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1. Report No. NASA TM-87091 2 Government Accession No. USAAVSCOM-TR-85-C-12 4.Title and Subtitle Three-Dimensional Inviscid Analysis of Radial Turbine Flow and a Limited Comparison with Experimental Data 7. Author(s) Y.K. Choo and K.C. Civinskas 9. Performing Organization Name and Address NASA Lewis Research Center and Propulsion Directorate U.S. Army Aviation Research and Technology Activity (AVSCOM), Cleveland, Ohio 44135 12 Sponsoring Agency Name and Address National Aeronautics and Space Administration Washington, D.C. 20546 and U.S. Army Aviation Systems Command, St. Louis, Mo. 63120 15. Supplementary Notes 3 Recipient's Catalog No. 5. Report Date 6 Performing Organization Code 505-31-04 8 Performing Organization Report NO. E-2679 10. Work Unit No. 11. Contract or Grant No. 13. Type of Report and Period Covered Technical Memorandum 14.SponsongAgency Code Y.K. Choo, NASA Lewis Research Center; K.C. Civinskas, Propulsion Directorate, U.S. Army Aviation Research and Technology Activity (AVSCOM). Prepared for the Three-Dimensional Flow Phenomena in Fluid Machinery Symposium, ASME Winter Annual Meeting, Miami, Florida, November 17-22, 1985. 16. Abstract The three-dimensional inviscid DENTON code was used to analyze flow through a radial-inflow turbine rotor. Experimental data from the rotor are compared with analytical results obtained by using the code. The experimental data available for comparison are the radial distributions of circumferen tially averaged values of absolute flow angle and total pressure downstream of the rotor exit. The computed rotor-exit flow angles are generally underturned relative to the experimental values, which reflect the boundary-layer separation at the trailing edge and the development of wakes downstream of the rotor. The experimental rotor was designed for a higher-than-optimum work factor of 1.126 result ing ina nonoptimum positive incidence and causing a region of rapid flow adjustment and large velo city gradients. For this experimental rotor, the computed radial distribution of rotor-exit to turbine-inlet total pressure ratios are underpredicted due to the errors in the finite-difference approximations in the regions of rapid flow adjustment and due to using the relatively coarser grids inthe middle of the blade region where the flow passage ishighly three-dimensional. Additional results obtained from the three-dimensional inviscid computation are also presented, but without comparison due to the lack of experimental data. These include quasi-secondary velocity vectors on cross-channel surfaces, velocity components on the meridional and blade-to-blade surfaces, and blade surface loading diagrams. Computed results show the evolution of a passage vortex and large stream linedeviationsfromthecoiputationalstreaynwisegridlines. Experiencegained-fromapplyingthe code to a radial turbine geometry is also discussed. 17. Key Words (Suggested by Author(s)) Turbines; Three-dimensional flow; Radial flow; Inviscid flow; Aerodynamics 18. Distribution Statement Unclassified - unlimited STAR Category 02 19. Security classif. (of this report) 20. Security Classif. (of this page) 21. No. of pages 22 Price' Unclassif ed *For sale by the National Technical information Service, Springfield, Virginia 22161 . Unclassified IPDF Image | 3-D Inviscid Analysis of Radial Turbine Flow
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