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Meshfree reduced order model for turbomachinery blade flutter analysis
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SYSNO ASEP 0556768 Document Type J - Journal Article R&D Document Type Journal Article Subsidiary J Článek ve WOS Title Meshfree reduced order model for turbomachinery blade flutter analysis Author(s) Prasad, Chandra Shekhar (UT-L) ORCID
Kolman, Radek (UT-L) RID
Pešek, Luděk (UT-L) RIDNumber of authors 3 Article number 107222 Source Title International Journal of Mechanical Sciences. - : Elsevier - ISSN 0020-7403
Roč. 222, May (2022)Number of pages 18 s. Publication form Print - P Language eng - English Country GB - United Kingdom Keywords aeroelastic instability ; turbomachinery blade flutter ; hybrid 3D panel method ; reduced order aeroelastic model ; boundary element method ; discrete vortex particle method Subject RIV BI - Acoustics OECD category Applied mechanics Subject RIV - cooperation Institute of Thermomechanics - Acoustics R&D Projects GA20-26779S GA ČR - Czech Science Foundation (CSF) EF15_003/0000493 GA MŠMT - Ministry of Education, Youth and Sports (MEYS) TN01000007 GA TA ČR - Technology Agency of the Czech Republic (TA ČR) Method of publishing Limited access Institutional support UT-L - RVO:61388998 UT WOS 000798733400002 EID SCOPUS 85127625644 DOI 10.1016/j.ijmecsci.2022.107222 Annotation 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. Workplace Institute of Thermomechanics Contact Marie Kajprová, kajprova@it.cas.cz, Tel.: 266 053 154 ; Jana Lahovská, jaja@it.cas.cz, Tel.: 266 053 823 Year of Publishing 2023 Electronic address https://www.sciencedirect.com/science/article/pii/S002074032200145X
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