On the Aerodynamic Design of Axial-Flow Compressors and Turbines

Abstract

Abstract In this paper a theoretical method is presented to determine the flow of a perfect (frictionless, incompressible) fluid across a cascade built up of arbitrary airfoils. The presentation refers to compressor blading but is immediately applicable to turbine blading. The lift-coefficient curve as a function of angle of attack (or deflection-angle curve) of an arbitrary cascade can be determined in about 10 man-hours. The complete investigation of all possible cascades built up of a given airfoil (any solidity and any stagger) requires about 60 man-hours. The procedure is graphical and standardized to the extent that no mathematical knowledge is required of the computer. Agreement between theory and tests is excellent (see Figs. 19 and 20). An extension of the method is indicated whereby the detailed pressure and velocity distribution of the flow can be obtained.