Patent ID: 9739156
Date: 2017-08-22
CPC Classifications: F01D,F05D,Y10T

Claim:
1. A rotor blade for a turbine or compressor stage of a gas turbine, the rotor blade comprising: a radially outer shroud having a sealing fin array having a first sealing fin and a second sealing fin adjacent to the first sealing fin and connected to the first sealing fin by a first groove base having a circumferential region of maximum radial height and located at a first circumferential position, the sealing fin array having a third sealing fin adjacent to the second sealing fin and opposite to the first sealing fin, the third sealing fin being connected to the second sealing fin by a second groove base having a further circumferential region of maximum radial height located at a second circumferential position different from the first circumferential position.