Statements (58)
| Predicate | Object |
|---|---|
| gptkbp:instance_of |
gptkb:engine
|
| gptkbp:bfsLayer |
4
|
| gptkbp:bfsParent |
gptkb:Bell_430
|
| gptkbp:application |
helicopters
|
| gptkbp:armament |
gptkb:3
|
| gptkbp:certification |
FAA certified
certified for various applications |
| gptkbp:compression_ratio |
8.5:1
|
| gptkbp:controls |
gptkb:full_authority_digital_engine_control_(FADEC)
|
| gptkbp:cooling_system |
air-cooled
|
| gptkbp:diameter |
0.4 m
|
| gptkbp:displacement |
1.5 L
|
| gptkbp:drivetrain |
reduction gearbox
|
| gptkbp:engine |
gptkb:Rolls-Royce_250-C20
advanced materials commercial aviation high reliability high power-to-weight ratio compact design widely used in the industry global support network proven track record fuel-efficient operation state-of-the-art engineering light helicopter engine starter-generator system single-shaft popular in the helicopter market continuous improvements over the years developed from the original 250 series part of Rolls-Royce's heritage. |
| gptkbp:engine_type |
various helicopter models
free turbine turbo-shaft C20 B variant |
| gptkbp:first_flight |
gptkb:1960
|
| gptkbp:fuel_capacity |
1.2 m
150 kg 0.4 m 0.5 kg/hp/hr |
| gptkbp:fuel_type |
gptkb:Jet_A-1
|
| https://www.w3.org/2000/01/rdf-schema#label |
Rolls-Royce 250-C20 B
|
| gptkbp:ignition_system |
annular combustion chamber
|
| gptkbp:introduced |
gptkb:1960
|
| gptkbp:length |
1.2 m
|
| gptkbp:maintenance |
500 hours
modular design for easy maintenance |
| gptkbp:manufacturer |
gptkb:Rolls-Royce
|
| gptkbp:max_speed |
42000
|
| gptkbp:notable_users |
gptkb:Bell_Helicopter
|
| gptkbp:operational_history |
used in military and civilian aircraft
|
| gptkbp:origin |
gptkb:United_Kingdom
|
| gptkbp:power_output |
420 shp
|
| gptkbp:powers |
2.8 k W/kg
|
| gptkbp:propulsion |
2.8 k W/kg
420 lbf |
| gptkbp:successor |
gptkb:Rolls-Royce_250-C30
|
| gptkbp:weight |
150 kg
|