Abstract
The following paper deals with the development of an optimized non-axisymmetric endwall contour for reducing the total pressure loss and for homogenizing the outflow of a highly-loaded compressor cascade. In contrast to former studies using a NACA-65 K48 cascade airfoil this study starts with the design of a new high-performance airfoil which is based on the aerodynamic boundary conditions of the NACA-65 K48 cascade. This new airfoil is then used as a basis. Optimizations of the airfoil and of the endwall contour are performed using the German Aerospace Center (DLR) in-house tool AutoOpti and the RANS (Reynolds-averaged Navier-Stokes)-solver TRACE (Turbomachinery Research Aerodynamic Computational Environment). Three operating points at an inflow Mach number of 0.67 with different inflow angles are used to secure a wide operating range. The optimized endwall contour changes the secondary flow in such a way that the corner stall is reduced which, in turn, significantly reduces the total pressure loss. The endwall contour in the outflow region leads to a considerable homogenization of the outflow in the near wall region. Using non-axisymmetric endwall shaping demonstrates a valuable measure to further improve highly-efficient compressor blading on the vane level.
Highlights
As compressors become more and more advanced, and in order to raise the efficiency and to widen the operating range, the design space has to be enlarged and three-dimensional design features have to be taken into account
Endwall contouring (EWC): The splines consisting of the control points, define
Figure contouring (EWC): The sixsix splines consisting of the control points, which define the SC14the endwall
Summary
As compressors become more and more advanced, and in order to raise the efficiency and to widen the operating range, the design space has to be enlarged and three-dimensional design features have to be taken into account. While Reutter et al [13] used a NACA 65 K48 airfoil (National Advisory Committee for Aeornautics) as a base configuration for EWC in a cascade, this study uses an optimized airfoil It is the step in the DLR research on endwall contouring. Geometry by thethe in-house tool BladeGenerator, and calculates the database It uses this database together with metamodels and/or an evolutionary algorithm in order aerodynamic behavior for the given operating points with the 2D flow solver MISES, described by to give new promising geometries to the slavesa to be calculated. Airfoil optimization each slave creates an airfoil geometry by the DLR in-house tool BladeGenerator, and calculates the aerodynamic behavior for the given operating points with the 2D flow solver MISES, described by Youngren and Drela [18], which incorporates a mesh generation.
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