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- W2024914919 abstract "Results are presented from a quasi-three-dimensional calculation of steady (relative), inviscid, adiabatic, subsonic/shock-free transonic flow on multiple hub-to-shroud stream surfaces through turbomachinery blade rows. The quasi-three-dimensional technique incorporates some three-dimensional effects while retaining much of the simplicity of two-dimensional computational methods. Three typical turbomachinery flowfield calculations are presented including an axial-flow compressor rotor, a turbine stator vane cascade, and a radial-inflow turbine rotor. The calculations were performed using quasi-three-dimensional extensions of existing two-dimensional methods. The current results represent an intermediate step in the complete quasi-three-dimensional solution process. However, the results demonstrate the usefulness of the quasi-three-dimensional technique in complementing and extending the applicability of the two-dimensional methods of turbomachinery flow analysis." @default.
- W2024914919 created "2016-06-24" @default.
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- W2024914919 date "1983-07-13" @default.
- W2024914919 modified "2023-09-23" @default.
- W2024914919 title "Quasi-three-dimensional turbomachinery flow calculations on multiplehub-to-shroud stream surfaces" @default.
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- W2024914919 doi "https://doi.org/10.2514/6.1983-1820" @default.
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