Meshfree reduced order model for turbomachinery blade flutter analysis

0556768 - ÚT 2023 RIV GB eng J - Článek v odborném periodiku
Prasad, Chandra Shekhar - Kolman, Radek - Pešek, Luděk
Meshfree reduced order model for turbomachinery blade flutter analysis.
International Journal of Mechanical Sciences. Roč. 222, May (2022), č. článku 107222. ISSN 0020-7403. E-ISSN 1879-2162
Grant CEP: GA ČR(CZ) GA20-26779S; GA MŠMT(CZ) EF15_003/0000493; GA TA ČR(CZ) TN01000007
Institucionální podpora: RVO:61388998
Klíčová slova: aeroelastic instability * turbomachinery blade flutter * hybrid 3D panel method * reduced order aeroelastic model * boundary element method * discrete vortex particle method
Obor OECD: Applied mechanics
Impakt faktor: 7.3, rok: 2022
Způsob publikování: Omezený přístup
https://www.sciencedirect.com/science/article/pii/S002074032200145X

The paper introduces a development and application of boundary element based meshfree reduced order model for subsonic flutter analysis of turbomachinery blade cascade. The prime objective of the present work is to demonstrate the efficient use of meshfree hybrid boundary element method for subsonic flutter analysis of low pressure stage steam turbine blades . The meshfreincompressible fluid solver is developed employing 3D inviscid panel method . To model the flow separation inviscid-PM is hybridized with integral boundary layer approach using inviscid-viscous coupling mechanism along with discrete vortex particle method. A 3D annular test cascade is modeled using proposed meshfree solver for the flutter analysis. The comparison of estimated pressure coefficient and aerodynamic damping highlights a good agreement with experimental data and mesh based CFD-model’s results. Moreover, it have observed that the computational time for flutter analysis using proposed method is significantly lower compared to traditionally used CFD based numerical models for subsonic flutter in 3D blade cascade.
Trvalý link: http://hdl.handle.net/11104/0331233