Effect of Design Parameters of an Axial Compressor Stage on Aerodynamic Damping and Excitation of Bending Flutter of Dynamically Uniform Rotor Blades.

General relations between head characteristics of the axial compressor stage and aerodynamic damping accompanying bending stresses of rotor blades in a viscous flow of incompressible fluid are solved in a quasi-steady approximation. Using an approximate description of head characteristics of a rotor wheel, the relations between the design characteristics of a stage (flowrate coefficients, theoretical head, useful effect, and the flow twist) and aerodynamic damping, as well as critical Strouhal numbers of the bending flutter of dynamically uniform rotor blades are established and analyzed.