Abstract
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Mohamed M Abo Elazm Shams Eldein
INVESTIGATION OF A NOVEL DISCRETE SLOT FILM COOLING SCHEME
The future of the gas turbine industry is strongly
relying on the development of new efficient cooling
schemes. Film cooling is one popular and reliable cooling
technique, one way to increase the film cooling
effectiveness is through the use of shaped holes. In this
paper two proposed shaped holes are being studied and
compared thoroughly against the conventional round hole
film cooling. The two proposed holes are based on the
theoretically perfect continuous slot film cooling, however,
these slots are not continuous, and preserves the solid
surface to the total blade surface ratio. The first design to
be studied is the Rectangular Divergent Slot, and the
second is the Aeroslot, which is a discrete
aerodynamically shaped slot both designs showed an
increase in the centerline film cooling effectiveness when
compared to the conventional round holes. The Aeroslot
showed a large increase in film cooling effectiveness for
the same blowing ratio, and mass flow rate of coolant,
when compared to the other shapes. A sensitivity study of
the blowing ratio to the centerline film cooling
effectiveness is carried out for several blowing ratios,
covering different jet in cross flow behaviors, fully
attached jet, and detached-reattached jet. |