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

The Effect of an Eroded Leading Edge on the Aerodynamic Performance of a Transonic Fan Blade Cascade

Hergt, Alexander and Klinner, Joachim and Steinert, Wolfgang and Grund, Sebastian and Beversdorff, Manfred and Giebmanns, Angela and Schnell, Rainer (2015) The Effect of an Eroded Leading Edge on the Aerodynamic Performance of a Transonic Fan Blade Cascade. ASME Journal of Turbomachinery, 021006-1. American Society of Mechanical Engineers (ASME). DOI: 10.1115/1.4028215 ISSN 0889-504X

Full text not available from this repository.

Abstract

Especially at transonic flow conditions the leading edge shape influences the performance of a fan profile. At the same time the leading edge of a fan profile is highly affected by erosion during operation. This erosion leads to a deformation of the leading edge shape and a reduction of the chord length. In the present experimental and numerical study, the aerodynamic performance of an original fan profile geometry is compared to an eroded fan profile with a blunt leading edge (BLE) and a chord length reduced by about 1%. The experiments are performed at a linear fan blade cascade in the Transonic Cascade Wind Tunnel of DLR in Cologne. The inflow Mach number during the tests is 1.25 and the Reynolds number 1.5�106. All tests are carried out at a low inflow turbulence level of 0.8%. The results of the investigation show that losses are increased over the whole operating range of the cascade. At the aerodynamic design point (ADP) the losses raise by 25%. This significant loss increase can be traced back to the increase of the shock losses at the leading edge. The change in shock structure is investigated and described in detail by means of particle image velocimetry (PIV) measurements and Schlieren imaging. Additionally, the unsteady fluctuation of the shock position is measured by a high-speed shadowgraphy. Then the frequency range of the fluctuation is obtained by a Fourier analysis of the time resolved shock position. Furthermore, liquid crystal measurements are performed in order to analyze the influence of the leading edge shape on the development of the suction side boundary layer. The results show that for the original fan blade the transition occurs at the shock position on the blade suction side by a separation bubble whereas the transition onset is shifted upstream for the fan blade with the BLE.

Item URL in elib:https://elib.dlr.de/97215/
Document Type:Article
Title:The Effect of an Eroded Leading Edge on the Aerodynamic Performance of a Transonic Fan Blade Cascade
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Hergt, Alexanderalexander.hergt (at) dlr.deUNSPECIFIED
Klinner, Joachimjoachim.klinner (at) dlr.deUNSPECIFIED
Steinert, WolfgangDLR-ATUNSPECIFIED
Grund, SebastianDLR-ATUNSPECIFIED
Beversdorff, Manfredmanfred.beversdorff (at) dlr.deUNSPECIFIED
Giebmanns, AngelaDLR-ATUNSPECIFIED
Schnell, RainerAT-FUVUNSPECIFIED
Date:February 2015
Journal or Publication Title:ASME Journal of Turbomachinery
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
DOI :10.1115/1.4028215
Page Range:021006-1
Publisher:American Society of Mechanical Engineers (ASME)
ISSN:0889-504X
Status:Published
Keywords:Leading Edge Performance, Transoinic Fan Blade
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: Hergt, Dr.-Ing. Alexander Silvio
Deposited On:16 Jul 2015 10:09
Last Modified:08 Mar 2018 18:53

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.