AbstractThe geometry of the leading-edge of a turbine blade has an important influence on the off-design aerodynamic performance. To investigate the performance of a blade with a large leading edge diameter and wedge angle, annular cascade experiments and numerical simulations were conducted at off-design conditions. Cascade experiments were carried out to obtain the static pressure distribution at the midspan in incidences ranging from -61° to 4.0° at exit Mach numbers of 0.70, 0.75, and 0.80. The corresponding Reynolds number varied from 6.35×105 to 6.78×105. Since the relevant numerical results agree well with the experimental data, the accuracy of the numerical method could be demonstrated. The trailing edge loss was decomposed into three terms and discussed in detail according to numerical simulations. The influences of the incidences and Mach numbers on flow loss of a turbine cascade were numerically investigated. The numerical results indicate that the cascade has a good off-design performance due ...
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