Handbook of Turbomachinery Second Edition Revised - Ventech!

Figure 16 Time resolved heat transfer measurements and predictions at 08
incidence, Abhari et al. [41].
blade. Variations in magnitude of about a factor of up to 8 occur at each
measurement point, but location on the blade surface is by far the most
important determiner of heat-flux magnitude.
The results of the prediction are also given. The code is the 2D thinlayer
Navier–Stokes code, called UNSFLO, developed by Giles and
described in [42]. The code generally does very well, at least in a qualitative
sense, at predicting the variation of heat flux with rotor position. Heat-flux
magnitude is sometimes greater than observed and sometimes lower. In
comparing the differences between incidence angles, it is the stagnation
point and the suction side near the leading edge that seem to differ most.
This is probably due the fluctuating state of the boundary layer as the wakes
and shocks move over the leading edge and into the rotor passage. Much
more concerning the detailed flow structure is given in [42].
Aerodynamic performance measurements made in short-duration
facilities have been relatively few to date due mostly to concerns about
accuracy. One can argue, however, that with proper care acceptable
aerodynamic results are possible. Figure 17 shows results from aturbine
vane cascade test in the AFRL TRF (Joe et al. [45]), which measured
loading and loss, velocity traverses, and uncooled vane surface heat flux.
Copyright © 2003 Marcel Dekker, Inc.