Additively manufactured bladed disk
A bladed disk for a gas turbine engine is provided. The bladed disk includes a rotor disk, a plurality of rotor blades, and an interlocking transition zone. The rotor disk includes a plurality of fused layers of a first material formed via additive manufacturing and defines an outer rim. The plurality of rotor blades includes a plurality of fused layers of a second material formed via additive manufacturing. The interlocking transition zone includes a plurality of projections alternately extending from the outer rim of the rotor disk and the plurality of rotor blades, respectively, to undetachably couple the rotor disk and the plurality of rotor blades.
1. A bladed disk for a gas turbine engine, comprising:
a rotor disk comprising a plurality of fused layers of a first material formed via additive manufacturing, wherein the rotor disk defines an outer rim;
a plurality of rotor blades comprising a plurality of fused layers of a second material formed via additive manufacturing; and
an interlocking transition zone comprising a plurality of projections alternately extending from the outer rim of the rotor disk and the plurality of rotor blades, respectively, to undetachably couple the rotor disk and the plurality of rotor blades, wherein each of the plurality of projections allows for variations in the relative motion between the rotor disk and the plurality of rotor blades.
2. The bladed disk of claim 1 , wherein at least a portion of adjacent projections between the rotor disk and the plurality of rotor blades prevents or limits the relative motion between the rotor disk and the plurality of rotor blades.
3. The bladed disk of claim 1 , wherein the interlocking transition zone defines a fluid channel, the fluid channel being configured to provide fluid communication between the rotor disk and the plurality of rotor blades.
4. The bladed disk of claim 1 , wherein the first material is a first metal alloy and the second material is a second metal alloy.
5. The bladed disk of claim 1 , wherein a brazed joint is located between the rotor disk and the plurality of rotor blades to act as adhesive.