This paper presents an analytical study of flow redistribution in a compressor stage due to asymmetric tip clearance distribution. The entire stage is modeled as an actuator disk and it is assumed that upstream and downstream flow fields are determined by the local tip clearance. The flow is assumed to be inviscid and incompressible. First, an axisymmetric flow model is used to connect upstream and downstream flows. Second, a linear perturbation approximation is used for nonaxisymmetric analysis in which each flow variable is assumed to consist of a mean (axisymmetric value) plus a small perturbation (asymmetric value). Thus, the perturbations in velocity and pressure induced by the tip clearance asymmetry are predicted. Furthermore, rotordynamic effects of such flow nonuniformity are examined as well. [S0889-504X(00)01404-5]
Skip Nav Destination
e-mail: sjsong@snu.ac.kr
Article navigation
October 2000
Technical Papers
Nonuniform Flow in a Compressor Due to Asymmetric Tip Clearance
Seung Jin Song,
e-mail: sjsong@snu.ac.kr
Seung Jin Song
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Korea
Search for other works by this author on:
Seung Ho Cho
Seung Ho Cho
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Korea
Search for other works by this author on:
Seung Jin Song
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Korea
e-mail: sjsong@snu.ac.kr
Seung Ho Cho
School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Korea
Contributed by the International Gas Turbine Institute and presented at the 45th International Gas Turbine and Aeroengine Congress and Exhibition, Munich, Germany, May 8–11, 2000. Manuscript received by the International Gas Turbine Institute February 2000. Paper No. 2000-GT-416. Review Chair: D. Ballal.
J. Turbomach. Oct 2000, 122(4): 751-760 (10 pages)
Published Online: February 1, 2000
Article history
Received:
February 1, 2000
Citation
Song, S. J., and Cho, S. H. (February 1, 2000). "Nonuniform Flow in a Compressor Due to Asymmetric Tip Clearance ." ASME. J. Turbomach. October 2000; 122(4): 751–760. https://doi.org/10.1115/1.1308569
Download citation file:
Get Email Alerts
The Cooling Effect of Combustor Exit Louver Scheme on a Transonic Nozzle Guide Vane Endwall
J. Turbomach (July 2025)
Aerodynamic Performance Evaluation of Subsonic Compressor Cascade Blade With Leading-Edge Damage
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
Modeling Shrouded Stator Cavity Flows in Axial-Flow Compressors
J. Turbomach (January,2000)
Numerical Simulation of the Flow Pulsations Origin in Cascades of the Rear Blade Rows in a Gas Turbine Axial Compressor Using Low Calorific Fuel
J. Turbomach (July,2010)
Unsteady Flow and Whirl-Inducing Forces in Axial-Flow Compressors: Part II—Analysis
J. Turbomach (July,2001)
Unsteady Flow and Whirl-Inducing Forces in Axial-Flow Compressors: Part I—Experiment
J. Turbomach (July,2001)
Related Proceedings Papers
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Other Components and Variations
Axial-Flow Compressors
Aerodynamic Performance Analysis
Axial-Flow Compressors