Comprehensive Controlling Study of Blade Groove-induced Jets on Three-dimensional Corner Separation and Mid-span Trailing Edge Separation

Blade groove-induced jets have been shown to effectively control flow separation in compressors. However, the optimal span-wise groove layout for grooved blades still requires further investigation. This paper presents a novel groove layout method specifically designed for high-load compressor stator blades, which experience significant three-dimensional corner separation and trailing edge separation around the mid-span of the blade. The proposed approach is compared in detail with a traditional blade root groove layout and a full blade height groove layout scheme. The findings indicate that the span-wise groove layout exerts a substantial impact on the aerodynamic performance of grooved blades. In areas of the blade span where flow separation is minimal, the groove structure can exacerbate the additional mixing loss caused by the interaction between groove-induced jets and the main flow, leading to an overall increase in total pressure loss. When the groove layout aligns with the flow separation structures present in the blade passage of the baseline (BAS) cascade, it demonstrates the most effective outcomes in suppressing corner separation and mid-span trailing edge separation. On average, this method increases the airflow turning angle by ۱.۹۶°, reduces total pressure loss by ۲۰.۲%, and enhances the static pressure coefficient by ۱۱.۹% within the incidence angle range of -۶° to ۶° for the BAS cascade.

کلیدواژه ها:

Blade groove-induced jets ، Groove layout method ، Three-dimensional corner separation ، Trailing edge separation ، Total pressure loss