Patent ID: 9719371
Date: 2017-08-01
CPC Classifications: C23C,C25D,F01D,F05D

Claim:
1. A vane device for a gas turbine, the vane device comprising: a first airfoil comprising a first suction side and a first pressure side, a second airfoil comprising a second suction side and a second pressure side, an inner shroud, and an outer shroud, wherein the first airfoil and the second airfoil are arranged between the inner shroud and the outer shroud, wherein the first airfoil and the second airfoil are at least partially coated with a MCrAlY coating, wherein at least the first suction side comprises a coated surface section which is coated with a thermal barrier coating and which represents at least a part of the total surface of the first suction side, and wherein at least the inner shroud or the outer shroud comprises a further coated surface section which is coated with a further thermal barrier coating, wherein the inner shroud comprises an inner platform, and wherein the outer shroud comprises a further inner platform, wherein an inner surface of the inner platform and a further inner surface of the further inner platform are washed during operation of the gas turbine by a working fluid of the gas turbine, wherein the inner surface of the inner platform and/or the further inner surface of the further inner platform comprises the further coated surface section, wherein the first airfoil further comprises a first leading edge and a first trailing edge, wherein the second airfoil further comprises a second leading edge and a second trailing edge, wherein the further coated surface section is located onto the inner platform and/or the further inner platform at a section which is located downstream of the first trailing edge and the second trailing edge, wherein the first pressure side and the second pressure side are free of a thermal barrier coating, and wherein the further coated surface section has a width extending from the platform trailing edge a distance between approximately 50% to approximately 80% of a dimension from the platform trailing edge to aerofoil trailing edge, wherein the thermal barrier coating and/or the further thermal barrier coating comprises a thinning out section, wherein in the thinning out section the thickness of the thermal barrier coating is smoothly reduced in a direction to an edge of the respective coated surface section and/or the further coated surface section.