Editable example inputs. Pressure ratio and efficiencies are assumptions, not measured performance. Fuel, thrust target and operating conditions are not yet specified.
Rotor
Direction
Study rpm
Input kW
Torque Nm
Axial Mach
Axial m/s
Study |beta| in / out, deg
Equal work per rotor; speed schedule holds mean blade speed constant. Animation preserves speed ratios at a reduced visual rate. No motor rating or bearing speed limit is established. Axial-flow estimates omit blade blockage and swirl; reference blade geometry is not regenerated from the velocity triangles.
Combustor and adjustable nozzle
12 outlet guide vanes · 50 mm annular diffuser · 1.6 area ratio · radial electrical feedthroughs · cooling supply provision · separate rear flange with thermal spacers.
Annular combustor concept with perforated liners, dome, six injector envelopes, fuel manifold and igniter. Axial plug travel varies the nozzle annulus; positive travel moves the cone aft and reduces its minimum area. The display samples axial annulus area, excluding support blockage and flow-angle effects. This is not a coupled engine operating point. Gas properties use gamma 1.33 and R 287 J/kg/K; combustion energy balance is not solved.
Isogrid ribs, six ESC heat sinks, an 18-pole AC terminal block and four frame lugs are provisional packaging. Current ratings, motor-phase current, mounting loads, pressure stresses and heat rejection remain unvalidated.
The cooling path marks supply plumbing and stator branches. Flow distribution, return passages, seals, thermal-spacer material and flange stresses still require design.
Clearance budgets and measured operating points
A removable 1 mm casing liner allows future clearance adjustment. The existing 25 × 37 × 7 mm bearing pairs remain provisional. Growth values are allowances, not a thermal or rotordynamic prediction.
No measured compressor map is loaded. The three pressure/temperature stations and six speed pickups are modeled as instrumentation provisions.
Shaft OD / ID: 25 / 20 mm · blade axial width: 18 mm · hub axial width: 22 mm · radial tip clearance: 0.65 mm.
* Reference section angle; smooth spanwise twist ±7°, curved sweep, tangential lean and variable camber / thickness. The 18 mm row envelope and original maximum diameters are retained. Blade shapes are conceptual; CFD optimization has not been performed.
Rotor support: 2 × SKF 71805 ACD/HCP4, 25 × 37 × 7 mm, 25° contact angle, DB pair. Preliminary selection; preload and operating speed depend on actual loads. Motor stator stack: 5.5 mm; power is unspecified.
Drag to rotate the model and scroll to zoom. Side and inlet views are available. Air travels from the larger first stage toward the smaller sixth stage. The inlet nose cone, central tube and motor stators are stationary; adjacent rotors turn in opposite directions. Rotation speed is illustrative. Wiring exits radially through the stationary outlet supports and connects to an 18-pole AC block and six ESCs. A perforated annular combustor feeds the adjustable center-plug nozzle. The casing has a triangular isogrid and four mounting lugs. Hide the entire casing to inspect internal parts; no cutaway is used.