|
gptkbp:instance_of
|
gptkb:turbofan_engine
|
|
gptkbp:application
|
civil helicopters
|
|
gptkbp:average_temperature
|
up to 1,000 ° C
|
|
gptkbp:combustor_type
|
annular
|
|
gptkbp:compression_ratio
|
16:1
|
|
gptkbp:configuration
|
free turbine
|
|
gptkbp:control_system
|
gptkb:FADEC
digital control system
|
|
gptkbp:cooling_system
|
gptkb:oil
air-cooled
|
|
gptkbp:design_purpose
|
medium lift helicopters
|
|
gptkbp:development
|
5 years
|
|
gptkbp:diameter
|
600 mm
|
|
gptkbp:emissions_standard
|
ICAO Chapter 4
|
|
gptkbp:engine_configuration
|
modular
flexible mounts
|
|
gptkbp:engine_power
|
high performance
up to 20,000 hours
|
|
gptkbp:engine_type
|
gptkb:turbofan_engine
Makila 1 A, Makila 1 B
|
|
gptkbp:exhaust_system
|
gptkb:straight
|
|
gptkbp:first_flight
|
gptkb:2005
|
|
gptkbp:fuel_capacity
|
lightweight
compact design
|
|
gptkbp:fuel_economy
|
high
200 kg/h
|
|
gptkbp:fuel_type
|
gptkb:Jet_A-1
dual fuel system
|
|
gptkbp:gearbox
|
reduction gearbox
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Makila 1 R engine
|
|
gptkbp:is_tested_for
|
extensive ground testing
|
|
gptkbp:launch_date
|
30 seconds
|
|
gptkbp:launch_window
|
starter-generator
|
|
gptkbp:length
|
1,200 mm
|
|
gptkbp:maintenance
|
1,500 hours
|
|
gptkbp:manufacturer
|
gptkb:Safran_Helicopter_Engines
|
|
gptkbp:market_segment
|
commercial aviation
|
|
gptkbp:noise_level
|
low
85 d B
|
|
gptkbp:number_of_stages
|
gptkb:3
|
|
gptkbp:operational_range
|
-40 to 50 ° C
|
|
gptkbp:power_output
|
1,800 shp
|
|
gptkbp:propulsion
|
6:1
|
|
gptkbp:regulatory_compliance
|
EASA and FAA
|
|
gptkbp:service_ceiling
|
20,000 ft
|
|
gptkbp:torque
|
1,800 Nm
|
|
gptkbp:turbine_speed
|
40,000 rpm
|
|
gptkbp:turbine_type
|
single-spool
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
|