The eigenvalue problems of grouped turbo blades were numerically formulated by using the generalized differential quadrature method (GDQM). Different boundary approaches accompanying the GDQM to transform the partial differential equations of grouped turbo blades into a discrete eigenvalue problem are discussed. Effects of the number of sample points and the different boundary approaches on the accuracy of the calculated natural frequencies are also studied. Numerical results demonstrated the validity and the efficiency of the GDQM in treating this type of problem.
Eigensolutions of Grouped Turbo Blades Solved by the Generalized Differential Quadrature Method
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, New Orleans, LA, June 4–7, 2001; Paper 01-GT-273. Manuscript received by IGTI, December 2000, final revision, March 2001. Associate Editor: R. Natole.
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Kuang, J. H., and Hsu, M. H. (September 24, 2002). "Eigensolutions of Grouped Turbo Blades Solved by the Generalized Differential Quadrature Method ." ASME. J. Eng. Gas Turbines Power. October 2002; 124(4): 1011–1017. https://doi.org/10.1115/1.1492833
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