Aeroelastic effects of mistuning and coupling in turbomachinery bladings

摘要: A numerical method has been developed to study the effects of structural mistuning on aeroelastic behaviour turbomachinery cascades. The specific objectives work presented here were following: was be that can assess major in a cascade sub- and transonic flow situations. influence mechanical aerodynamic coupling between blades as well multiple modes for each blade included. Accurate representations forces, taken from modern three-dimensional unsteady solver used. should applicable design use, meaning it supply results quickly large number configurations. applicability accuracy demonstrated by comparison available data recent experiments. parameters stability resonant amplitude representative test cases assessed. approach used achieve these goals is combination linearised Euler calculations with modal reduction technique, where properties are represented only few eigenmodes. validated applied two cases, comprising compressor rotor high pressure turbine rotor. Both designs. final conclusions this are: newly capable dominant cascades, including adjacent arbitrarily complex modeshapes. In method, characteristics accurately using generalised coefficients derived solver, both simplifications employed significantly contribute computational efficiency making purposes assessment parametric variations or statistical studies stochastically mistuned current successfully experimental data. favourable agreement measured computed results. Based validations, selected cases. show wide range phenomena, dependent type strength mistuning, frequency, modeshape interblade phase angle. highlight close inter-dependence eigenvalue analysis amplitudes forced response analysis.