Patent ID: 6984107
Filing Date: 2006-01-10
Classification: F01D,Y02T

Abstract:
1. A turbine blade for a gas-turbine engine impeller rotationally mounted in a housing, comprising: a blade tip; a leading edge arranged upstream in a direction of flow; a trailing edge arranged downstream in the direction of flow; a blade section having a section depth parallel to the direction of flow and a section thickness parallel to a direction of travel of the turbine blade; and an abrasive coating provided on the blade tip and having an effective length corresponding to the section thickness along the section depth; wherein the blade tip with the abrasive coating is configured to brush against an abrasion coating provided on a surrounding housing, the abrasive coating provided on the blade tip arranged to contact the abrasion coating having an effective length along the section depth greater than and at least equal to a predefined, minimum dimension; wherein the abrasive coating has a flattened area in a region of at least one of the leading edge and the trailing edge, the flattened area substantially parallel to the direction of travel of the turbine blade and substantially perpendicular to the direction of flow.