|
gptkbp:instance_of
|
gptkb:turbofan_engine
|
|
gptkbp:application
|
gptkb:transport_aircraft
|
|
gptkbp:armament
|
gptkb:4
|
|
gptkbp:average_temperature
|
-40 to 50 ° C
|
|
gptkbp:certification
|
FAA certified
|
|
gptkbp:compression_ratio
|
12:1
|
|
gptkbp:compressor_type
|
gptkb:6
|
|
gptkbp:configuration
|
twin-shaft
|
|
gptkbp:control_system
|
gptkb:full_authority_digital_engine_control_(FADEC)
|
|
gptkbp:cooling_system
|
gptkb:Interpol
air-cooled
|
|
gptkbp:diameter
|
1,200 mm
|
|
gptkbp:emissions_standard
|
low emissions
|
|
gptkbp:engine
|
Brayton cycle
T56-A-15
|
|
gptkbp:engine_configuration
|
free turbine
pylon-mounted
|
|
gptkbp:engine_power
|
10,000 hours
|
|
gptkbp:engine_type
|
gptkb:turbofan_engine
T56-A-1, T56-A-3, T56-A-15
|
|
gptkbp:first_flight
|
gptkb:1954
|
|
gptkbp:fuel_capacity
|
1,500 liters
|
|
gptkbp:fuel_economy
|
0.5 lb/hp/hr
|
|
gptkbp:fuel_type
|
Jet fuel
dual fuel system
|
|
gptkbp:gearbox
|
reduction gearbox
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
T56-A-14 turboprop
|
|
gptkbp:ignition_system
|
spark ignition
|
|
gptkbp:investment
|
30 psi
|
|
gptkbp:is_tested_for
|
ground testing required
|
|
gptkbp:launch_window
|
air start
|
|
gptkbp:length
|
1,800 mm
|
|
gptkbp:maintenance
|
1,500 hours
|
|
gptkbp:manufacturer
|
gptkb:Pratt_&_Whitney
|
|
gptkbp:noise_level
|
85 d B
|
|
gptkbp:operational_range
|
0 to 30,000 feet
|
|
gptkbp:power_output
|
4,600 shp
|
|
gptkbp:propeller
|
4.5 m
variable pitch
constant-speed propeller
|
|
gptkbp:propulsion
|
4,600 lbf
3.83 hp/kg
|
|
gptkbp:reliability
|
high reliability
|
|
gptkbp:service_entry
|
gptkb:1956
|
|
gptkbp:speed
|
1,100 RPM
|
|
gptkbp:turbine_type
|
2
nickel-based superalloy
|
|
gptkbp:type
|
turbo-prop engine
|
|
gptkbp:used_in
|
gptkb:Lockheed_C-130_Hercules
|
|
gptkbp:weight
|
1,200 kg
|
|
gptkbp:bfsParent
|
gptkb:P-3_Orion
gptkb:Lockheed_Martin_P-3_Orion
|
|
gptkbp:bfsLayer
|
5
|