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The Effect of a Bend-Slot Casing Treatment on the Blade Tip Flow Field of a Transonic Compressor Rotor

Voges, Melanie and Willert, Christian and Mönig, Reinhard and Schiffer, H.-P. (2013) The Effect of a Bend-Slot Casing Treatment on the Blade Tip Flow Field of a Transonic Compressor Rotor. In: ASME-Paper, GT2013-94006. ASME Turbo Expo: Power for Land, Sea and Air, 2013-06-03- 2013-06-07, San Antonio, Texas, USA.

Full text not available from this repository.

Abstract

The application of casing treatments (CT) is an effective measure to increase the stable operating range of modern aero engine or gas turbine compressors. As the development and design process of optimized CT geometries is primarily based on numerical simulations, the need for accurate experimental flow field data for related code validation is increasing with the number of applications. While the stall margin enhancement and other stage characteristics can be verified using con-ventional measurement techniques such as pressure and temperature probes, a deeper insight to the aerodynamic effect of the CT on the rotor flow field can only be provided using non-intrusive, laser-based flow field diagnostics, given that optical access to the compressor stage can be established. The investigation presented herein involved particle image velocimetry (PIV) measurements at high spatial resolution in the blade tip region of the Darmstadt Transonic Compressor Rotor-1 under the influence of a bend-slot CT. Tangential PIV measurement planes were placed at 95% span as well as in the tip gap of the rotor. The investigation included operating conditions at the aerodynamic design point (peak efficiency) and near stall conditions at 100% rpm. Additional reference measurements were performed with the untreated, smooth casing. The experimental study was accomplished by numerical simulations of the same compressor and CT geometry using the DLR TRACE code. Based on the combination of both, experimental and numerical flow field results, a detailed analysis of the shock structures and the tip clearance vortex under the influence of the CT was performed. Under the influence of the CT, the fluid exchange between rotor passage and CT slots – driven by the pressure gradient over the blade tip and the leading edge bow shock, respectively – induces secondary flow structures in the tip vortex regime. At near stall conditions the periodical injection of energized fluid out of the CT cavities was identified to be one of the major effects stabilizing the tip clearance vortex and hence delaying the onset of rotating stall.

Item URL in elib:https://elib.dlr.de/82781/
Document Type:Conference or Workshop Item (Speech, Paper)
Title:The Effect of a Bend-Slot Casing Treatment on the Blade Tip Flow Field of a Transonic Compressor Rotor
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Voges, Melaniemelanie.voges (at) dlr.deUNSPECIFIED
Willert, Christianchris.willert (at) dlr.deUNSPECIFIED
Mönig, Reinhardreinhard.moenig (at) dlr.deUNSPECIFIED
Schiffer, H.-P.Technische Universität DarmstadtUNSPECIFIED
Date:3 June 2013
Journal or Publication Title:ASME-Paper, GT2013-94006
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:PIV, casing treatment, compressor, numerical simulation, secondary flow, tip clearance vortex
Event Title:ASME Turbo Expo: Power for Land, Sea and Air
Event Location:San Antonio, Texas, USA
Event Type:international Conference
Event Dates:2013-06-03- 2013-06-07
Organizer:IGTI
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 - Virtual Engine and Validation Methods (old)
Location: Köln-Porz
Institutes and Institutions:Institute of Propulsion Technology
Institute of Propulsion Technology > Engine Measurement Systems
Deposited By: Voges, Melanie
Deposited On:10 Jul 2013 14:42
Last Modified:10 Jul 2013 14:42

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