Abstract: A turboengine blading member having a platform and an airfoil. The airfoil includes a pressure side, a suction side, a leading edge and a trailing edge. An upstream region of the airfoil extends from the leading edge in a direction towards the trailing edge and a downstream region of the airfoil extends from the trailing edge in a direction towards the leading edge. The airfoil is connected to the platform in the upstream region, and is disconnected from the platform in the downstream region, such that the downstream region cantilevers from the upstream region, whereby a gap is formed between a cross sectional face of the airfoil in the downstream region and an opposed surface of the platform facing the cross sectional face. A sealing member is provided inside airfoil and platform pockets and bridges the gap.