LES and CDNS Investigation of T106C Low Pressure Turbine

[+] Author and Article Information
Site Hu

College of Engineering, Peking University, Beijing, China

Chao Zhou

State Key Laboratory for Turbulence and Complex Systems, College of Engineering; BIC-EAST, Peking University Beijing, China; Collaborative Innovation Center of Advanced Aero-Engine, 100191, Beijing, China

Zhenhua Xia

School of Aeronautics and Astronautics, Zhejiang University, Hangzhou, China

Shiyi Chen

College of Engineering, Southern University of Science and Technology, Shenzhen, China

1Corresponding author.

ASME doi:10.1115/1.4037489 History: Received January 19, 2017; Revised May 23, 2017


The current study investigates the aerodynamic performance of a low pressure turbine, namely the T106C, by large eddy simulation (LES) and coarse grid direct numerical simulation (CDNS) at a Reynolds number of 100,000. Existing experimental data was used to validate the CFD tool. The effects of sub-grid scale (SGS) models, mesh densities, computational domains and boundary conditions on the CFD predictions are studied. On the blade suction surface, a separation zone starts at a location of about 55% along the suction surface. The prediction of flow separation on the turbine blade is always found to be difficult, and is one of the focuses of the current work. The ability of Smagorinsky and wall adapting local eddy viscosity (WALE) model in predicting the flow separation is compared. WALE model produces better predictions than the Smagorinsky model. CDNS produces very similar predictions to WALE model. With a finer mesh, the difference due to SGS models becomes smaller. The size of the computational domain is also important. At blade midspan, 3D features of the separated flow have an effect on the downstream flows, especially for the area near the reattachment. By further considering the effects of endwall secondary flows, a better prediction of the flow separation near the blade midspan can be achieved. The effect of the endwall secondary flow on the blade suction surface separation at the midspan is explained with the analytical method based on the Biot-Savart Law.

Copyright (c) 2017 by ASME
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