A hybrid incompressible boundary element based reduced ordered aeroelastic model for fast aeroelstic simulations for flexible wing and turbomachinery blade cascade

0510198 - ÚT 2020 GR eng C - Konferenční příspěvek (zahraniční konf.)
Prasad, Chandra Shekhar - Pešek, Luděk
A hybrid incompressible boundary element based reduced ordered aeroelastic model for fast aeroelstic simulations for flexible wing and turbomachinery blade cascade.
ICOVP 2019. Atény: National Technical University of Athens, 2019 - (Sapountzakis, E.), s. 1-13
[ICOVP 2019. Kréta (GR), 01.09.2019-04.09.2019]
Institucionální podpora: RVO:61388998
Klíčová slova: turbomachinery * dynamic stall flutter * boundary layer method * reduce order aeroelastic mode * blade cascade
Obor OECD: Applied mechanics

In this paper the development of medium fidelity reduced order aeroelastic model for fast execution is described. Only incompressible flow regime has been considered to model here.A boundary element based hybrid flow solver with viscous-inviscid coupling strategy have been successfully developed and implemented here. In the present paper aeroelastic modeling of flexible structures e.g. aircraft wing and steam turbine blades selected to model using the hybrid incompressibleboundary element based medium fidelity aeroelastic numerical model. The unsteady flow fieldis modeled using hybrid/modified panel method where, integral boundary layer theory (viscouspart), surface panel method ( inviscid part) and vortex particle method (separated shear layermodeling) are used together. For the structural part non-linear beam element method e.g. Timoshenko beam, based FEM structural solver is used. A weak/loose two way coupling strategy is adopted to couple the both flow and structural solver to perform co-simulation. The estimated aerodynamic lift coefficients are compared with experimental results for static and dynamic stall
flow conditions for rectangular wing. Furthermore, the results from new aeroelastic model will be compared with classical CFD-CSD based aeroelastic models for efficiency and accuracy check.The proposed methodology for the aeroelastic analysis of gas turbine or steam turbine blades orlong flexible wings will provide researchers and engineers a fast, cost effective and efficient tool for aeroelastic analysis for different design at preliminary design stage where large numbers of design
iteration are required within short time frame.
Trvalý link: http://hdl.handle.net/11104/0302582