A design methodology is presented for turbines in an annulus with high end wall angles. Such stages occur where large radial offsets between the stage inlet and stage outlet are required, for example in the first stage of modern low pressure turbines, and are becoming more prevalent as bypass ratios increase. The turbine vanes operate within s-shaped ducts which result in meridional curvature being of a similar magnitude to the blade-to-blade curvature. Through a systematic series of idealized computational cases, the importance of two aspects of vane design are shown. First, the region of peak end wall meridional curvature is best located within the vane row. Second, the vane should be leant so as to minimize spanwise variations in surface pressure—this condition is termed “ideal lean.” This design philosophy is applied to the first stage of a low pressure turbine with high end wall angles.
Aerodynamic Design of High End Wall Angle Turbine Stages—Part I: Methodology Development
University of Cambridge,
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received December 17, 2012; final manuscript received January 24, 2013; published online September 26, 2013. Editor: David Wisler.
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Cranstone, A. W., Pullan, G., Curtis, E. M., and Bather, S. (September 26, 2013). "Aerodynamic Design of High End Wall Angle Turbine Stages—Part I: Methodology Development." ASME. J. Turbomach. February 2014; 136(2): 021006. https://doi.org/10.1115/1.4023905
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