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gptkbp:instance_of
|
gptkb:turbofan_engine
|
|
gptkbp:application
|
civil helicopters
|
|
gptkbp:average_temperature
|
up to 1,000 ° C
|
|
gptkbp:certification
|
EASA certified
|
|
gptkbp:combustor_type
|
annular combustor
|
|
gptkbp:compression_ratio
|
16:1
|
|
gptkbp:compressor_type
|
axial compressor
|
|
gptkbp:configuration
|
free turbine
|
|
gptkbp:control_system
|
gptkb:FADEC
|
|
gptkbp:cooling_system
|
air-cooled
|
|
gptkbp:design_purpose
|
helicopter propulsion
|
|
gptkbp:diameter
|
600 mm
|
|
gptkbp:emissions_standard
|
EURO 1
|
|
gptkbp:engine
|
starter-generator
|
|
gptkbp:engine_configuration
|
free turbine
|
|
gptkbp:engine_design_purpose
|
helicopter propulsion
|
|
gptkbp:engine_power
|
1,800 shp
|
|
gptkbp:engine_stages
|
2
|
|
gptkbp:engine_temperature
|
up to 1,000 ° C
|
|
gptkbp:engine_thrust_to_weight_ratio
|
6:1
|
|
gptkbp:engine_type
|
turboshaft
|
|
gptkbp:first_flight
|
gptkb:2005
|
|
gptkbp:fuel_capacity
|
1,200 mm
300 kg
600 mm
|
|
gptkbp:fuel_economy
|
200 kg/h
|
|
gptkbp:fuel_type
|
gptkb:Jet_A-1
|
|
gptkbp:gearbox
|
reduction gearbox
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Makila 1 S engine
|
|
gptkbp:launch_window
|
starter-generator
|
|
gptkbp:length
|
1,200 mm
|
|
gptkbp:maintenance
|
3,500 hours
|
|
gptkbp:manufacturer
|
gptkb:Safran_Helicopter_Engines
|
|
gptkbp:noise_level
|
85 d B
|
|
gptkbp:number_of_stages
|
2
|
|
gptkbp:power_output
|
1,800 shp
|
|
gptkbp:propulsion
|
6:1
|
|
gptkbp:service_ceiling
|
15,000 ft
|
|
gptkbp:torque
|
1,800 Nm
|
|
gptkbp:turbine_type
|
single-stage turbine
nickel-based superalloy
|
|
gptkbp:type
|
turbo-shaft
|
|
gptkbp:used_in
|
gptkb:Eurocopter_EC225_Super_Puma
|
|
gptkbp:weight
|
about 300 kg
|
|
gptkbp:bfsParent
|
gptkb:Safran_Helicopter_Engines
|
|
gptkbp:bfsLayer
|
5
|