TDA CR 2.0 16V
Competitive Advantages for General AviationThe TDA CR 2.0 16V engine is an aviation derivative of the automotive 4‑stroke diesel engine with common rail fuel system, controlled by dual FADEC and with a gearbox to power an aircraft by a pull/push propeller.
EASA Certified >> TC EASA E.079
- 30% fuel consumption reduction
- Operation with same fuel of jet aviation engines (kerosene Jet A-1 or JP 8) for easier availability, higher safety and lower cost.
- Good suitability for turbocharging for high specific power and constant performances with the altitude.
- High torque even at low speed to obtain gearbox weight reduction.
- Robustness, reliability and longer maintenance intervals.
- Low lubricant consumption.
| Architecture | - | 4 cylinder in line |
| Bore | mm | 83.0 |
| Stroke | mm | 90.4 |
| Displacement | cm3 | 1955 |
| Valves / cylinder | # | 4 |
| Compression ratio | - | 16.0 |
| Turbocharger | - | Single Stage - WG |
| Fuel Injection System | - | Common Rail 1800 bar |
| Fuel | - | JET A-1 & Diesel Fuel EN 590 |
| Alternators | volt | 28 (sdt 2.8 kW - opt 3.5 kW) |
| EECS | - | DUAL FADEC ECU |
| Dimensions LxWxH | mm | 600 x 507 x 687 (no GearBox) |
| Take Off Power | kW | 160 ( at propeller shaft ) |
| Continous Power | kW | 142 ( at propeller shaft ) |
| Altitude for max power | ft | 8700 |
| Max Operative Altitude | ft | 35000 |
| Min. BSFC | g/kWh | 210 ( at propeller shaft ) |