Trailing edge injection enables control of the detached and unsteady flow within the base region. The interaction of the jet with the base region alters the flow topology causing pressure bifurcations at the trailing edge that affect the aerodynamic performance of the system and modify the vortex patterns downstream the body. The purpose of this work is to fully characterize the physical effects related to the use of base bleed on the trailing edge of an airfoil at subsonic conditions. Defining a non-dimensional base bleed rate $C_b=\dot{m}/{\rho }_{\infty }{U}_{\infty }h$, a wide range from $C_b=0$ to $C_b=1$ is applied to a simplified model of a turbine blade. The influence of the trailing edge geometry shape is also evaluated, showing that rounded geometries have the potential to minimize the undesirable effects of the injection. Vortex shedding is neutralized when the (non-dimensional) ejected mass flow exceeds the value of $C_b=0.8$ and $C_b=0.55$ for straight and rounded geometries, respectively. Additionally, neutralization of the shedding also occurs for relatively low base bleed rates, often accompanied by the onset of a non-symmetrical configuration at the trailing edge. This work has particular relevance in aerothermal gas turbine design, where coolant flow may be ejected at the trailing edge to ensure adequate thermal protection of the airfoils.

后缘注射能够控制基础区域内的分离流动和不稳定流动。射流与基部区域的相互作用改变了流动拓扑结构，从而在后缘造成压力分叉，从而影响系统的空气动力学性能并改变了人体下游的涡流模式。这项工作的目的是全面表征与在亚音速条件下机翼后缘使用基础放气有关的物理效应。定义无量纲基本流失率$C_b=\dot{米}/{\rho }_{\infty }{ü}_{\infty }H$，范围从 $C_b=0$ 至 $C_b=\mathrm{1个}$将其应用于涡轮叶片的简化模型。还评估了后缘几何形状的影响，显示出圆角的几何形状具有将注射的不良影响降至最低的潜力。当（无量纲的）喷射质量流量超过的值时，涡旋脱落被抵消。$C_b=0.8$ 和 $C_b=0.55$分别用于直线和圆形几何。另外，脱落的中和也发生在较低的基本渗出率的情况下，通常伴随着在后缘的不对称构型的出现。这项工作与空气热力燃气轮机的设计特别相关，在该设计中，冷却剂流可能会在后缘喷出，以确保对翼型件进行充分的热保护。