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

Experimental and Numerical Examinations of a Transonic Compressor-Stage With Casing Treatment

Schönweitz, Dirk and Goinis, Georgios and Voges, Melanie and Enders, Gerd and Johann, Eric (2013) Experimental and Numerical Examinations of a Transonic Compressor-Stage With Casing Treatment. ASME Turbo Expo 2013, 03.-07. Juni 2013, San Antonio, USA. doi: 10.1115/GT2013-95550.

Full text not available from this repository.


The flow in the blade tip vicinity of the transonic first stage of a multi-stage axial flow compressor with variable inlet guide vane (IGV) and casing treatment (CT) above the rotor is investigated experimentally and numerically with focus on the effects of the CT on flow structures and compressor performance. For the experimental part of this study, conventional performance instrumentation is used to estimate the operating condition of the compressor. Radial distributions of total temperature and total pressure are taken at the leading edges of the stators for comparison with simulations as well as for adjusting the operating conditions of the compressor. The velocity field in the rear part of the first-rotor is determined with Particle Image Velocimetry (PIV) at 90% and 96% radial height using two periscope light sheet probes. The employed PIV setup allows a spatial resolution of 0.7mm x 0.7mm and thus a similar resolution as the spatial discretization in the simulation. For the numerical part of the study, time-accurate simulations are conducted for the same operating conditions as during experiments. Additional simulations of the same configuration with smooth casing are conducted in order to estimate the effect of the CT on the flow. The examination of PIV measurements and corresponding simulations exposes complex vortical structures originating from the interaction of the rotor bow shock with the IGV trailing edge, CT, IGV wake and the tip leakage vortex. The associated induced velocities together with the general passage flow form a complex flow field with significantly altered blockage compared to a common flow field in the tip vicinity. Position and trajectory of the tip leakage vortex are deduced from interactions between tip leakage vortex and IGV wake / CT. The detailed comparison of the tip region of simulations with and without CT shows that the CT influences pressure rise and flow parameters in a wide radial range due to a radial redistribution of the flow. Correspond­ingly, a rotor with CT can achieve an increased total pressure rise compared to a rotor with smooth casing, with only minor effects on the efficiency.

Item URL in elib:https://elib.dlr.de/85524/
Document Type:Conference or Workshop Item (Speech)
Title:Experimental and Numerical Examinations of a Transonic Compressor-Stage With Casing Treatment
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Enders, GerdUNSPECIFIEDhttps://orcid.org/0000-0003-2991-364XUNSPECIFIED
Johann, EricRolls-Royce DeutschlandUNSPECIFIEDUNSPECIFIED
Date:June 2013
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:Turbomachinery, Casing Treatment, PIV, Simulation, Rig250
Event Title:ASME Turbo Expo 2013
Event Location:San Antonio, USA
Event Type:international Conference
Event Dates:03.-07. Juni 2013
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Propulsion Systems (old)
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: Schönweitz, Dirk
Deposited On:25 Nov 2013 09:17
Last Modified:21 Jul 2023 08:24

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.