A design approach to avoid flutter of low pressure turbine blades in aircraft engines is described. A linearized Euler analysis, previously validated using experimental data, is used for a series of parameter studies. The influence of mode shape and reduced frequency are investigated. Mode shape is identified as the most important contributor to determining the stability of a blade design. A new stability parameter is introduced to gain additional insight into the key contributors to flutter. This stability parameter is derived from the influence coefficient representation of the cascade, and includes only contributions from the reference blade and its immediate neighbors. This has the effect of retaining the most important contributions to aerodynamic damping while filtering out terms of less significance. This parameter is utilized to develop a stability map, which provides the critical reduced frequency as a function of torsion axis location. Rules for preliminary design and procedures for detailed design analysis are defined. [S0742-4795(00)01401-0]

Issue Section:
Gas Turbines: Structures and Dynamics
Keywords:
design engineering, gas turbines, aircraft, engines, stability, aerodynamics, damping, torsion
Topics:
Blades, Damping, Flutter (Aerodynamics), Stability, Torsion, Mode shapes, Design, Cascades (Fluid dynamics)
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Copyright © 2000
 by ASME
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