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Axisymmetric Casing Optimization for Transonic Compressor Rotors

Kröger, Georg and Voß, Christian and Nicke, Eberhard (2010) Axisymmetric Casing Optimization for Transonic Compressor Rotors. ISROMAC 13, 04.-09. April 2010, Honolulu, USA .

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In the present work, a method for tip clearance loss reduction by casing contouring above a transonic rotor with a constant clearance height is presented. The proposed method is found to be effective especially at design point conditions, which marks an important difference to nearly all well known casing treatment configurations. The Stage 3 of the DLR test RIG 250 was used as vehicle for the following work. In order to achieve a well increased performance of Stage 3 of the test rig an automated process chain is used to couple the DLR in house Optimizer AutoOpti (Voß et al., 2006; Siller et al., 2009) with the DLR 3D Navier-Stokes flow solver TRACE (Kügeler, 2004; Nürnberger, 2004). Kriging and neural networks are used as accelerating surrogate metamodels in the optimization process. It has been found that similar to casing contouring in high pressure stages (Kröger et al., 2009b) an optimized casing and blade tip contour in transonic stages with small clearance heights lead to a smaller overall pressure loss coefficient of the clearance flow so that the endwall blockage can be reduced and the stage performance can be improved up to 0.4% at design point conditions.

Item URL in elib:https://elib.dlr.de/64955/
Document Type:Conference or Workshop Item (Speech, Paper)
Title:Axisymmetric Casing Optimization for Transonic Compressor Rotors
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Date:April 2010
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:axisymmetric, casing contour, compressor, rotor
Event Title:ISROMAC 13
Event Location:Honolulu, USA
Event Type:international Conference
Event Dates:04.-09. April 2010
HGF - Research field:other
HGF - Program:other
HGF - Program Themes:L TT - Triebwerkstechnologien (old), E VG - Combustion and Gas Turbine Technologies (old)
DLR - Research area:Energy, Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):E - Gasturbine (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology > Fan and Compressor > Fan and Compressor Technology
Institute of Propulsion Technology > Fan and Compressor
Deposited By: Kröger, Georg Philipp
Deposited On:16 Aug 2010 07:36
Last Modified:16 Aug 2010 07:36

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