Abstract: Disclosed is an aerodynamically shaped body for use in a hot fluid flow. The body extends along a camber line from a leading edge to a trailing edge and includes at least one coolant supply plenum provided inside the body, wherein the coolant supply plenum is delimited by a body wall. The body wall extends from a first side of the camber line to a second side of the camber line and extends over the leading edge, thereby providing a leading edge wall section. At least one first leading edge cooling duct extends from an inner surface to an outer surface of the wall and is in fluid communication with the coolant supply plenum through an inlet opening and opens out onto the outer surface through a discharge opening.

Abstract: A gap seal in a gas turbine for sealing off a cooling space, formed between a heat shield and a heat shield carrier, from a hot gas space of the gas turbine. A sealing body is retained in a movable manner on the heat shield, on the one hand, and on a blade carrier, on the other hand, adjacent to the heat shield carrier.

Abstract: The invention relates to a gap seal in a gas turbine for sealing off a cooling space (6), formed between a heat shield (4) and a heat shield carrier (5), from a hot gas space (7) of the gas turbine. A sealing body (10) is retained in a movable manner on the heat shield (4), on the one hand, and on a blade carrier (2), on the other hand, adjacent to the heat shield carrier (5).