Turbine blade for the impeller of a gas-turbine engine

Abstract

In a turbine blade for a gas-turbine engine impeller, which is rotationally mounted in a housing, the turbine blade has a blade tip, a leading-edge positioned upstream in the direction of flow, and trailing edge positioned downstream, and includes a blade section, which has a section depth parallel to the direction of flow and a section thickness parallel to the direction of travel of the turbine blade. An abrasive coating, which has an effective length corresponding to the section thickness along the section depth, is applied to the blade tip, the abrasive coating of the blade tip brushing against an abrasion coating, which is introduced into the surrounding housing. Along the section depth, in particular in the region of the leading and trailing edges, the abrasive coating coming into contact with the abrasion coating has an effective length, which may always, continually or very frequently be greater, but at least equal to a predefined, minimum dimension.

Dependencies are inferred from the claim text.