DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

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. ISSN 2504-186X.

[img] PDF

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


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
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Reutter, OliverUNSPECIFIEDhttps://orcid.org/0000-0002-2080-7691UNSPECIFIED
Hergt, AlexanderUNSPECIFIEDhttps://orcid.org/0009-0008-1643-7326UNSPECIFIED
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 ISI Web of Science:Yes
Page Range:pp. 1-12
EditorsEmailEditor's ORCID iDORCID Put Code
Publisher:Multidisciplinary Digital Publishing Institute (MDPI)
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 (old)
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:21 Nov 2023 10:26

Repository Staff Only: item control page

Help & Contact
electronic library is running on EPrints 3.3.12
Website and database design: Copyright © German Aerospace Center (DLR). All rights reserved.