During the last decade, rapid advances have been made in the area of
flow analysis in the components of gas turbine engines. Improving the
design methods of turbomachine blade rows and under- standing of the
flow phenomena through them, has become one of the major research topics
for aE'rodynamists. This increase of research efforts is due to the need
of reducing the weight and fuel consumption of turbojet engines for the
same thrust levels. One way of achieving this is to design more
efficient components working at high local velocities. Design efforts
can lead to desired results only if the details of flow through the
blade rows are understood. It is also known that for aircraft propulsion
systems development, time and cost can be reduced significantly if the
perf ormance can be predicted with conf idence and enough precision.
This- generally iK: eds sophisticated two or three dimensional computer
codes that can give enough information for design and performance
prediction. In the recent years, designers also started to use these
sophisticated codes more and more with confidence, in connection with
computer aided design and manufacturing techniques. On the other hand,
the modelling and solution of flow and the meast