Patent ID: 7326033
Filing Date: 2008-02-05
Classification: F01D,F05D

Abstract:
1. A turbomachine blade having a circumferential fitting direction and a radial fitting direction, comprising: a blade root; an airfoil; a shroud band element; and a radial sealing strip, which runs in a circumferential direction, being arranged on the shroud band element which is arranged on a tip-side end of the airfoil, a thickness of which sealing strip varies in the circumferential direction such that the sealing strip has a first thickness at a position of the airfoil, and wherein the thickness of the sealing strip in regions lying on an outside as viewed in the circumferential fitting direction is smaller than the first thickness, wherein an inflow-side sealing strip and an outflow-side sealing strip are provided, and wherein only the thickness of the inflow-side sealing strip varies.