Handbook of Turbomachinery Second Edition Revised - Ventech!

Figure 2 Intersecting S1 and S2 surfaces in a blade row. (Wu [2]).
the unknown components at the same point on the intersecting S2 surface.
Therefore, the ‘‘Quasi-3-D’’ solutions for each plane are coupled through
the out-of-plane velocity components. Using an iterative (guess-and-correct)
technique and the continuity equation, the final Quasi-3-D solution can be
achieved, but not without considerable work.
Computer performance restrictions as well as a lack of good
turbulence modeling capability usually required that the assumption of
inviscid flow (potential or Euler form) be made for the bulk flow through the
turbine. Use of these inviscid assumptions, of course, limits accuracy
primarily because we cannot deal with flow separation.
Wu’s method or derivatives thereof became quite popular through the
1950s until the mid-1980s, when sufficient computing power became
Copyright © 2003 Marcel Dekker, Inc.