Experiments and computational analyses were completed to understand the nature of shrouded stator cavity flows. From this understanding, a one-dimensional model of the flow through shrouded stator cavities was developed. This model estimates the leakage mass flow, temperature rise, and angular momentum increase through the cavity, given geometry parameters and the flow conditions at the interface between the cavity and primary flow path. This cavity model consists of two components, one that estimates the flow characteristics through the labyrinth seals and the other that predicts the transfer of momentum due to windage. A description of the one-dimensional model is given. The incorporation and use of the one-dimensional model in a multistage compressor primary flow analysis tool is described. The combination of this model and the primary flow solver was used to reliably simulate the significant impact on performance of the increase of hub seal leakage in a twelve-stage axial-flow compressor. Observed higher temperatures of the hub region fluid, different stage matching, and lower overall efficiencies and core flow than expected could be correctly linked to increased hub seal clearance with this new technique. The importance of including these leakage flows in compressor simulations is shown. [S0889-504X(00)00501-8]
Skip Nav Destination
Article navigation
January 2000
Technical Papers
Modeling Shrouded Stator Cavity Flows in Axial-Flow Compressors
S. R. Wellborn,
S. R. Wellborn
Rolls-Royce Allison, Indianapolis, IN 46206
Search for other works by this author on:
I. Tolchinsky,
I. Tolchinsky
Rolls-Royce Allison, Indianapolis, IN 46206
Search for other works by this author on:
T. H. Okiishi
T. H. Okiishi
Iowa State University, Ames, IA 50011
Search for other works by this author on:
S. R. Wellborn
Rolls-Royce Allison, Indianapolis, IN 46206
I. Tolchinsky
Rolls-Royce Allison, Indianapolis, IN 46206
T. H. Okiishi
Iowa State University, Ames, IA 50011
Contributed by the International Gas Turbine Institute and presented at the 44th International Gas Turbine and Aeroengine Congress and Exhibition, Indianapolis, Indiana, June 7–10, 1999. Manuscript received by the International Gas Turbine Institute February 1999. Paper No. 99-GT-75. Review Chair: D. C. Wisler.
J. Turbomach. Jan 2000, 122(1): 55-61 (7 pages)
Published Online: February 1, 1999
Article history
Received:
February 1, 1999
Citation
Wellborn , S. R., Tolchinsky , I., and Okiishi , T. H. (February 1, 1999). "Modeling Shrouded Stator Cavity Flows in Axial-Flow Compressors ." ASME. J. Turbomach. January 2000; 122(1): 55–61. https://doi.org/10.1115/1.555427
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
The Influence of Shrouded Stator Cavity Flows on Multistage Compressor Performance
J. Turbomach (July,1999)
Influence of Stator-Rotor Interaction on the Aerothermal Performance of Recess Blade Tips
J. Turbomach (January,2011)
Rotordynamic-Coefficients and Static (Equilibrium Loci and Leakage) Characteristics for Short, Laminar-flow Annular Seals
J. Tribol (April,2006)
Nonuniform Flow in a Compressor Due to Asymmetric Tip Clearance
J. Turbomach (October,2000)
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