Abstract
A three-dimensional, linearized, unsteady, Euler analysis is being developed to efficiently predict the aeroelastic and aeroacoustic behaviors of axial-flow turbomachinery blading. The aerodynamic and numerical formulations are presented in Part 1 of this paper. In particular, the field equations and boundary conditions governing nonlinear and linearized, unsteady, inviscid flows through blade rows in cylindrical annular ducts are derived. A linearized numerical formulation, coupling a near-field, wave-split, finite-volume analysis to far-field eigenanalyses, is also described. The linearized aerodynamic and numerical models have been implemented into a three-dimensional, unsteady flow code, LINFLUX. This code is applied in Part 2 to benchmark, unsteady, subsonic flows to demonstrate its accuracy and prediction capabilities.
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Montgomery, M.D., Verdon, J.M. (1998). A 3D Linearized Euler Analysis for Blade Rows Part 1: Aerodynamic and Numerical Formulations. In: Fransson, T.H. (eds) Unsteady Aerodynamics and Aeroelasticity of Turbomachines. Springer, Dordrecht. https://doi.org/10.1007/978-94-011-5040-8_28
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DOI: https://doi.org/10.1007/978-94-011-5040-8_28
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