Unitized rotor assembly
A method of making a rotor assembly of a turbojet includes building the rotor assembly via layer-by-layer additive manufacturing. A turbine portion is formed and a compressor portion is integrally formed with the turbine portion. A shaft portion is integrally formed with the compressor portion. A material of the rotor assembly includes a nickel based alloy.
1. A method of making a rotor assembly of a turbojet, the method comprising:
building, via layer-by-layer additive manufacturing, the rotor assembly, wherein building the rotor assembly comprises:
forming a turbine portion;
forming a compressor portion integrally with the turbine portion;
forming a shaft portion integrally with the compressor portion, wherein a material of the rotor assembly comprises a nickel based alloy;
forming a plurality of internal cavities within the rotor assembly; and
forming a structural member within the rotor assembly, wherein the structural member is positioned between and separates two of the plurality of internal cavities apart from each other and the structural member is disposed between the turbine portion and the compressor portion.
2. The method of claim 1 , further comprising forming a cooling passage in the rotor assembly.
3. The method of claim 1 , further comprising applying a heat treatment to the rotor assembly.
4. The method of claim 3 , further comprising hot isostatic pressing the rotor assembly.
5. The method of claim 1 , further comprising smoothing a portion of a surface of the rotor assembly.
6. The method of claim 1 , wherein the layer-by-layer additive manufacturing comprises laser beam melting or electron beam melting.
7. The method of claim 1 , wherein the nickel based alloy material comprises Inconel 718, Waspaloy, Haynes 282, Inconel 713, Inconel 738, Mar M 247, or Inconel 792.
8. A rotor assembly of a turbojet, the rotor assembly comprising:
a turbine portion;
a compressor portion integrally formed with the turbine portion;
a shaft portion integrally formed with the compressor portion, wherein a material of the rotor assembly comprises a nickel based alloy;
a plurality of internal cavities within the rotor assembly; and
a structural member within the rotor assembly, wherein the structural member is positioned between and separates two of the plurality of internal cavities apart from each other and the structural member is disposed between the turbine portion and the compressor portion.
9. The rotor assembly of claim 8 , further comprising a cooling passage in the rotor assembly.
10. The rotor assembly of claim 8 , wherein the nickel based alloy material comprises Inconel 718, Haynes 282, Inconel 713, Inconel 738, Mar M 247, or Inconel 792.