Annular Test Facility Goettingen (RPG)

Measured values

  • Flows
  • Pressure

Description of facility

The facility is designed to perform aeroelastic tests (flutter and forced response) of compressor and turbine blading. It was built according to plans of the Ecole Polytechnique Fédérale de Lausanne (LTT).

Technical specification:

  • Test section for annular cascades for subsonic and transonic compressor and turbine blading
  • Diameter of the test section: 400 mm
  • Blade height: 40 mm
  • max. upstream Mach number: 1,3 for compressor cascades
  • max. downstream Mach number: 1,7 for turbine cascades
  • max. mass flow: 10 m3/s
  • Investigation of non-rotating cascades: realistic upstream conditions of the blades (7) due to a radial-axial nozzle and an upstream generated pre-swirl (5,6)
  • Electromagnetic excitation of controlled blades oscillation in magnitude and phase
  • Up- and downstream probe measurements
  • Unlaboured instrumentation due to non-rotating cascades
  • Measuring aerodynamic forcing function and forced blade response by optionally installed rotating struts in front of the cascade

Located at DLR Göttingen

Application

  • Design and optimization of new blade profiles for energy efficient aero engines and more efficient turbines in power generation
  • Aeroelastic investigations of blade profiles in the field of aero engines and stationary gas and steam turbines
    • Experimental investigation of the flutter tendency of compressor and turbine profiles
    • Experimental investigation of the aerodynamic forcing function and of the forced blade response of turbine and compressor profiles
  • Measurements of the unsteady pressure distribution on the blade surface using integrated pressure sensors (easy implementation)
  • Optical measurements and visualisation of the flow field due to simple and permanent visual accessibility (no triggering to a particular rotational position)

Literature / References

  • 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

Institute / Organization

Institute for Aeroelasticity

Contact

Dr.-Ing. Joachim Belz
Institute for Aeroelasticity

Dr. Frank Holtmann
Technology Marketing

Similar Measures

Subsequent references to data sheets are given which describe with high probability similar measured values. The selection is made on the basis of semantic affinity:

Flows :: more

Pressure :: more