A Quasi-Three-Dimensional Turbomachinery Blade Design System: Part II—Computerized System

[+] Author and Article Information
I. K. Jennions, P. Stow

Theoretical Science Group, Rolls-Royce Limited, Derby DE2 8BJ, England

J. Eng. Gas Turbines Power 107(2), 308-314 (Apr 01, 1985) (7 pages) doi:10.1115/1.3239716 History: Received December 19, 1983; Online October 15, 2009


The purpose of this work has been to develop a quasi-three-dimensional blade design and analysis system. In Part II of the paper the computerized blade design system is presented and an example given to illustrate its use. The system comprises a streamline curvature throughflow program incorporating the analysis of Part I of this paper, a blade section stacking program, and one of a number of blade-to-blade calculation programs. The information flow between each part of the system is described and the importance of each stage in the calculation indicated. Information is transferred between programs via a data base which enables other design programs, e.g., heat transfer programs, to access the results. This modular approach enables individual design program advances to be made relatively easily. The system is flexible enough to incorporate a number of blade-to-blade programs, the one used depending on the specific application. An example of the flow through a turbine nozzle guide vane is presented. Experimental data are compared with the results from the quasi-three-dimensional system, a fully three-dimensional program and an unlinked two-dimensional system. The results from the quasi-three-dimensional system are very encouraging.

Copyright © 1985 by ASME
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