|
gptkbp:instance_of
|
gptkb:turbofan_engine
|
|
gptkbp:accessories
|
gptkb:gasoline
|
|
gptkbp:application
|
helicopters
utility helicopters
|
|
gptkbp:armament
|
gptkb:3
|
|
gptkbp:average_temperature
|
up to 800 ° C
|
|
gptkbp:certification
|
EASA certified
|
|
gptkbp:compression_ratio
|
8:1
|
|
gptkbp:control_system
|
hydromechanical
|
|
gptkbp:cooling_system
|
air-cooled
|
|
gptkbp:design
|
gptkb:compact
|
|
gptkbp:development
|
gptkb:Turbomeca
|
|
gptkbp:diameter
|
0.4 m
|
|
gptkbp:emissions_standard
|
low
|
|
gptkbp:engine
|
gptkb:Turbomeca_Astazou_IIIB
starter motor
|
|
gptkbp:engine_accessories
|
gptkb:gasoline
|
|
gptkbp:engine_configuration
|
gptkb:compact
free turbine
|
|
gptkbp:engine_emissions
|
low
|
|
gptkbp:engine_market
|
military and civilian
|
|
gptkbp:engine_operating_temperature
|
up to 800 ° C
|
|
gptkbp:engine_power
|
high
370 k W
|
|
gptkbp:engine_service_life
|
2000 hours
|
|
gptkbp:engine_thrust
|
500 to 600 lbf
|
|
gptkbp:engine_type
|
turboshaft
|
|
gptkbp:first_flight
|
gptkb:1956
|
|
gptkbp:fuel_capacity
|
120 kg
1.2 m
0.4 m
|
|
gptkbp:fuel_economy
|
0.5 kg/k W·h
|
|
gptkbp:fuel_type
|
gptkb:Jet_A-1
|
|
gptkbp:gearbox
|
reduction gearbox
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Turbomeca Astazou II
|
|
gptkbp:ignition_system
|
spark ignition
|
|
gptkbp:length
|
1.2 m
|
|
gptkbp:maintenance
|
500 hours
|
|
gptkbp:manufacturer
|
gptkb:Turbomeca
|
|
gptkbp:market
|
military and civilian
|
|
gptkbp:noise_level
|
low
|
|
gptkbp:operational_range
|
varies by application
|
|
gptkbp:power_output
|
370 k W
|
|
gptkbp:propulsion
|
500 to 600 lbf
|
|
gptkbp:reliability
|
high
|
|
gptkbp:service
|
2000 hours
|
|
gptkbp:successor
|
gptkb:Turbomeca_Astazou_IIIB
|
|
gptkbp:type
|
gptkb:turbofan_engine
|
|
gptkbp:used_in
|
gptkb:Aérospatiale_SA_315_Lama
|
|
gptkbp:weight
|
120 kg
|