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Advanced Endwall Contouring for Loss Reduction and Outflow Homogenization for an Optimized Compressor Cascade

Reutter, Oliver and Rozanski, Magdalena and Hergt, Alexander and Nicke, Eberhard (2017) Advanced Endwall Contouring for Loss Reduction and Outflow Homogenization for an Optimized Compressor Cascade. International Journal of Turbomachinery, Propulsion and Power, 2 (1), pp. 1-12. Multidisciplinary Digital Publishing Institute (MDPI). DOI: 10.3390/ijtpp2010001 ISBN EISSN 2504-186X ISSN 2504-186X

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Official URL: http://www.mdpi.com/2504-186X/2/1/1

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

Item URL in elib:https://elib.dlr.de/111566/
Document Type:Article
Title:Advanced Endwall Contouring for Loss Reduction and Outflow Homogenization for an Optimized Compressor Cascade
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Reutter, Oliveroliver.reutter (at) dlr.deUNSPECIFIED
Rozanski, Magdalenaat-fuvUNSPECIFIED
Hergt, Alexanderalexander.hergt (at) dlr.deUNSPECIFIED
Nicke, Eberhardeberhard.nicke (at) dlr.deUNSPECIFIED
Date:16 March 2017
Journal or Publication Title:International Journal of Turbomachinery, Propulsion and Power
Refereed publication:No
Open Access:Yes
Gold Open Access:Yes
In SCOPUS:No
In ISI Web of Science:No
Volume:2
DOI :10.3390/ijtpp2010001
Page Range:pp. 1-12
Editors:
EditorsEmail
Manna, Marcellomanna@unina.it
Publisher:Multidisciplinary Digital Publishing Institute (MDPI)
ISSN:2504-186X
ISBN:EISSN 2504-186X
Status:Published
Keywords:compressor; CFD; optimization; endwall contouring; cascade; outflow angle; overturning; secondary flow; corner stall; Eckenablösung; Endwandkonturierung; Sekundärströmung
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:propulsion systems
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Fan and Compressor Technologies
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Fan and Compressor
Deposited By: Reutter, Oliver
Deposited On:10 Apr 2017 12:46
Last Modified:08 Mar 2018 18:40

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