power (July,1982)
Annulus Wall Boundary Layers in Axial Compressor Stages
J. Basic Eng (March,1963)
Related Proceedings Papers
Related Chapters
Other Components and Variations
Axial-Flow Compressors
Aerodynamic Performance Analysis
Axial-Flow Compressors
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential