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gptkbp:instance_of
|
gptkb:jet_engine
|
|
gptkbp:application
|
gptkb:military_aircraft
|
|
gptkbp:average_temperature
|
high temperature
|
|
gptkbp:budget
|
moderate production cost
|
|
gptkbp:certification
|
FAA certified
|
|
gptkbp:check_in_time
|
yes
|
|
gptkbp:combustor_type
|
annular combustor
|
|
gptkbp:compressor_type
|
axial compressor
|
|
gptkbp:control_system
|
digital control system
|
|
gptkbp:cooling_system
|
air-cooled
|
|
gptkbp:design
|
4,000 hours
General Electric engineers
|
|
gptkbp:design_philosophy
|
modular design
|
|
gptkbp:development
|
1965-1972
|
|
gptkbp:development_cost
|
high development cost
|
|
gptkbp:diameter
|
1.2 m
1.0 m
|
|
gptkbp:emissions_standard
|
low emissions
|
|
gptkbp:engine
|
air start
|
|
gptkbp:engine_configuration
|
twin-spool
pylon-mounted
|
|
gptkbp:environmental_impact
|
reduced environmental impact
|
|
gptkbp:facilities
|
NASA facilities
|
|
gptkbp:first_flight
|
gptkb:1972
|
|
gptkbp:fuel_economy
|
high efficiency
0.85 lb/hp/hr
|
|
gptkbp:fuel_type
|
gptkb:Jet_A-1
|
|
gptkbp:gearbox
|
reduction gearbox
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
M53-P44 engine
|
|
gptkbp:involved_technology
|
advanced materials
|
|
gptkbp:key_feature
|
high thrust-to-weight ratio
|
|
gptkbp:length
|
3.8 m
|
|
gptkbp:maintenance
|
1,000 hours
|
|
gptkbp:manufacturer
|
gptkb:General_Electric
various suppliers
|
|
gptkbp:market_segment
|
gptkb:military_aircraft
|
|
gptkbp:max_speed
|
Mach 2.5
|
|
gptkbp:noise_level
|
low
|
|
gptkbp:operational_range
|
2,500 km
|
|
gptkbp:operational_status
|
in service
|
|
gptkbp:power_output
|
16,000 to 22,000 lbf
|
|
gptkbp:predecessor
|
gptkb:J79_engine
|
|
gptkbp:project
|
ongoing improvements
|
|
gptkbp:propulsion
|
no
22,000 lbf
|
|
gptkbp:reliability
|
high reliability
|
|
gptkbp:service_entry
|
gptkb:1974
|
|
gptkbp:successor
|
gptkb:F110_engine
|
|
gptkbp:turbine_type
|
high bypass turbine
|
|
gptkbp:type
|
gptkb:turbofan_engine
|
|
gptkbp:used_in
|
gptkb:Mc_Donnell_Douglas_F-15_Eagle
|
|
gptkbp:weight
|
1,200 kg
|
|
gptkbp:weight_to_thrust_ratio
|
0.054
|
|
gptkbp:bfsParent
|
gptkb:Snecma_Propulsion
gptkb:Snecma_Moteurs
|
|
gptkbp:bfsLayer
|
6
|