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gptkbp:instance_of
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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:cancellation_reason
|
gptkb:battle
|
|
gptkbp:certification
|
FAA certified
|
|
gptkbp:check_in_time
|
gptkb:battle
|
|
gptkbp:compression_ratio
|
30:1
|
|
gptkbp:controls
|
fly-by-wire
digital electronic control
|
|
gptkbp:cooling_system
|
air-cooled
|
|
gptkbp:developer
|
1990s
|
|
gptkbp:diameter
|
1.1 m
3.0 ft
|
|
gptkbp:engine
|
advanced materials
ongoing improvements
high reliability
Brayton cycle
twin-spool
high thrust-to-weight ratio
high thermal efficiency
air start
pylon-mounted
detailed specifications available.
developed for the F-22 program
|
|
gptkbp:engine_type
|
gptkb:F119-PW-100
high-bypass turbofan
|
|
gptkbp:features
|
vectoring thrust
|
|
gptkbp:first_flight
|
gptkb:1997
|
|
gptkbp:fuel_capacity
|
0.5 lb/lbf/hr
|
|
gptkbp:fuel_type
|
gptkb:JP-8
gptkb:full_authority_digital_engine_control_(FADEC)
annular combustor
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
F119-PW-900 Engine
|
|
gptkbp:investment
|
40 psi
|
|
gptkbp:is_tested_for
|
ground testing
|
|
gptkbp:length
|
16.5 ft
|
|
gptkbp:maintenance
|
1,000 hours
|
|
gptkbp:manufacturer
|
gptkb:Pratt_&_Whitney
|
|
gptkbp:max_speed
|
Mach 2.25
|
|
gptkbp:propulsion
|
gptkb:battle
11.7 lbf/lb
35,000 lbf
|
|
gptkbp:service_ceiling
|
65,000 ft
|
|
gptkbp:type
|
gptkb:engine
|
|
gptkbp:used_in
|
gptkb:Lockheed_Martin_F-22_Raptor
|
|
gptkbp:weight
|
3,000 lb
|