The structure of a computing system for bladed or unbladed turbomachinery passages is described and discussed. The system, in an overall sense, is modeled after the work of Wu, and is comprised of two coordinated computer programs, one providing solutions on rotationally symmetric blade-to-blade surfaces and the second on streamsheets roughly parallel to the blades. Both approaches utilize streamline curvature techniques.
A Nearly Three-Dimensional Intrablade Computing System for Turbomachinery
R. A. Novak,
R. A. Novak
Aerodynamics Aircraft Engine Group, General Electric Co., Lynn, Mass.
R. M. Hearsey
Hearsey Technology, Allentown, Pa.
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Novak, R. A., and Hearsey, R. M. (March 1, 1977). "A Nearly Three-Dimensional Intrablade Computing System for Turbomachinery." ASME. J. Fluids Eng. March 1977; 99(1): 154–166. https://doi.org/10.1115/1.3448517
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