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Ringgitterprüfstand Göttingen (RPG)
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Non-Rotating Annular Test Facility Göttingen (RPG)
General data
Task: Aeroelastic investigations (flutter, aerodynamic excitation) of compressor and turbine blades.
Location: Institute of Aeroelasticity, Göttingen
Design and initial deployment: Ecole Polytechnique Fédérale de Lausanne (LTT)
Technical data
Technische Skizze RPG
Test section for annular cascade with subsonic and transonic compressor or turbine blading
Outer diameter of the measuring section: 400 mm
Blade height: 40 mm
Max. inlet Mach number: 1.3 for compressor cascades
Max. outlet Mach number: 1.7 for turbine cascades
Max. mass flow: 12 kg/s
Investigations of non-rotating annular cascade: realistic inlet flow conditions of the blades (7) by radial-axial deflection with pre-swirl in the radial nozzle (5,6)
Electromagnetic excitation of the blades to controlled oscillations in magnitude and phase
Aerodynamic probe measurement up and downstream the annular cascade
Simple instrumentation of the non-rotating annular cascade
Aerodynamic excitation and vibration response measurements (forced response) by optional rotating struts upstream of the annular cascade
Application areas
Development and optimization of new blade profiles to increase energy efficiency of aircraft engines and power generation turbines
Aeroelastic investigations of blade profiles for aircraft engines and stationary gas and steam turbines
Experimental flutter investigations of compressor and turbine airfoils
Experimental investigations of aerodynamic excitation and forced vibration response of turbine and compressor airfoils
Unsteady pressure distribution measurements on the airfoil surfaces using built-in pressure sensors (improved spatial resolution possible due to non-rotating conditions)
Optical flow measurements and visualization through simple and permanent optical accessibility (no trigger needed at a specific rotation position)
Literature
Bölcs, A., 1983. A Test Facility for the Investigation of Steady and Unsteady Transonic Flows in Annular Cascades. ASME Paper 83-GT-34
Belz, J., Hennings, H., 2006. Experimental Flutter Investigations of an Annular Compressor Cascade: Influence of Reduced Frequency on Stability. K.C.Hall, R.E.Kielb, J.P.Thomas (Eds.): Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines, Springer, pp.77—91
Belz, J., Hennings, H., Kahl, G., 2010. Experimental Investigation of the Forcing Function and Blade's Forced Pitching Oscillations of an Annular Compressor Cascade in Transonic Flow. ASME Paper GT2010-23590
Chenaux, V.A., 2012. Experimental Investigation of the Aeroelastic Stability of an Annular Compressor Cascade at Reverse Flow Conditions. Ecole Polytechnique Fédérale de Lausanne, Thèse No 5358
Contact
Dr.-Ing. Joachim Belz
Teamleader Aeroelastic of Turbomachinary
German Aerospace Center
Institute of Aeroelasticity
Göttingen
Tel.: +49 551 709-2897
Fax: +49 551 709-2862
RPG Documents
Factsheet Non-Rotating Annular Test Facility Göttingen (RPG)
(0.29 MB)
RPG News
DLR nimmt neue Forschungsanlage für Flugzeug- und Kraftwerksturbinen in Betrieb
Read more
Related Topics
Aerodynamic
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