A linear aerodynamic analysis for unsteady transonic cascades

摘要: A potential flow analysis to predict unsteady airloads produced by the vibrations of turbomachinery blades operating at transonic Mach numbers is presented. The aerodynamic model includes effects blade geometry, finite mean pressure variation across row, high frequency motion, and shock motion within framework a linearized, domain formulation. equations are solved implicit, least squares, difference approximation which applicable on arbitrary grids. numerical solution for entire field determined matching rectilinear type cascade mesh, covers an extended passage region, detailed polar local extends well beyond supersonic region(s) adjacent surface. Cascades double circular arc flat plate demonstrate analysis, partially illustrate inlet number, vibration response.