Patent ID: 8545183
Filing Date: 2013-10-01
Classification: F01D,F04D,F05D

Abstract:
1. A rotor blade and a rotor disk for a gas-turbine engine, the rotor blade comprising: an aerofoil portion; and a root portion, the rotor disk, comprising: a slot in which the root portion is secured, wherein the root portion includes a first pair of side portions, the first pair of side portions mate with a corresponding second pair of side portions of the rotor-disk slot, wherein a first bottom portion connects the first pair of side portions, wherein a coating seals a gap between the first bottom portion and a second bottom portion of the slot, wherein the coating is on the first bottom portion and/or on the second bottom portion, wherein the rotor blade is a turbine blade driven by a working fluid, and wherein the aerofoil portion of the rotor blade includes a cooling duct for receiving a cooling fluid, wherein the first bottom portion comprises a lobe portion, and wherein the coating is on the lobe portion or on a part of the second bottom portion which lies opposite the lobe portion, wherein the first bottom portion comprises a first lobe portion and a second lobe portion, and wherein the coating is on one of the first or second lobe portions only and only on a part which is disposed closer to the other of the first or second lobe portions, or the coating is on the second bottom portion such that the coating lies opposite only the part of one of the first or second lobe portions which is disposed closer to the other of the first or second lobe portions.