Cranstone, AW and Pullan, G and Curtis, EM and Bather, S (2013) Aerodynamic design of high end wall angle turbine stages-part I: Methodology development. Journal of Turbomachinery, 136. ISSN 0889-504XFull text not available from this repository.
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 bladeto-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. © 2014 by ASME.
|Divisions:||Div A > Turbomachinery|
|Depositing User:||Cron Job|
|Date Deposited:||07 Mar 2014 12:04|
|Last Modified:||08 Dec 2014 02:16|