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gptkbp:instance_of
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gptkb:turbofan_engine
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gptkbp:application
|
civil and military helicopters
|
|
gptkbp:average_temperature
|
high turbine inlet temperature
high operating temperature range
|
|
gptkbp:certification
|
EASA certified
|
|
gptkbp:compressor_type
|
axial compressor
|
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gptkbp:configuration
|
single shaft
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gptkbp:control_system
|
gptkb:full_authority_digital_engine_control_(FADEC)
digital control system
|
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gptkbp:cooling_system
|
air-cooled
active cooling system
|
|
gptkbp:emissions_standard
|
ICAO Chapter 4
|
|
gptkbp:engine
|
ongoing research and development
global support network
innovative design features
spare parts availability
quick engine start
competitive market position
safe engine shutdown
upgradeable engine design
|
|
gptkbp:engine_configuration
|
modular design
|
|
gptkbp:engine_power
|
up to 20,000 hours
optimized performance for helicopters
|
|
gptkbp:first_flight
|
gptkb:2005
|
|
gptkbp:fuel_capacity
|
1,500 mm
600 mm
|
|
gptkbp:fuel_economy
|
high fuel efficiency
low fuel consumption
|
|
gptkbp:fuel_type
|
gptkb:Jet_A-1
|
|
gptkbp:gearbox
|
reduction gearbox
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Makila 1 V engine
|
|
gptkbp:is_tested_for
|
extensive testing conducted
|
|
gptkbp:launch_platform
|
electronic starter
|
|
gptkbp:maintenance
|
3,500 hours
|
|
gptkbp:manufacturer
|
gptkb:Safran_Helicopter_Engines
|
|
gptkbp:max_continuous_power
|
1,800 shp
|
|
gptkbp:max_takeoff_weight
|
2,000 shp
|
|
gptkbp:noise_level
|
low vibration levels
low noise emissions
|
|
gptkbp:power_output
|
1,800 shp
|
|
gptkbp:propulsion
|
6:1
0.17 kg/shp
|
|
gptkbp:reliability
|
high reliability
|
|
gptkbp:service_entry
|
gptkb:2005
|
|
gptkbp:training
|
pilot and technician training available
|
|
gptkbp:turbine_type
|
free turbine
|
|
gptkbp:type
|
turbo-shaft
|
|
gptkbp:used_in
|
gptkb:Eurocopter_EC225_Super_Puma
|
|
gptkbp:warranty
|
warranty options available
|
|
gptkbp:weight
|
about 300 kg
|
|
gptkbp:bfsParent
|
gptkb:Safran_Helicopter_Engines
|
|
gptkbp:bfsLayer
|
5
|