|
gptkbp:instanceOf
|
turbojet engine
|
|
gptkbp:application
|
helicopters
|
|
gptkbp:controls
|
manual control
|
|
gptkbp:coolingSystem
|
air-cooled
|
|
gptkbp:diameter
|
0.3 m
|
|
gptkbp:emissionsStandard
|
low emissions
|
|
gptkbp:engine
|
compact design
inline engine layout
|
|
gptkbp:engineConfiguration
|
discontinued
turbojet engine configuration
|
|
gptkbp:engineType
|
axial
simple design
single-stage
air start
Artouste II, Artouste III
|
|
gptkbp:firstFlight
|
1955
|
|
gptkbp:fuel_capacity
|
high
0.5 kg/s
|
|
gptkbp:fuelType
|
annular combustor
Aviation kerosene
|
|
gptkbp:hasArea
|
ground testing
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Turbomeca Artouste I
|
|
gptkbp:introduced
|
1955
|
|
gptkbp:is_used_in
|
gptkb:Aérospatiale_Alouette_II
|
|
gptkbp:length
|
1.2 m
|
|
gptkbp:maintenance
|
500 hours
|
|
gptkbp:manufacturer
|
gptkb:Turbomeca
|
|
gptkbp:maximum_speed
|
0.8 Mach
|
|
gptkbp:noise_level
|
85 dB
|
|
gptkbp:notableUsers
|
gptkb:French_Army
|
|
gptkbp:operational_status
|
military and civilian aircraft
|
|
gptkbp:performances
|
2000 hours
reliable performance
detailed specifications available.
|
|
gptkbp:propulsion
|
4.17
500 lbf
|
|
gptkbp:related_engine
|
Brayton_cycle
|
|
gptkbp:retired
|
1970s
|
|
gptkbp:successor
|
gptkb:Turbomeca_Artouste_II
|
|
gptkbp:type
|
turbojet
|
|
gptkbp:weight
|
120 kg
|