A momentum-integral analysis of the three-dimensional flow on the turbine endwall is presented. The formulation is for a compressible turbulent boundary layer with a constant streamwise shape factor. The effect of compressibility enters through a coordinate transformation and an assumed energy equation. An aerodynamic loss model is derived using inner and outer expansions. The losses decompose into frictional losses on the annulus and a vortex loss. Results are predicted for four cascade tests. In addition, previously observed trends of loss versus inlet boundary layer thickness, blade height, and blade chord are predicted. To illustrate a possible application, a parametric study is presented showing the effect on losses and heat transfer of various inlet boundary layer thickness distributions, which simulates different secondary flow configurations.
An Analysis of the Turbine Endwall Boundary Layer and Aerodynamic Losses
Booth, TC. "An Analysis of the Turbine Endwall Boundary Layer and Aerodynamic Losses." Proceedings of the ASME 1975 International Gas Turbine Conference and Products Show. Volume 1A: General. Houston, Texas, USA. March 2–6, 1975. V01AT01A022. ASME. https://doi.org/10.1115/75-GT-23
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