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- W1926118864 abstract "The flow through a turbine cascade was numerically simulated for an exit isentropic Mach number of 0.79 and a Reynolds number of 2.8 × 10? The objective of the present study is to improve the base pressure distribution at this high subsonic Mach number. Calculation was carried out using the in-house numerical code, where the 2 nd order Roe scheme for inviscid numerical fluxes. the 2 nd order implicit dual lime method for time integration, and Delayed Detached Eddy Simulation for turbulence are employed. Time-averaged pressure distributions through the cascade have been presented with more attention paid to the trailing edge region. Calculated results show the non-uniform pressure distribution along the trailing edge, which is close to experimental data and different from almost uniform pressure distributions at moderate subsonic Mach numbers. To improve the trailing edge pressure distribution, we use an elliptic trailing edge instead of a circular one as a proposal for a new, practical trailing edge shape. The elliptic trailing edge make not only the trailing edge pressure distribution uniform but also increase the average base pressure by 5.26%." @default.
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- W1926118864 date "2008-11-01" @default.
- W1926118864 modified "2023-09-28" @default.
- W1926118864 title "Elliptic Trailing Edge for a High Subsonic Turbine Cascade" @default.
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