TY - GEN
T1 - Numerical simulation of cascade flows using block-structured cartesian mesh
AU - Koike, Masaki
AU - Kojima, Takaya
AU - Sasaki, Daisuke
AU - Misaka, Takashi
AU - Shimoyama, Koji
AU - Obayashi, Shigeru
AU - Hirakawa, Karin
AU - Tani, Naoki
N1 - Publisher Copyright:
© 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2017
Y1 - 2017
N2 - Mesh generation is one of the critical problems in numerical simulation of cascade flow, particularly cooled turbine blade. To overcome this problem, Cartesian-mesh CFD solver is focused these days. In this study, block-structured Cartesian-mesh solver, Building-Cube Method (BCM), is applied to cascade flow of T106 low pressure turbine cascade. Ghost-cell approach is employed to represent the curved surface of T106 blade. The result is compared with the result of wall boundary condition with staircase representation. As a result, Ghost-cell approach can mitigate the pressure oscillations and obtain more smooth results. The computational results are also compared with experimental results for the validation, and the similar surface pressure coefficients are obtained. However, the difference is observed at the location of laminar-turbulent transition due to the lack of mesh resolution.
AB - Mesh generation is one of the critical problems in numerical simulation of cascade flow, particularly cooled turbine blade. To overcome this problem, Cartesian-mesh CFD solver is focused these days. In this study, block-structured Cartesian-mesh solver, Building-Cube Method (BCM), is applied to cascade flow of T106 low pressure turbine cascade. Ghost-cell approach is employed to represent the curved surface of T106 blade. The result is compared with the result of wall boundary condition with staircase representation. As a result, Ghost-cell approach can mitigate the pressure oscillations and obtain more smooth results. The computational results are also compared with experimental results for the validation, and the similar surface pressure coefficients are obtained. However, the difference is observed at the location of laminar-turbulent transition due to the lack of mesh resolution.
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U2 - 10.2514/6.2017-1925
DO - 10.2514/6.2017-1925
M3 - Conference contribution
AN - SCOPUS:85017193364
T3 - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
BT - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 55th AIAA Aerospace Sciences Meeting
Y2 - 9 January 2017 through 13 January 2017
ER -