Abstract
The flow field in a supersonic rotor cascade has been analyzed for different operating conditions. Cascade performance, i.e., losses, blade pressure distribution, and inlet and outlet flow angles, are obtained by testing the cascade in a supersonic wind tunnel. A numerical investigation is performed by means of a Navier-Stokes code and a shock-fitting inviscid code. The computed results are discussed and compared to the experimental data so as to determine the degree of accuracy now achieveable in the prediction of flows characterized by high Mach numbers and large viscous effects. An analysis of the unique incidence angle for different inlet Mach numbers is carried out by numerical codes and simplified methods. The predicted incidence angles are shown to be in good agreement with the experimental data.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
Similar content being viewed by others
References
Baldwin, B., and Lomax, H., 1978, “Thin Layer Approximation and Algebraic Model for Separated Turbulent Flows,” AIAA paper 78–257. 1
Bassi, F., 1978, “Calcolo non Isentropico di Flussi Supersonici per to Studio di Schiere di Pale di Turbomacchine,” Congresso Nazionale ATI, Ancona.
Bassi, F., Grasso, F., and Savini, M., 1988, “Numerical Solution of Compressible Navier-Stokes Flows,” AGARD CP-437, 1.
Boxer, E., Sterret, J.R., and Woldarskie, J., 1952, “Application of Supersonic Vortex Flow Theory to the Design of Supersonic Impulse Compressor or Turbine Blade Sections,” NACA RM L52B06.
Chauvin, J., Sieverding, C., and Griepentrog, H., 1970, “Flow in Cascades with a Transonic Regime,” Proc. of the Symposium on Flow Research on Blading, Elsevier, Amsterdam.
Colantuoni, S., Terlizzi, A., and Grasso, F.,1989, “A Validation of a Navier-Stokes 2D Solver for Transonic Turbine Cascade Flows,” AIAA paper 89–2451.
Colclough, C.D., 1966a, “Design of Turbine Blades Suitable for Supersonic Relative Inlet Velocities and the Investigation of their Performance in Cascades: Part I—Theory and Design,” J. of Mechanical Science, 8, 1.
Colclough, C.D., 1966b, “Design of Turbine Blades Suitable for Supersonic Relative Inlet Velocities and the Investigation of their Performance in Cascades: Part II—Experiments, Results and Discussion,” J. of Mechanical Science, 8, 2.
Deich, M.E., et al., 1964, “Investigation and Calculation of Axial Turbine Stages,” Wright Patterson Air Force Base, Ohio.
Eriksson, L., 1984, “Development of a Supersonic Turbine Stage for the HM60 Engine,” AIAA-84–1464.
Goldman, L., and Sculling, J., 1968, “Analytical Investigation of Supersonic Turbo-machinery Blading,” NASA TN-D- 1 4421.
Holst, T.L., 1987, “Viscous Transonic Airfoil Workshop Compendium of Results,” AIAA paper 87–1460. 1
Jameson, A., 1983, “Transonic Flow Calculations,” MAE Report no. 1651, Princeton University.
Jameson, A., Schmidt, W., and Turkel, E., 1981, “Numerical Solutions of the Euler Equations by Finite Volume Methods Using Runge-Kutta Time-Stepping Schemes,” AIAA paper n. 81–1259. 1
Kurzrock, J.W., 1989, “Experimental Investigation of Supersonic Turbine Performance,” ASME paper 89-GT-238.
Liccini, L.L., 1949, “Analytical and Experimental Investigation of 90° Supersonic Turning Passages, Suitables for Supersonic Compressors or Turbines,” NACA RM L9G07.
Meauzé, G., and Fourmaux, A., 1987, “Numerical Simulation of Flows in Axial and Radial Turbomachines Using Euler Solvers,” Small High Pressure Ratio Turbines, VKI LS 07. NASA, 1974, “Liquid Rocket Engine Turbines,” NASA SP-81110.
Ohlsson, G.O., 1964, “Supersonic Turbines,” J. of Engineering for Power, 86, 1
Jan Osnaghi, C., 1971, “Progetto di Palette ad Azione per Turbine Supersoniche,” La Termotecnica, 4. 1
Starken, H., Yongxing, Z., and Schreiber, H.A., 1984, “Mass Flow Limitation of Supersonic Blade Rows due to Leading Edge Blockage,” ASME paper 84-GT-233.
Tomé, C. 1972, “Une Application de la Methóde des Caracteristiques en Coordonnées Intrinsiques,” La Recherche Aerospatiale, 6. 1
Vanco, M.R., and Goldman, L.J., 1968, “Computer Program for Design of Two-dimensional Supersonic Nozzle with Sharp-Edged Throat,” NASA TM X-1502. 1
Verdonk, G., and Dufurnet, T., 1987, Development of a Supersonic Steam Turbine with a Single Stage Pressure Ratio of 200 for Generator and Mechanical Drive,“ Small High Pressure Ratio Turbines, VKI LS 07. 1
Verneau, A., 1987, “Supersonic Turbines for Organic Fluid Rankine Cycles from 3 to 1300 KW,” Small High Pressure Ratio Turbines. VKI LS 07. 1
Visbal, M. and Knight, D, 1984, “The Baldwin-Lomax Turbaulence Model for Two-Dimensional Shock-Wave/Boundary-Layers Interactions,” AIAA J. 22, 7.
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 1991 Springer Science+Business Media New York
About this chapter
Cite this chapter
Bassi, F., Osnaghi, C., Perdichizzi, A. (1991). Highly Loaded Turbines for Space Applications: Rotor Flow Analysis and Performance Evaluation. In: Angelino, G., De Luca, L., Sirignano, W.A. (eds) Modern Research Topics in Aerospace Propulsion. Springer, New York, NY. https://doi.org/10.1007/978-1-4612-0945-4_17
Download citation
DOI: https://doi.org/10.1007/978-1-4612-0945-4_17
Publisher Name: Springer, New York, NY
Print ISBN: 978-1-4612-6956-4
Online ISBN: 978-1-4612-0945-4
eBook Packages: Springer Book Archive