Transonic Cascade Wind Tunnel (TGK)

Transonic Cascade Wind Tunnel
Oil streak pattern of the corner region between endwall an profile suction side (M = 0.7)
Schlieren picture if the shock system of a transonic profile (M = 1.25)

Measured values

  • static pressure on profile and endwalls
  • Pitotsonden
  • 3-hole and 5-hole wakeprobes
  • 2-hole angleprobes
  • boundary layer total pressure rake
  • temperature probes
  • angle and velocity (by means of L2F system)
  • angle and velocity distribution in the S1 plane (by means of PIV system)
  • flow visualisation by means of oil streak pattern
  • shock visualisation by means of Schlieren optics
  • visualisation of the boundary layer behaviour by means of Liquide Crystals

Description of facility

Experimental investigation of sub- and transonic flow through plane compressor cascade. The main task of the test facility is the exact determination of losses, performance parameters and working range of compressor profiles. Due to the very good optical and measuring accessibility, secondary flow phenomena can be studied in detail. The realistic blade profile can be exactly modeled in this channel by the independent adjustment of the two main aerodynamic parameters Mach number and Reynolds number. With the help of optical methods and flow visualisation, detailed analysis of the flow are performed.

Characteristic parameters of the cascade wind tunnel

  • M = 0.2 - 1.4
  • Re = 100000 - 3000000
  • Tu = 0,6 % - 4 %
  • Inflow angle: 80 deg - 160 deg

Application

Aerodynamic investigation of sub and transonic compressor cascades for

  • Experimental validation of 2D and 3D numerical flow simulations with very detailed measurement data
  • Development and verification of new profile design concepts
  • Fundamental investigations of flow phenomena in turbomachines, e.g. boundary layer development on the profiles (transition and separation), passive and active separation control, shock boundary layer interaction
  • Development and control of secondary flow and corner separation. Analysis of the effects of different side wall contouring concepts or profile alignments, as for example sweep or lean.

Literature / References

  • [1] Dorfner, C., Hergt, A., Nicke, E., Mönig, R.: Advanced Non-Axisymmetric Endwall Contouring for Axial Compressors by Generating an Aerodynamic Separator Part I: Principal Cascade Design and Compressor Application, ASME Journal of Turbomachinery, April 2011, Volume 133, Issue 2, 021026–1 – 021026–6
  • [2] Hergt, A., Dorfner, C., Steinert, W., Nicke, E., Schreiber, H. A.: Advanced Non-Axisymmetric Endwall Contouring for Axial Compressors by Generating an Aerodynamic Separator Part II: Experimental and Numerical Cascade Investigation. ASME Journal of Turbomachinery, April 2011, Volume 133, Issue 2, 021027–1 – 021027–8
  • [3] Hergt, A., Klinner, J., Steinert, W., Dorfner, C., Nicke, E.: Detailed Flow Analysis of a Compressor Cascade with a non-axisymmetric Endwall, 9th European Conference on Turbomachinery Fluid Dynamics and Thermodynamics - ETC 9, Paper No. 95, Istanbul, Turkey, 2011
  • [4] Dorfner, C.: Entwicklung eines Verfahrens zur Konstruktion nicht-rotationssymmetrischer Seitenwandkonturen in axialen Verdichtern, Dissertation. Fakultät für Maschinenbau der Ruhr-Universität Bochum, 2009. ISSN 1434-8454. Auch DLR-FB-2009-05
  • [5] Sonoda, T., Schreiber, H. A.: Aerodynamic Characteristics of Supercritical Outlet Guide Vanes at Low Reynolds Number Conditions, Proceedings of the ASME Turbo Expo 2006, Barcelona, Spain, Journal of Turbomachinery, Vol. 129, GT2006-90882. (2006)
  • [6] Schreiber, H. A., Steinert, W., Sonoda, T., Arima, T.: Advanced High-Turning Compressor Airfoils for Low Reynolds Number Condition - Part II: Experimental and Numerical Analysis. ASME Journal of Turbomachinery, Vol. 126 , October 2004, S. 482 – 492. (2004)
  • [7] Schreiber, H. A., Steinert, W., Küsters, B.: Effects of Reynolds Number and Free-Stream Turbulence on Boundary Layer Transition in a Compressor Cascade - 2000 Heat Transfer Commitee Best Paper. ASME Journal of Turbomachinery, Vol. 124, January 2002, S. 1 – 9. (2002)
  • [8] Weber, A., Schreiber, H. A., Fuchs, R., Steinert, W.: 3-D Transonic Flow in a Compressor Cascade With Shock-Induced Corner Stall. ASME Journal of Turbomachinery, Vo. 124, July 2002, S. 358 – 366. (2002)
  • [9] Köller, U., Mönig, R., Küsters, B., Schreiber, H.A.: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines - Part I: Design and Optimization. ASME Journal of Turbomachinery, -, Vol. 122, (2000), S. 397-405
  • [10] Küsters, B., Schreiber, H.A., Köller, U., Mönig, R.: Development of Advanced Compressor Airfoils for Heavy-Duty Gas Turbines - Part II: Experimental and Theoretical Analysis. ASME Journal of Turbomachinery, -, Vol. 122, (2000), S. 406-415

Institute / Organization

DLR Institute of Propulsion Technology

Contact

Alexander Silvio Hergt
DLR Institute of Propulsion Technology

Jochen Krampe
Technology Marketing

Dr.-Ing. Alexander Born
Technology Marketing

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:

static pressure on profile and endwalls :: more

Pitotsonden :: more

3-hole and 5-hole wakeprobes :: more

2-hole angleprobes :: more

boundary layer total pressure rake :: more

temperature probes :: more

angle and velocity (by means of L2F system) :: more

angle and velocity distribution in the S1 plane (by means of PIV system) :: more

flow visualisation by means of oil streak pattern :: more

shock visualisation by means of Schlieren optics :: more

visualisation of the boundary layer behaviour by means of Liquide Crystals :: more