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Losses In Turbine and Compressor Cascades

  • Meinhard T. SchobeiriEmail author
Chapter

Abstract

The flow through a turbomachine is generally three-dimensional, viscous, highly unsteady, transitional, turbulent, and compressible. This complex flow is associated with total pressure losses caused by different flow and geometry parameters. To accurately predict the efficiency of a turbomachine, accurate flow calculation is required.

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Bibliography

  1. [1]
    Schobeiri, M. T., 2010, “Fluid Mechanics for Engineers, A Graduate Text Book,” ISBN 978-3-642-11593-6, e-ISBN 978-3-642-11594-32010 Springer-Verlag Berlin, Heidelberg.Google Scholar
  2. [2]
    Traupel, W., “Thermische Turbomaschinen,” Bd.I, 1977, Springer-Verlag Berlin Heidelberg New York.Google Scholar
  3. [3]
    Pfeil, H., 1968, “Verlustbeiwerte von optimal ausgelegten Beschaufelungs-gittern,” Energie und Technik 20, Jahrgang 1968, Heft 1, L.A. Leipzig Verlag Düsseldorf.Google Scholar
  4. [4]
    Kirchberg, G., Pfeil, H., 1971, “Einfluß der Stufenkenngrössen auf die Auslegung von HD-Turbinen,” Zeitschrift Konstruktion, 23, Jahrgang (1971), Heft 6.Google Scholar
  5. [5]
    Speidel, L., 1954, “Einfluß der Oberflächenrauhigkeit auf die Strömungs-verluste in ebenen Schaufelgittern,” Zeitschrift Forschung auf dem Gebiete des Ingenieurwesens, Band 20, Heft 5. NASA SP-36Google Scholar
  6. [6]
    NASA Report, 1965.Google Scholar
  7. [7]
    Prandtl, L., 1938, “Zur Berechnung von Grenzschichten,” ZAMM 18,77-82.Google Scholar
  8. [8]
    von Kármán , Th., 1921, “Über laminare und turbulente Reibung,” ZAMM, 1, 233-253, (1921).ADSCrossRefGoogle Scholar
  9. [9]
    Ludwieg, H., and Tillman, W., 1949, “Untersuchungen über die Wand-schubspannung in turbulenten Reibungsschichten,” Ingenieur Archiv 17, 288–299, Summary and translation in NACA-TM- 12185 (1950).Google Scholar
  10. [10]
    Lieblein, S., Schwenk, F., Broderick, R. L., 1953, “Diffusions factor for estimating losses and limiting blade loadings in axial flow compressor blade elements,” NACA RM E53D01 June 1953.Google Scholar
  11. [11]
    Schobeiri, M. T., 1998, “A New Shock Loss Model for Transonic and Supersonic Axial Compressors With Curved Blades,” AIAA, Journal of Propulsion and Power, Vol. 14, No. 4, pp. 470–478.CrossRefGoogle Scholar

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© Springer Nature Switzerland AG 2019

Authors and Affiliations

  1. 1.Department of Mechanical EngineeringTexas A&M UniversityCollege StationUSA

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