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gptkbp:instance_of
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gptkb:turbofan_engine
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|
gptkbp:application
|
helicopter propulsion
|
|
gptkbp:average_temperature
|
up to 800 ° C
|
|
gptkbp:certification
|
EASA certified
|
|
gptkbp:combustor_type
|
annular combustion chamber
|
|
gptkbp:compression_ratio
|
10:1
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|
gptkbp:compressor_type
|
axial compressor
|
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gptkbp:control_system
|
electronic control unit
|
|
gptkbp:cooling_system
|
air-cooled
direct air cooling
|
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gptkbp:design
|
modular design
|
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gptkbp:diameter
|
0.4 m
|
|
gptkbp:emissions_standard
|
ICAO Chapter 4
|
|
gptkbp:engine
|
advanced materials
state-of-the-art technology
lightweight design
ongoing improvements
modular assembly
|
|
gptkbp:engine_applications
|
gptkb:helicopter
|
|
gptkbp:engine_configuration
|
upgrade options
twin spool
Turbomeca 12345
|
|
gptkbp:engine_power
|
high reliability
2000 hours
|
|
gptkbp:engine_serial_number
|
SN-001
|
|
gptkbp:engine_test_stand
|
Turbomeca test facility
|
|
gptkbp:engine_type
|
free turbine engine
various airframes
Turmo IIIC-1
|
|
gptkbp:exhaust_system
|
axial exhaust
|
|
gptkbp:first_flight
|
gptkb:1960
|
|
gptkbp:fuel_capacity
|
200 liters
|
|
gptkbp:fuel_economy
|
0.5 kg/k W·h
|
|
gptkbp:fuel_type
|
gptkb:Jet_A-1
dual fuel system
|
|
gptkbp:gearbox
|
reduction gearbox
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Turbomeca Turmo IIIC
|
|
gptkbp:ignition_system
|
spark ignition
|
|
gptkbp:is_tested_for
|
onboard diagnostics system
|
|
gptkbp:launch_window
|
starter motor
|
|
gptkbp:length
|
1.2 m
|
|
gptkbp:maintenance
|
500 hours
overhaul capability
|
|
gptkbp:manufacturer
|
gptkb:Turbomeca
|
|
gptkbp:noise_level
|
85 d B
|
|
gptkbp:number_of_stages
|
3 stages
|
|
gptkbp:operational_range
|
500 km
|
|
gptkbp:power_output
|
480 k W
|
|
gptkbp:propulsion
|
mechanical drive
650 lbf
|
|
gptkbp:rotor_speed
|
40000 RPM
|
|
gptkbp:service_ceiling
|
3000 m
|
|
gptkbp:turbine_blades
|
single crystal blades
|
|
gptkbp:turbine_inlet_temperature
|
1200 ° C
|
|
gptkbp:turbine_type
|
two-stage turbine
|
|
gptkbp:type
|
gptkb:turbofan_engine
|
|
gptkbp:used_in
|
gptkb:Aérospatiale_SA_315_Lama
|
|
gptkbp:weight
|
120 kg
|
|
gptkbp:weight_to_power_ratio
|
0.25 kg/k W
|
|
gptkbp:bfsParent
|
gptkb:SA_330_Puma
|
|
gptkbp:bfsLayer
|
8
|