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Experimental investigation of the forcing function and forced pitching blade oscillations of an annular compressor cascade in transonic flow

Belz, Joachim and Hennings, Holger and Kahl, Gerhard (2010) Experimental investigation of the forcing function and forced pitching blade oscillations of an annular compressor cascade in transonic flow. In: Proceedings "ASME Turbo Expo 2010". ASME Turbo Expo 2010 - Gas Turbine Technical Congress & Exposition, 14-18 June 2010, Glasgow, United Kingdom.

Full text not available from this repository.

Abstract

The interaction between rotor blades and non-rotating stator blades is the most significant blade excitation mechanism in turbomachines. It is well documented in various numerical and experimental investigations for turbine cascades. Like turbine blades, also compressor blades are excited as well by potential fields of the following stator, the downstream flowfield of the stator of the previous stage or struts and incoming flow distortions. In this paper, experimental investigations of the excitation of a transonic compressor cascade due to gust generating struts upstream are presented. The experiments were performed in the test facility of non-rotating annular cascades at EPFL using a compressor cascade, which consists of 20 blades (NACA3506 profile) mounted on elastic spring suspensions for torsional motions at the midchord. For the non-rotating annular cascade, relative flow conditions similar to those present in a rotating cascade are generating by swirling the flow in front of the test test section. The struts are rotating in order to create a periodic excitation upstream of the cascade. The so generated pressure dristribution on the cascade’s profiles as well as the measured vibration response of the blades are presented and compared for a pure subsonic and a transonic flow case.

Item URL in elib:https://elib.dlr.de/65730/
Document Type:Conference or Workshop Item (Speech, Paper)
Title:Experimental investigation of the forcing function and forced pitching blade oscillations of an annular compressor cascade in transonic flow
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Belz, Joachimjoachim.belz (at) dlr.deUNSPECIFIED
Hennings, Holgerholger.hennings (at) dlr.deUNSPECIFIED
Kahl, GerhardMTU Aero EnginesUNSPECIFIED
Date:2010
Journal or Publication Title:Proceedings "ASME Turbo Expo 2010"
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:rotor blade, turbomachine
Event Title:ASME Turbo Expo 2010 - Gas Turbine Technical Congress & Exposition
Event Location:Glasgow, United Kingdom
Event Type:international Conference
Event Dates:14-18 June 2010
Organizer:International Gas Turbine Institute
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 - Turbine Technologies (old)
Location: Göttingen
Institutes and Institutions:Institute of Aeroelasticity
Deposited By: Erdmann, Daniela
Deposited On:20 Oct 2010 08:11
Last Modified:16 May 2013 10:02

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