An Experimental Study on the Flow Characteristics ofa Supersonic Turbine Cascade as Pressure Ratio

  • Cho, Jong-Jae (Department of Aerospace Engineehng,Pusan Nation University) ;
  • Jeong, Soo-In (Department of Aerospace Engineehng,Pusan Nation University) ;
  • Kim, Kui-Soon (Department of Aerospace Engineehng,Pusan Nation University) ;
  • Lee, Eun-Seok (Korea Aerosoace Research Institute)
  • Published : 2004.12.31


In this paper, a small supersonic wind tunnel was designed and built to studythe flow characteristics of a supersonic impulse turbine cascade by experiment. Theflow was visualized by means of a single pass Schlieren system. The supersoniccascade with 3-dimensional supersonic nozzle was tested over a wide range ofpressure ratio. Highly complicated flow patterns including shocks, nozzle-cascadeinteraction and shock boundary layer interactions were observed.


  1. Langston, L.S., Nice, M.L. and Hooper, R.M., 1977, 'Three-Dimensional Flow Within a Turbine Cascade Passage', Trans. of the ASME, J. of Eng. for Power, Vol. 99, pp. 21-28
  2. Kiock, A., Lehthaus, F., Baines, N.C. and Sieverding, C.H., 1986, 'The Transonic Flow through a Plane Turbine Cascade as Measured in Four European Wind Tunnels', Trans. of the ASME, J. of Eng. for Gas Turbines and. Power. Vol. 108, pp. 277-85
  3. Ainley, D.G., and Mathieson, G.C.R., 1951, 'A Method of Performance Estimation for Axial Flow Turbines', British ARC. R&M 2974
  4. Dunham, J., and Came, P.M., 1970, 'Improvements to the Ainley/Mathieson Method ofTurbine Performance Prediction', ASME Journal of Engineering for Power, pp. 252-256
  5. Coldough, C. D., 1966, 'Design of turbine blades suitable for supersonic relative inlet velocities and the investigation of their performance in cascades: part II experiments, results and discussion', Journal of Mechanical Engineering Science, 8 (No. 2)
  6. Stratford, B. S. and Sansome, G. E., 1965, 'Theory and tunnel tests of rotor blades for supersonic turbines', R&M 3275