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gptkbp:instance_of
|
gptkb:engine
|
|
gptkbp:bfsLayer
|
4
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|
gptkbp:bfsParent
|
gptkb:General_Electric's_aviation_division
|
|
gptkbp:aircraft_operated
|
gptkb:F-22_Raptor
|
|
gptkbp:application
|
gptkb:aircraft
|
|
gptkbp:average_temperature
|
1,600 ° F
|
|
gptkbp:bypass_ratio
|
5:1
|
|
gptkbp:certification
|
military certification
|
|
gptkbp:combat_radius
|
1,839 km
|
|
gptkbp:compression_ratio
|
30:1
|
|
gptkbp:controls
|
gptkb:full_authority_digital_engine_control_(FADEC)
digital control system
|
|
gptkbp:cooling_system
|
advanced cooling technology
advanced cooling systems
|
|
gptkbp:design
|
modular design
|
|
gptkbp:developer
|
1990s
|
|
gptkbp:diameter
|
3.0 ft
|
|
gptkbp:emissions_standard
|
low
|
|
gptkbp:engine
|
gptkb:aircraft
high performance
advanced materials
high reliability
twin-engine
upgradable
innovative technology
air start
ongoing production
dual-spool
detailed specifications
ground test
developed for F-22 Raptor
|
|
gptkbp:engine_type
|
gptkb:F119-PW-100
high-pressure turbine
|
|
gptkbp:fan_art
|
wide-chord fan
|
|
gptkbp:features
|
thrust vectoring
|
|
gptkbp:first_flight
|
gptkb:1997
|
|
gptkbp:fuel_capacity
|
high
|
|
gptkbp:fuel_type
|
gptkb:JP-8
annular combustor
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
F119-PW-300 Engine
|
|
gptkbp:impact
|
significant impact on aviation.
|
|
gptkbp:is_tested_for
|
extensive testing
|
|
gptkbp:length
|
16.5 ft
|
|
gptkbp:maintenance
|
1,500 hours
|
|
gptkbp:manufacturer
|
gptkb:Pratt_&_Whitney
|
|
gptkbp:max_speed
|
Mach 2.25
|
|
gptkbp:noise_level
|
low
|
|
gptkbp:operational_area
|
air superiority
|
|
gptkbp:propulsion
|
35,000 lbf
19.4:1
|
|
gptkbp:service_ceiling
|
65,000 ft
|
|
gptkbp:successor
|
F135
|
|
gptkbp:supports
|
30,000 lb/s
|
|
gptkbp:type
|
gptkb:engine
|
|
gptkbp:used_in
|
gptkb:Lockheed_Martin_F-22_Raptor
|
|
gptkbp:weight
|
1,800 lb
|