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]
A Design Method to Prevent Low Pressure Turbine Blade Flutter
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Stockholm, Sweden, June 2–5, 1998; ASME Paper 98-GT-575. Manuscript received by IGTI December 9, 1997; final revision received by the ASME Headquarters October 20, 1999. Associate Technical Editor: R. Kielb.
Panovsky, J., and Kielb, R. E. (October 20, 1999). "A Design Method to Prevent Low Pressure Turbine Blade Flutter ." ASME. J. Eng. Gas Turbines Power. January 2000; 122(1): 89–98. https://doi.org/10.1115/1.483180
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