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Engine · 993-ENG-K16-TURBINE-WHEEL-IN718-F0-0001

K16 turbine wheel, IN718 F0 concept

ConceptNot authorised until engineering review

Clean-sheet concept of a twelve-blade K16 hot rotor to screen the value and limits of an IN718 LPBF route. The diameters, blade count and part reference come from supplier catalogues; all profiles and interfaces remain hypothetical.

Concept CAD rendering for 993-eng-k16-turbine-wheel-in718-f0-0001.
Not a photograph, not a render of a manufactured part, not evidence of fit or function.
Concept CAD orthographic views for 993-eng-k16-turbine-wheel-in718-f0-0001.
Front, side and top views of the same concept CAD. Dimensions describe the model; fit on the car remains unverified.

The design

Vehicle
Porsche 993, 1995–1998
Variants
993 Turbo
Porsche part numbers
Not recorded
Category
Turbocharger turbine wheel
Geometry basis
Mixed
Preferred process
Not chosen yet
Other candidate processes
Laser powder-bed fusion (metal printing), Direct metal laser sintering (metal printing), casting, CNC machining
Material
EOS NickelAlloy IN718 API, M290 40 µm, heat treated for comparison
Material standard
UNS N07718; program-specific rotor, process, heat treatment and allowables specification to be contracted

Known limits

  • Only reference 5316-120-5000, the diameters, twelve blades, tip height and shaft diameter are published, by replacement-part catalogues.
  • The 20 mm axial envelope, the disk, the hub and the straight four-step blades are synthetic.
  • The STEP excludes the full shaft, the weld, the aerodynamic profiles, fillets, clearances and balancing details.
  • The speed of 103,464 rpm comes from the synthetic F1 compressor point, not from a K16 measurement.
  • The F0 fails the root and thermal-gradient screens at the 1.5 threshold; the gas context also exceeds the generic range stated by EOS.
  • The EOS properties are room-temperature coupons of the API process, not hot HCF, creep or burst allowables.
  • The single-point power balance replaces neither a turbine map, nor rotating CFD, nor CHT, nor rotordynamics.
  • The STEP proves only a readable BREP and is authorized neither for manufacturing, nor rotation, nor turbo or engine use.

Post-processing it would need

  • Blade orientation and supports to be qualified against the recoater
  • Traced stress relief, solution treatment, gas quench and aging
  • HIP to be decided on defects, creep, toughness, HCF and burst
  • Machining of the shaft interface, back face, datums and allowances
  • Controlled profiling and polishing of blades and fillets
  • Wheel-to-shaft joining process or one-piece shaft to be qualified
  • Individual then rotor balancing, spin proof and contained overspeed

What a supplier would have to provide

  • Traceable EOS M290 machine, IN718 API parameter set, software, parameters, powder and lot
  • Oriented coupons with tensile, HCF, LCF, creep, rupture, toughness and crack growth at temperature
  • Distortion witnesses and capability after finishing of the 0.8 mm tips
  • Full CT before and after machining with zoned defect criteria
  • FPI, metallography, microstructure, hardness, roughness and residual stresses
  • Metrology of profiles, fillets, interface, runout and polar inertia
  • High-speed balancing, overspeed, burst and containment before turbo bench testing

Sources