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Institute
BTU
Verbesserte Vorauslegung des Kerntriebwerks mithilfe eines kaskadierten Optimierungsprozesses
(2018)
Due to their high complexity, aero engine development
is a time-consuming and cost-intensive process. Therefore,
pre-developed proven aerodynamic and geometric
compressor information is often used as starting point and
transferred to new compressor designs. In the present paper,
a new approach for aerodynamic cloning of an already
existing compressor flow to a new compressor geometry by
use of a streamline curvature based Throughflow solver is
presented. Parameterized compressor quantities are
automatically modified with the help of optimization
strategies, and the resulting compressor aerodynamics are
compared to a reference design in each iteration step. The
target is to minimize the discrepancy between reference
design and new design regarding essential flow parameters
like de Haller number, Mach number etc., and thereby to
reproduce the aerodynamic image of the reference design.
Thus, already collected experience from existing compressor
flow fields can be used to reduce costs for developing as well
as testing of new compressor configurations. Conducted
investigations show a notable acceleration of the design
process in comparison to former strategies starting from
scratch while achieving an acceptable compliance of
aerodynamic parameters.