Description
Turbocharged internal combustion engine is a combination of turbine engine and aerial pistonengine, use combustion chamber and compression system the propellers to generate thrust.
The engine combines the characteristics of turbine engine and internal combustion engine such as high thermal efficiency, low fuel consumption, and high altitude.
The engine could have the same dynamic performance as at sea level, and achieve long endurance night at the height of 0-20km.
The engine can supply the power for such as rotary-wing and fixed wing aircraft which applied to general aviation, meteorological observation, agriculture protect, forest conservancy, rescue and relief work. It is also the ideal power of the high altitude long endurance unmanned air vehicle.
Technical Specifications:
| Take-off power | 84 kW @ 5800 r/min |
| Maximum continuous power (<=8000m) | 73.5 kW |
| Pressure ratio | 3.5 |
| Take-off altitude | >= 4500 m |
| Ceiling | >= 9000 m |
| 8500m altitude cruise power | >= 62.5 kW |
| Weight | <= 80 kg |
| Time between overhaul (TBO) | 2000 h |
Key Components of TICE
The TICE has 3 key components which are the aviation turbocharger, the intercooler and the turbocharger control unit.
Aviation Turbocharger
Specification:
Mass flow: 0.03 kg/s ~ 0.23 kg/s
Maximum pressure ratio: >= 3.5
Compressor efficiency (design point): 0.74
Weight: <= 6.5 kg
Intercooler
Specification:
Type: air-to-air
Efficiency (mass flow ratio = 1.1): >= 0.51
Weight: <=2.6 kg
Turbocharger control unit (TCU)
Specification:
Temperature range: -45°C ~ 55°C
Sampling: ±0.5%
lnterface: RS232/RS422/CAN
Weight: <= 0.5 kg
