Abstract
By applying the inventive forms of the end-wall between the turbine vane/blade passage, known as end-wall contouring, sought to solve the flow aerodynamics near the end-wall area of the vane/blade. The benefits of a contoured end-wall are not restricted to the area immediately adjacent to it; they also contribute to an improvement in the vane/blade’s overall performance. But careful design is necessary due to the LP turbine’s complicated flow and different operating conditions. The primary goals of this paper were to investigate secondary flow creation and its impact on the flow field as well as to identify the region where end-wall contouring placement can help to lessen unfavorable characteristics in terms of losses. The flow behavior close to the end-wall region is significantly impacted by the incidence angle change from negative to positive. Losses are reduced when the incidence angle is negative, while they significantly increase when the incidence angle is positive. Utilizing the curved end-wall, the cross-passage pressure gradient is systematically managed to aid lower losses. Pitch-wise mass flow average secondary kinetic energy and total pressure loss coefficient were used as benchmarks to assess improvements in secondary flow loss. The selected contoured end-wall case showed 25 and 4.68 percent of Pitch-wise mass flow average secondary kinetic energy and total pressure loss coefficient improvement compare to the baseline case without end-wall contouring.
