Patent ID: 8882442
Filing Date: 2014-11-11
Classification: B23K,B23P,F01D,F05B,F05C,F05D,Y10T

Abstract:
1. A component for a gas turbine, comprising; a rotor base made of a high temperature-resistant nickel alloy; and a plurality of turbine blades joined to the rotor base, each turbine blade comprising a rotor blade made of a titanium alloy and a blade root, the blade root being configured as an adapter element made of a material weldable to the titanium alloy as well as to the high temperature-resistant nickel alloy and being integrally fused to the rotor base and to the rotor blade, the adapter element having at least a first layer of the high temperature-resistant nickel alloy, and at least a second layer of the titanium alloy, and at least an interlayer between the first and second layers as a diffusion barrier for elements that form brittle phases.