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Cooled airfoil trailing edge and method of cooling the airfoil trailing edge

机译：冷却的翼型后缘和冷却翼型后缘的方法

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摘要

An airfoil and method of cooling a airfoil including a leading edge, a trailing edge, a suction side, a pressure side and at least one internal cooling channel configured to convey a cooling fluid, is provided. A plurality of trailing edge bleed slots are in fluid communication with the at least one internal cooling channel, wherein a downstream edge of the pressure side of the airfoil lies upstream of a downstream edge of the suction side to expose the plurality of trailing edge bleed slots proximate to the trailing edge of the airfoil. The at least one internal cooling channel is configured to supply the cooling fluid from a source of cooling fluid towards the plurality of trailing edge bleed slots. A plurality of obstruction features are disposed within the at least one internal cooling channel and at a downstream edge of the remaining pressure side. The one or more obstruction features are configured having a predefined substantially polygon shape, to distribute a flow of the cooling fluid and provide distributed cooling to the plurality of trailing edge bleed slots.
机译：提供了一种翼型件和冷却翼型件的方法，该翼型件和翼型件包括前缘，后缘，吸力侧，压力侧和构造成输送冷却流体的至少一个内部冷却通道。多个后缘排气槽与至少一个内部冷却通道流体连通，其中，翼型件的压力侧的下游边缘位于吸力侧的下游边缘的上游，以暴露出多个后缘排气槽。靠近机翼的后缘。至少一个内部冷却通道被配置为从冷却流体源向多个后缘排放槽供应冷却流体。在至少一个内部冷却通道内并且在剩余压力侧的下游边缘处布置有多个障碍物特征。一个或多个阻塞特征被配置为具有预定的大致多边形的形状，以分配冷却流体的流，并向多个后缘排放槽提供分配的冷却。

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